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Flight Readiness Review

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2. 58 3 715 Results eM aaa DET dg 58 3 7 1 6 Ahalysis cote ere cre e en pe D ae e ec reete nee ve ts 59 3 12 Verlficatloli a code e I be M dictns iM ipte novato 59 3 8 Vehicle SALVARSAN So cp d uta eR 59 ESSE SCIL 59 3 8 2 Personnel EIaz ads oo eee ivo ib dua dime neu iiM e ud LE t 60 3 8 3 Environmental CONCERNS eos 61 3 9 mL SR 61 3 9 1 Intestaton PAM toa o ide ad AAS a OSS 61 3 9 1 1 Payload to i teet m eite t teet d dete d dien 61 3 9 1 2 Vehicle to Ground Interface wo cccccccccesseccccecceseseeeeecceeeusseuseeeseeeeeeeseaueeuceeeeseuseuaees 62 3 0 2 Element Compatibility sesane as 62 3 9 3 Housing Integrity lo DU a E E a A A 62 PAGS CAMS al ns sear ir e 64 4 1 Seicence Valem RSS 64 4 11 JAGSE Objec Ves iis e bessie een aS 64 41 2 64 21 3 Mission SUCCES S CHI S 66 al saa savas ag te tent 64 4 1 4 AGSE Experimental Approach eee ee tette eene enne netta setenta seen 65 41 3 Variable Control e gues Eust deus EON 65 4 2 AGSE Design C E M 66 42 T1 Tower SO UIUC LUIS vies nae de ase
3. sss 184 List of Figures Figur l Eielit Prollle ver ce ia c SEARS 17 Figure 2 OpenRocket Design and Solid Works Model eee 18 Ereure 5 Rocket DIMENSIONS docete eo a uda cubes 19 Figure 4 Pin and Motor Dimensions oor 20 Figure 5 Full Seale Rocket o niea edle tied uu epe Ue eee ee 20 Figure 6 Body Tube Molds 48 inches ei Monte Leodii iet eniti ta preci onu 22 Figure 7 Body Tube Mold eee 23 Figure 8 Tubing Mold Shape Half Cirele 5 ine a ee tds 23 Figure 9 Tubing Connections Full Circle 24 Figure 10 Avionics Flange Window Open and Closed eee 24 Eigure LLE Nose Gone Mold Halves tuuc otn 25 Figure 12 Nose Cone Mold Pinal ConstruetiOl acido teed pe tace i Hr HEU e t He ees 25 Figure 13 Mount Mo nt 2 i eit ci evidence 26 14 Motor Retention Systeln oid o aep ease ect aed iae seen uide tee eeu oes 27 Figure 15 PVC Couplers Installed ote ebd Maen mua 27 Figure 16 Full Scale Rocket during Launch ies titii 28 Figure 17 DC Motor and Gearing SySUeIm eerie etre qoot ed eer See 33 Figure 18 Payload Section Electrical Schematic Reus 33 Figure 19 Arduino Micro in T
4. uoti ses cats ee 66 41 2 2 Tower Motor amd Aper oo oda e a SAAR aS 68 4 2 3 Tower Sled nnne EG RS Ress 69 424 SOOIDOLEB SY eoe ade eiit dan Sees Qs iE at dust ds ini dot Me Ert 71 4 2 5 leniter Insertion Device ad SSA 72 4 3 PSG tn AT ATOM s edere esc 73 49 1 S o Resets e oan 75 4 3 2 Instrurment Precision Sissel e aa 75 4 4 Testing and Verification Plans usas o EO Rr ho Toro E Rb Fatum cnade 75 4 5 AGSE TS ORAL OM tesi iain A 77 ASL Integration Plan iiie etr en UNSER RETE SET Foe S aU aa reg 77 45 2 ANGSE Timeframe i tester ees E 79 4 6 Verifica T C ET 79 4 6 1 Requirement Verification ocius 79 AT PGS ELS ADC Ly Ra RRR RSA aa 80 4 7 1 Safety Analysis a eoe ee YEA MURS SHAB US SENTI dua Ud 80 47 2 Personnel Hazards ues deti eed ada odas e dieu edt ute Mua end 8l 4 7 3 Environmental Concerns ose ERSTE donum uh ui eh 81 Launch Operations tactis a rs de RES RAT VES S E LUE 82 5 1 REP TAR ts OSS 82 Sell Preeti ght m EM LER 82 D2 RECOVERY noresi en as di iiu ule id 83 31 3 Motor 83 25 1 4 AGSE Assembly Set p IA dU ELK es Q
5. eee 52 Figure 37 Lateral Wind Drift vs Wind Speed for the Best and Worst Case Scenarios 55 Figure 38 Surface Plot of Wind Drift with Respect to Direction and Speed 56 Ergure 39 Payload HOUSING SNARES Sea a tM 63 Figure 40 Figure 41 Figure 42 Figure 43 Figure 44 Figure 45 Figure 46 Figure 47 Figure 48 Figure 49 Figure 50 Figure 51 Figure 52 Figure 53 Figure 54 Figure 55 Tower Foot with Milled Coupler and Flange Bearing sass 66 Ladder Design of Tower Structure qi ed eb pis 67 AGSE Loading Configuration sss 68 AGSE Launching configuration 68 Motor Mount TI ay eR Siig ct atte Eum E cd OE d Ld Ld E 69 Tower Sled coes uet eite dii gate EERSTE ASANE 69 Sled sis ose LN adn sates ei 70 Top down View of Scorbot Operating Range sees 71 Side View of Scorbot Operation Range essere nennen 71 Teniter Insertion Drawings ie Bade Ba Naess Ble 72 Un mounted Igniter Insertion System enne enne 73 Neorbot ERV odes ceno catene ur p DR 74 Payload Tube etf e eiue imu iA ese codd OAM 76 SCHenmadlie d eid ees 78 ORM V CIO cT ccm 88 ORM Risk Matrix iiid eite poetic eo Reo tee QUEE 88 List of Table
6. Box 87 Bellevue NE 68005 Articles of Incorporation and Bylaws High Power Rocketry Safety Code Tripoli Motor Testing Committee Testing Policies Appendix A Additional Tripoli Rulings A 1 NFPA 1127 was adopted by the Tripoh Board of Directors as the Tripoli Safety Code Tripoli Report April 1994 Tnpoli Board Minutes New Orleans 21 January 1994 Motion 13 Simce this adoption the code has gone through some revisions Such is the way with codes they are constantly undergoing change to improve and update them when safety prompts or when the federal regulation change or are reinterpreted 2 All Tripoli members who participate in Association activities shall follow the Tripoli Certification Standards A 3 Any Board action s with regard to safety made previous to or after publication of this document shall be a part of the Tripoli Safety Code 4 Increased descent rates for rocket activites conducted at the Black Rock Desert venue are acceptable if needed to msure a controlled descent to remain inside the FAA approved Dispersion Area 5 A rocket motor shall not be ignited by using a switch that uses mercury b Pressure roller switches This edition and all other editions of the High Power Rocketry Safety Code is Copyright 2012 by the Tripoli Rocketry Association Inc All rights reserved Reproduction in whole or in part without written permission is prohibited 7 31 2012 132 E
7. where there Is Immediate access to safety shower and emergency eye wash Wash thoroughly after use Contact lens should not be wom when working with this material Generally speaking working cleanly and following basic precautionary measures wl greatly minimize the potential for harmful exposure to fnis product under normal use conditions OCCUPATIONAL EXPOSURE LIMITS 1 Not established for product as whole Refer to OSHA s Permissible Exposure Level PEL or the ACGIH Guidelines for Information on specific Ingredients MSDS 205 13a Last Revised 26APR13 145 West System Inc Page 3 of 4 WEST SYSTEM 205 Hardener SOLUBILITY IN WATER se SPECIFIC GRAVITY eren 106 FERMO a VOLATILE BY WEIGHT ASTM 2369 07 was used to determine the Volatile Matter Content of mixed epoxy resin and hardener 105 Resin and 205 Hardener mixed together at 5 1 by weight has a density of 1137 g L 9 49 Ibsiga The combined VOC content for 105 205 is 7 91 g L 0 07 insigat HAZARDOUS POLYMERIZATION NE not occur hA AL rii Avokd excessive heat Avoid acids oxidizing materials halogenated organic compounds e g methylene chloride Extemal heating or self heating could result in rapid temperature Increase and serious hazard If such a reaction were to take place In a waste drum the drum could expand and rupture violently DECOMPOSITION PRODUCTS sss Vary fumes and gases when bumed or
8. Liquid Amber Clear Amine Mercaptan CAUSES EYE SKIN AND RESPIRATORY TRACT BURNS MAY CAUSE ALLERGIC SKIN REACTION HARMFUL IF SWALLOWED OR ABSORBED THROUGH SKIN Relevant routes of exposure Skin Inhalation Eyes ingestion Potential Health Effects inhalation Respiratory tract bums May cause respiratory tract irritation May cause irritation to nose and throat Lung damage Skin contact May cause skin bums Allergic skin reaction May be harmful If absorbed through skin Rash Redness Tissue damage Eye contact Burns Severe eye irritation Redness Tissue damage May be harmful If swallowed May cause bums of mouth and throat I swallowed Existing conditions aggravated by Eye skin and respiratory disorders Skin allergies This material is considered hazardous by the OSHA Hazard Communication Standard 29 CFR 1910 1200 See Section 11 for additional toxicological Information 3 COMPOSITION INFORMATION ON INGREDIENTS IDH number 1137985 Product name Loctite Epoxy Heavy Duty Hardener Page 105 158 4 FIRST AID MEASURES Move to fresh alr If breathing Is difficult give oxygen If not breathing give artificial respiration If symptoms develop and persist get medical attention immediately flush skin with plenty of water using soap If available Remove contaminated clothing and footwear Wash clothing before reuse Thoroughly clean shoes before reuse If symptoms develop and persist get medical
9. heated to decomposition Decomposition products may include but not minted to oxides of nitrogen volatile amines ammonia nitric acid aldehydes Adsorption of phenolic solutions through the skin may be very rapid and can cause death Lesser exposures can cause damage to the kidney liver pancreas and spleen and cause edema of the lungs Chronic exposures can cause death from Iver and Kidney damage CARCINOGENICITY MN LL esL C No No UNA ecient No No ingredient of fis product present at levels greater than or equal to 0 1 is identifed as a carcinogen or poten carcinogen by OSHA or 12 ECOLOGICAL INFORMATION tn the non cured form this product may be ramha if released to tne environment Do not allow info sewers on the ground or In any body 13 DISPOSAL CONSIDERATIONS WASTE DISPOSAL METHOD Evaluation of this product using RCRA criteria shows that It is not a hazardous waste either by listing or characteristics In fis purchased form It Is the responsibilty of the user to determine proper disposal incinerate recycie fuel blending or reciaim may be preferred methods when conducted In accordance with federal state and local regulations MSDS 205 13a Last Revised 26APR13 146 West System Inc Page 4 of 4 WEST SYSTEM 205 Hardener TSCA STATUS s All G mponents istad on TSCA Inventory or otherwise comply with TSCA requirements Canada WHMIS Classification DZA Very toxic materia
10. eee REO na eer ere ena E REO 105 6 4 3 2 MIBISSTEM S ite ette tte aveo tette ead hast e ehe oes RASRA 106 6 4 3 3 Girls Only STEM Day nettes teint ene a ERE Fine e dee e NR rnt 106 6 4 3 4 Space Exploration Merit Badge sess nnn nnn 106 6 4 4 Sustainability s s 106 6 4 4 1 Major Sustainability Challenges and Solutions eene 107 6 4 5 Educational Engagement Progress Proposal to 107 6 4 6 Outreach Update erectae NAAR I ray EH BN ENS EVE STAR SR ENS HR Sosa P eene 108 1 a Mode td sai ca teta eee 109 APBENDEIX JN ERR Flysh t STAN etae stax Mires ahora dtd Gel 110 APPENDIX B Component Sizing 112 APPENDIX C Wind Tunnel Test Plancio ca tede eee te haha Mte 114 APPENDIX D Mission Requirements 2 2 pee tb ee pu 120 APPENDIX E Laws and Safety verte cs ae ose veug eu Rau te M ee Dd eger sa 127 E 1 NAR High Power Rocket Safety Code eese eren eee 127 E 2 TRA Code for High Power Rocketry 5 nitet eet eh teen tte ena rane pe 129 E 3 Amateur Rockets pa e as 133 Est Law amp Regulations NAR aiuta cerei etu qned epp a exu cae uela nene I35 APPENDIX Pe 140 APPENDIX G
11. 118 attached with the sting balance attachment Ensure all pressure ports and force measuring devices are securely fitted by inspection then by flow through test section Run program at initial test speed When flow steadies tabulate data for given speed Perform steps 5 6 as needed for each successive test speed at each angle of attack Once all data is taken run again at initial test speed Perform free stream velocity sweep from initial to final test speeds simultaneously tabulating data 10 When finished tabulating velocity sweep move wind tunnel test speed down to 0 11 Shut down wind tunnel and wind tunnel software 12 Detach the assembly in reverse order of attachment 119 APPENDIX D Mission Requirements f Designated Req t Requirement Subsystem 11 The vehicle shall deliver the payload to but not exceeding an Structures amp apogee altitude of 3 000 feet above ground level AGL Propulsion The vehicle shall carry one commercially available barometric altimeter for recording the official altitude used in the competition scoring The altitude score will account for 10 of the team s overall competition score Teams will receive the maximum 1 2 number of altitude points 3 000 by fully reaching the 3 000 feet Avionics AGL mark For every foot of deviation above or below the target a
12. Sop leak without additional risk Dike and absorb with Inert material sand and collect in a suitable closed container Warm soapy water or non flammable safe solvent may be used to dean residual 7 HANDLING AND STORAGE STORAGE TEMPERATURE minimax __ 40 F 4 C 120 F 49 e t tt t t Store In cook dry piace Store In tightly sealed containers to prevent moisture abeorpton and loss of volatiles Excessive heat over long periods of time wil degrade the resin HANDLING PRECAUTIONS prolonged or repeated skin contact Wash thoroughly after handling Launder contaminated clothing before reuse Avoid inhalation of vapors trom heated product Precautionary steps shouid be taken when curing product In large quantities When mixed with epoxy curing agents fnis product causes an exothermic which In large masses can produce enough heat to damage or ignite surrounding materials and emit fumes and vapors Mat vary widely in composition and toxicity EYE PROTECTION GUIDELINES sss Safety gasses with side shields or chemical splash goggles SKIN PROTECTION GUIDELINES Wear liquid proof chemical resistant gloves nitrile buty rubber neoprene Duty rubber or natural rubber and full clothing RESPIRATORYIVENTILATION GUIDELINES Good room ventilation Is usually adequate for most operations Wear a NIOSH MSHA ap
13. Vertical acceleration ft s7 Figure 35 Vertical Motion vs Time at 20 mph 51 100 105 Uonela a32e BIA AIJA E3II 8A uoneJaja22e EIA A1302 EIA The highest apogee occurred at 5 mph with a height of 3095 feet The lowest apogee occurred at 20 mph with a height of 2934 feet At 10 mph and 15 mph the resulting apogees were 3057 and 3025 respectively As sustained winds increase the vertical motion of the rocket will be translated into greater horizontal motion The Navy Rockets team will have the greatest chance of reaching the goal height of 3000 feet as long as winds do not go over 15 mph 3 6 4 Rocket Stability The stability of each motor as compared to angle of attack is shown in Figure 36 This figure was created using the OpenRocket program and allowed the stability margin to be determined throughout flight A stable flight refers to a balance of the six degrees of freedom that the rocket encounters during flight A successful balance of a rocket s flight is when the rocket does not rotate around the pitch or the yaw axis By rotating on these axes the flight will alter course and reduce the performance of the rocket A rocket that has the Center of Gravity CG forward of the Center of Pressure CP will have a positive stability relationship This leads to a rocket being able to fly straight in the direction of the launch rail and have pitch stiffness to deter from external forces attempting to change the
14. 8l Table 18 Hazard Analysis for Project and Safety sess 89 Table 19 Hazard Analysis Tor Vehicle Safety eoe eese er Resa spas uasa tend ee da e de Rea eR SUE 91 Table 20 Hazard Analysis for the AGSE System eecceeescesseceseeceeneeceeneeceeceeceeeeecseeeeseeeeees 94 Table 21 Hazard Analysis for the Student Launch Project seen 95 Table 22 Safety Concerns Tor the Student Launch 96 Table 23 Environmental Impact on the Rocket 2 eei o 97 Table 24 Rocket Impact on the Environment esses ener enne 99 Table 25 Navy Rockets Comprehensive Budget eese 100 Table 26 Full Scale Itemized Budget o quse cda de Dove tu atenta 101 Table 27 Navy Rockets Funding Platte o iet por bee Eh Iis astute terere T 102 Table 28 Milestone Schedule tesa 102 Table 29 Project Punch LIS sesa 103 C l Wind T nel Fest Personnel ter e ou gud satan she daa 116 List of Abbreviations ut Sonat ae Above Ground Level AGSE Autonomous Ground Support Equipment ATAA American Institute of Aeronautics and Astronautics BS e soie eei Boy Scouts of America ec Center of Gravity Computer Numerical Control CCP Center of Pressure DARPA Defense Advanced Research Projects Agency He Gl
15. Harming animals Chemicals leaking into the ground Motor fire Mid air explosion Materials not discarded Rocket Impact on the Environment Rocket material falling directly Be aware of wind direction and Do not launch if the potential for Launched clear of sensitive onto or in such a possible drift harming wildlife locations way that iteffects range of rocket or plants exists wildlife or plant under parachute research the species local wildlife Faulty seals poor Could expose Be cautious in Materials handling of harmful handling of handled materials chemicals to the materials ensure carefully environment components are properly sealed Overheating poor firing sequence Rocket won t launch burns Ensure ignition sequence occurs No motor fire occurred still could harm rocket properly do not taking proper structure operate in precautions excessive heat situations Various causes Parachute won t Test repeatedly deploy rocket to ensure materials will fall sequences occur uncontrollably properly Materials and Hazard to animals Check the area Proper trash may be left and does not look for garbage and attention around the launch good for the area ensure that all directed site rocket supplies toward cleanup and materials are efforts accounted for after launch 99 6 Project Plan 6 1 Budget Plan A comprehensive budget of Navy
16. 122 Teams who are participating in the Maxi MAV competition limited to a 10 000 budget while teams participating in Mini are limited to 5 000 The cost is for the competition rocket and AGSE as it sits on the pad including all purchased components The fair market value of all donated items or materials shall be included in the cost analysis The following items may be omitted from the total cost of the vehicle 1 16 Vehicle Prohibitions 1 16 1 The launch vehicle shall not utilize forward canards Structures 1 16 2 The launch vehicle shall not utilize forward firing motors Propulsion 1 163 The launch vehicle shall not utilize motors that expel titanium Propulsion sponges Sparky Skidmark Metal Storm 1 16 4 The launch vehicle shall not utilize hybrid motors Propulsion 1 16 5 The launch vehicle shall not utilize a cluster of motors Propulsion The launch vehicle shall stage the deployment of its recovery devices where a drogue parachute is deployed at apogee and a main parachute is deployed at a much lower altitude Tumble 2 1 recovery or streamer recovery from apogee to main parachute Recovery deployment is also permissible provided the kinetic energy during drogue stage descent is reasonable as deemed by the Range Safety Officer Teams must perform a successful ground ejection test for both the 22 drogue and main parachutes This must be done p
17. Cea ni 36 342 Parachutes War acer Stace NE 38 Sp Electrical ce nasa 39 SAA Recovery Schematic e Lee 41 34 97 GPS Transmitter Shs n SESSA Oss 42 34 6 Recovery TESINE RSA SSS 43 34 7 Safety and Parure Analysts ceeds 44 3 2 AS 44 3 5 1 Final Rocket Motor Selection eiii eene eot sete heat da eie 44 3 9 2 Fed ein S N IU TET 47 3 5 3 Flight Reliability and Confidence sdeaototeoken tes aa ness itd duis better edu papa erento 48 3 6 Mission Performance PredictiONnS sss 48 3 01 Performanoe veis ee ndi 48 3 0 2 S bscale osea elec n ade putes tu rendu C Eu ME 48 3 0 3 Silage ois gms Lee 49 3 0 4 Rocket MK VER 52 3 6 5 Kinetic Emer gy E 53 ERONEN D Int ALY SIS Go estre cn veta cem gta vl e a Mes e ties peu aenea 54 3 7 ERS 57 3 7 1 Wind Tunnel o dai REI UMP mase 57 3 71 1 NOSC CONG E e E A E 57 3 7 1 2 BodySectiOn ido en dede eth ri P eg ete 57 32 1 3 cim Section zs tede e tute 57
18. 74 4 3 1 Assembly A checklist has been established in order to complete the entire AGSE assembly procedure 1 Slide track coupler into short segment of foot A Secure with bolts 2 Slide other side of track coupler into short segment of foot B Secure with bolts 3 Slide tower segment C onto the stock couplers protruding from both foot A and foot B Secure with bolts 4 Slide tower segment D onto the stock couplers protruding from the top of ladder segment C Secure with bolts 5 Loop chains from gears on top rung to outer gears on lowest rung Secure with connecting link to form full loop 6 Adjust chain tighteners as need to remove slack 7 Place motor on back portion of tower feet and secure with 4 quick release pins 8 Loop chain from middle gear on lowest rung to the motor gear Secure with connecting link to form full loop 9 Slide the rocket onto the launch rail 10 Connect sled to chains Tighten connector nuts to secure the sled Ensure that each wheel is on its respective track 11 Place Scorbot on ground 12 inches from payload bay Secure with 4 stakes 12 Place Scorbot driver as far from the Scorbot arm as the cable will allow 13 Run igniter wire through insertion tube 14 Connect all systems to the power source 4 3 2 Instrument Precision The laptop computer utilized by the AGSE will control and monitor all subsystems through the use of MATLAB The Scorbot control unit will relay feedback to the progr
19. 88 Table 18 Hazard Analysis for Project and Safety Hazard ORM Cause Effect Mitigation Verification Value Project Over budget Not paying Could run out Maintain Specific attention to of money at the detailed budget individual where money is end of the records and designated to being spent project that hold maintain budget spending money could have been individuals records on items that are used to fix a accountable for Thorough not necessary or last minute money that is research on could be problem or spent Do alternative costs purchased for emergency thorough completed cheaper research on the most cost effective ways to purchase materials Fall behind Lack of focus Quality of Leadership Team leader on the and big picture project could maintain held responsible schedule oversight decrease constant for schedule procrastinating overall oversight on set on projects not threatening timeline hold paying attention performance at team members or adhering to set final accountable for deadlines competition project Could not finish deadlines Try on time and to finish therefore not be able to compete projects ahead of schedule and don t procrastinate 89 1 available Material damaged during testing Machines breakdown Team fails to communicate Sometimes out of Could force Do not All materials team s c
20. Fixed to the bottom of the rocket sled below the rocket nozzle is a flat plate on which the igniter insertion system will be mounted as shown in Figure 49 The igniter insertion system consists of a Firgelli Automations 24 inch stroke 150 pounds force linear actuator a flat circular steel plate and an 18 inch aluminum rod of inch outer diameter mounted onto the end of the extendable shaft The rod is threaded and screws in to the extendable shaft so it can be removed as necessary to avoid damage to the structure of the system Figure 49 Igniter Insertion Drawing The ignition wire runs from a hole in the base of the rod to the top of the rod below the nozzle The igniter is exposed at the end of the tube facing towards the rocket The un mounted igniter insertion system can be seen below in Figure 50 72 Figure 50 Un mounted Igniter Insertion System The linear actuator is powered by a mounted 12 volt DC motor that draws a maximum of 5 amps powered by the AGSE power source The automated portion of the actuator will be controlled by a Roboteq SDC1130 Single Channel Forward Reverse Brushed DC Motor Controller The Roboteq will be programmed using Matlab on the laptop to insert the rod with the igniter on the end to the top of the rocket s engine The linear actuator will be mounted to the base of the tower sled using a system of bolts and spacers The threaded rod will screw into the end of the actuator s arm so it can be easily r
21. The planned flight profile and sequence of events 7 All nominal impact areas including those for any spent motors and other discarded hardware within three standard deviations of the mean impact point 8 Launch commits criteria 9 Countdown procedures and 10 Mishap procedures E 4 Law amp Regulations NAR User Certification NFPA Code 1127 and the safety codes of both the NAR and TRA require that high power motors be sold to or possessed by only a certified user This certification may be granted by a nationally recognized organization to people who demonstrate competence and knowledge in handling storing and using such motors Currently only the NAR and TRA offer this certification service Each organization has slightly different standards and procedures for granting this certification but each recognizes certifications granted by the other Certified users must be age 18 or older Explosives Permits Hobby rocket motors including high power no longer require a Federal explosives permit to sell purchase store or fly Certain types of igniters and cans or other bulk amounts of black powder do require such permits Under the Organized Crime Control Act of 1970 Public Law 91 452 A Federal Low Explosives User Permit LEUP from the Bureau of Alcohol Tobacco and Firearms BATF is required to purchase these items outside one s home state or to transport them across state lines These items once bought
22. There is also potential for additional funding from the USNA MSTEM program but this funding is currently non finalized Table 27 below details Navy Rockets funding plan Table 27 Navy Rockets Funding Plan Navy Rockets SL Funding 2014 2015 DARPA 40 000 00 USNA MSTEM 5 000 00 45 000 00 Navy Rockets expected funding results in over a 17 000 margin over the budgeted project costs This margin will allow Navy Rockets to successfully compete in the 2014 2015 Student Launch even if the projections of project costs are exceeded 6 3 Timeline In order for Navy Rockets to stay on track a schedule has been created This Gantt chart found in Appendix G shows the progress and plans for the team until launch The Navy Rockets milestone schedule for the project is shown in Table 28 Table 28 Milestone Schedule Date Milestone Event Nov 05 Design Concept Sub Scale Model Completed Nov 08 Successful Flight Body Design Validated Nov 19 Y Sub Scale Model Completed Nov 14 PDR Presentation Nov 30 SCORBOT Initial Programming Complete Dec 01 GPS Recovery Components Avionics I242 Motor Received Dec 06 Recovery Systems Test Flight Scrubbed Weather Dec 10 Rocket Body Mold Design Finished Jan 08 Wind Tunnel Test Model Fabrication Begins Jan 12 SCORBOT Payload Test Bed Complete Jan 14 CDR Mock Presentation with Faculty Jan 15 CDR Completed and Submitted Jan 25 Subscale Launches Successful Mar 05 Launch Vehicle for Te
23. carcinogen or potential carcinogen by OSHA or 4 when nie are e wegrit or ii GOCE show that DGEBPA is carcinogenic Indeed the most recent review of the avallabie data by the Intemational Agency for Research on Cancer IARC has concluded that DGEBPA Is not classified as a carcinogen Epichiorohydrin an impurtty this product lt 5 pom has been reported to produce cancer In laboratory animais and to produce mutagenic changes in bacteria and culured hirman celi has been estabished by the Intemational Agency for Research on Cancer ARC a a ed an cpated human carcnagen Die Nationa Toxicology N uninely that noma use ot peen fumar carage by ne Nona Toxcaogy rm it Is unlikely that normal use of this product would resuft in measurable exposure concentrations to n the non cured liquid form this product may cause long term harm If released to the environment Prevent entry Into sewers and natural waters Movement and Partitioning Bloconcentration potential is moderate ECF between 100 and 3000 or Log Kow between 3 and 5 Degradation and Transformation Theoretical oxygen demand is calculated to be 2 35 pip 20 day biochemical oxygen demand Is lt 2 5 Material is moderately toxic to aquatic organisms on an acute basis between 1 and 10 mg L In most sensitive 13 DISPOSAL CONSIDERATIONS WASTE DISPOSAL s Evaluation of this product using RCRA cri
24. modeled out of PVC because of reduced cost and simplicity of construction PVC was determined to be sufficient because of few constraints regarding weight and material strength The body section contains 7 pressure ports in order to calculate the pressure along the body of the rocket Directly across the pressure ports access holes were drilled in order to put the stainless steel tip that connected to the tygon tubing into the pressure port of the PVC The access ports were covered by aluminum tape during the testing 3 7 1 3 Fin Section The fin section was also 3 D printed The fin section was attached to the body section by means of an aluminum attachment located on the inside of the rocket The main purpose of the aluminum attachment was to connect the rocket to the sting balance The fin section was chosen to be 3 D printed in order to accurately attach the fins at 120 intervals The additive printing of the whole fin section allowed for the sting attachment to be lengthened and hold the PVC in place 57 3 7 1 4 Testing The scale model was tested on the sting balance in the Eiffel Wind Tunnel at varying Reynolds numbers and angles of attack To determine the pressure along the nose cone and rocket body at different radial locations the nose cone was to be manually rotated on the sting balance Because the speed of the Eiffel Wind Tunnel limits the Reynolds number the Reynolds numbers are characteristic of the boost phase of the actual
25. state and local laws and regufations Avoid inhaling exhaust products 163 MSDS ProX Rocket Motor Reload Kits Page 26 Veron 202 Farvisice Date Feb 2010 nw n b i Du inside tne plastic tube are cylinders of composite propellant rocket fuel The forward closure also contains a small quantity of black powder AI parts are odouriess solids Potential Health Effects Eye amey roule of exposure May cause eye Not a likely route of exposure Low hazard tor usual Industrialhooby handling Not a likely route of exposure Not a likely route of exposure May cause respiratory tract irritation Do not inhale exhaust products 40 FIRST AID MEASURES i Immediately flush eyes with plenty of water for at least 15 minutes occasionally the upper and lower eyelids Get medical aid Flush skin with plenty of soap and water for at least 15 minutes while removing contaminated clothing and shoes Get medical ald If irritation develops or persists Ingestion Do NOT induce vomiting If conscious and alert rinse mouth and drink 2 4 cupfuls of milk or water Remove from exposure to fresh air Immediately If not breathing give artificial respiration If breathing is dificult give oxygen Get medical aki Burns Bums can be treated as per normal first ald procedures Extinguishing Media In case of fire use water dry chemical chemical foam or aicohoi resistant foam to contain surrounding fire Exposure Hazards Duri
26. the progress on per week before 90 their sections splitting up to complete tasks Table 19 Hazard Analysis for Vehicle Safety Hazard ORM Cause Effect Mitigation Verification Value Vehicle Parachute Poor packing Rocket falls Ensure parachute Parachute fails to damage on uncontrollably is packed packed very deploy launch potentially properly test carefully under environmental causing project repeatedly before experienced circumstances at ending damage competition to supervision deployment determine best altitude packing configuration Parachute Poor packing or Rocket falls Ensure parachute Sufficient fire catches not enough uncontrollably is packed retardant on fire protection from potentially properly and material the motor causing project place fire packed ending damage retardant material between between them parachute and and the motor motor Parachute Poor packing of Rocket falls Ensure parachute Parachute lines lines the parachutes uncontrollably is properly wrapped gently tangled potentially packed and cautiously causing project ending damage Sections Sections initially Rocket does not Ensure sections Couplings fail to connected perform to are connected inspected separate improperly project standards properly Test before launch damage on liftoff potentially connections for proper environmental causing project repeatedly before frict
27. using suitable mechanical fasteners These rods are secured to the aft bulkhead of the payload section An eyehook is also mounted on this bulkhead facing aft It is used to attach the payload section and nosecone to the recovery system Additionally a metal slide will be mounted to both the rocket body and the nosecone This component supports the weight of the nosecone while it is extended away from the rocket body relieving the DC motor and it s gearing from any shear forces During the launch process the payload section of the rocket will initially be open with the nosecone separated from the rocket body Once the AGSE places the payload into the payload containment area within the payload section the wireless serial modem will receive a command from the control element of the AGSE to rotate the payload securement tab 90 degrees via the servomotor Following securement of the payload sample the brushed DC motor will activate and slide the nosecone back onto the rocket body through the associated rack and pinion system The nosecone will be sealed onto the rocket body with O rings and the brushed DC motor and its rack and pinion system will lock into place The gearing of the DC motor will prevent any back driving of the motor thereby providing a static force that will secure the nosecone to the rocket body The nosecone is a protective housing for the sample during the launch procedures and flight After the nosecone separates and lands t
28. 1 15 REGULATORY INFORMATION TSCA 8 b Inventory Status components are listed or are exempt from listing on the Toxic Substances Control Act TSCA 12 b Export Notification None above reporting de minimus IDH number 1137985 Product name Loctite Epoxy Heavy Duty Hardener Page 4 of 5 161 CERCLA SARA Section 302 EHS None above reporting de minimus CERCLA S ARA Section 311 312 immediate Health CERCLA S ARA 313 None above reporting de minimus California Proposition 65 No Calfornia Proposition 65 Ested chemicals are known to be present Canada Regulatory information CEPA DSL NDSL Status All components are listed on or are exempt from listing on the Canadian Domestic Substances List WHMIS hazard class 025 E 16 OTHER INFORMATION This material safety data sheet contains changes from the previous version sections New Material Safety Data Sheet Prepared by Gary Pierson Manager Regulatory Affairs DISCLAIMER The data contained herein are furnished for information only and are believed to be rellable However Henke Corporation and Its affllates Henkel does not assume responsibility for any results obtained by persons over whose methods Henkel has no control It is the user s responsibility to determine the suitability of products or any production methods mentioned herein for a particular purpose and to adopt such precautions as may be advisable for the protection of property and a
29. 2 right 3 4 5 GPS Transmitters The TT15 Dog tracking device from Garmin is used to track both sections of the rocket during and after launch Each section will contain a tracking device that transmits back to a hand held receiver The GPS is capable of being detected for up to seven miles while using the MURS frequency The characteristics of the GPS can be found in Table 7 42 Table 7 GPS Characteristics VHF Radio Specifications frequency Up to 7 miles 11 2 km line of sight power Astro 320 User s Manual 3 4 6 Recovery Testing Ground testing of a subscale recovery system was completed in order to ground test the deployment of parachutes The parachutes were packed and flame retardant wadding into a Y scale rocket fuselage section The fuselage section was inserted into a small section of PVC pipe which has been glued to a section of plywood Through a hole in the bottom of the plywood a black powder loaded ejection canister was inserted The ejection charge was detonated using a standard model rocketry launch trigger switch The system was modeled after the recovery deployment system of previous rockets and shown in Figure 26 Figure 26 Recovery Test Stand 43 3 4 7 Safety and Failure Analysis The recovery system has been designed such that in the event of an avionics failure there are back up systems and wiring in place to continue operability and complete the mission successfully The dual arming s
30. 3 Amateur Rockets Laws 101 21 Applicability a This subpart applies to operating unmanned rockets However a person operating an unmanned rocket within a restricted area must comply with 101 25 b 7 and with any additional limitations imposed by the using or controlling agency b A person operating an unmanned rocket other than an amateur rocket as defined in 1 1 of this chapter must comply with 14 CFR Chapter III 101 22 Definitions The following definitions apply to this subpart A Class 1 Model Rocket means an amateur rocket that 1 uses no more than 125 grams 4 4 ounces of propellant 2 Uses a slow burning propellant 3 Is made of paper wood or breakable plastic 4 Contains no substantial metal parts and 5 Weighs no more than 1 500 grams 53 ounces including the propellant b Class 2 High Power Rocket means an amateur rocket other than a model rocket that is propelled by a motor or motors having a combined total impulse of 40 960 Newton seconds 9 208 pound seconds or less c Class 3 Advanced High Power Rocket means an amateur rocket other than a model rocket or high power rocket 101 23 General operating limitations a You must operate an amateur rocket in such a manner that it 1 Is launched on a suborbital trajectory 2 When launched must not cross into the territory of a foreign country unless an agreement is in place between the United States and the country of conce
31. 4 year students on the team will not be able to be with the team next year there will be a high turnover rate If there are not enough incoming third and second year students this could pose a problem Adding to that the Naval Academy is a smaller school with a relatively small selection of students pursuing aerospace engineering The best solution to this challenge will be to make team information flyers and events more effective in providing interest A way to do this will to branch outside of the aerospace engineering department when soliciting for members The major members of the team now are all aerospace majors In the future this will most likely not be the case with increased solicitation to and interest from other engineering majors 6 4 5 Educational Engagement Progress Proposal to CDR The educational engagement events have progressed as expected following Navy Rocket s admission into the Student Launch competition Between the submission of the proposal and the admission into the competition Navy Rockets members conducted educational outreach with a community elementary school through the American Institute of Aeronautics and Astronautics AIAA Although the educational outreach did not count towards requirements that NASA has made the outreach was both beneficial for the participants and the Navy Rockets team members Navy Rockets has taken a major part in outreach with the Girls STEM Day at the Naval Academy With an effect
32. 5 Structures Design 1 6 Design 17 Avionics Payload and Design Recovery 1 8 Propulsion Design 1 9 Propulsion Design 1 9 1 Propulsion Design 1 9 2 Propulsion Design 1 10 Propulsion Analysis 1 11 Propulsion Design 1 12 Structures E21 Structures Analysis 1 12 2 Structures Analysis 1 12 3 Structures Analysis 1 12 4 Structures Analysis 1 13 All Testing 1 14 All Testing Analysis and 1 1 14 1 Recovery e 1 14 2 All Testing 1 14 2 1 Recovery Testing 1 12 2 2 Payload Testing 125 1 14 2 3 Payload Testing 1 14 3 Payload Testing 1 14 4 All Testing 1 14 5 All Testing 1 15 All Design 1 16 1 16 1 Structures Design 1 16 2 Propulsion Design 1 16 3 Propulsion Design 1 16 4 Propulsion Design 1 16 5 Propulsion Design 2 1 Design 2 2 Testing 23 Analysis 2 4 Recovery Design 2 5 Design 2 6 Recovery Design Del Recovery Design 2 8 Recovery Design 2 9 Recovery Design 2 10 Avionics Design 2 10 1 Avionics Design 2 10 2 Avionics Design 2 11 Recovery Testing 2 11 1 Recovery Design 2 11 2 Testing 211 3 Testing 2 11 4 Recovery Testing 3 21 12 Payload amp Recovery Testing 3 2 4 1 Payload Design 3 2 4 2 Payload Design 3 2 4 3 Payload Design 3 2 4 4 Payload Testing 3245 Avionics Payload amp Design Recove
33. Frequencies MURS Frequency to ensure they operste property Esch one will be set to spark the charge in case the other fait Beck Powder Drogue Chute grams Pad Stay Time Launch Bleck Powder Mass Main Configuration Chute grams 110 Milestone Review Flysheet institution Milestone Autonomous Ground Support Equipment AGSE E ee The Scorbot ER V is capable of using six different motions to complete the assigned task These motions are base rotation shoulder rotation elbow rotation wrist pitch wrist rol aed gripper open close The base has is a rotation angle of 310 degrees he shoulder has a rotation angle of 130 35 degrees and elbow has a rotation angle of 130 degrees The wrist can rotate up within 130 degrees and the wrist cae rol within 570 degrees The gripper will sense when has grasped an object by means of a gripper sensor integrated into the system The maximum payload thet the Scorbot is rated for is 2 2 Ibs inckading the mass of the gripper The Scorbot is capable of operating within a temperature range of 36 to 104 degrees Fahrenheit The Scordot component of the AGSE will piace the payload sample into peyloBd hoiding bed within the paylosc section of the rocket body This payload Ded will be a halt cylinder made of steel Once the payloac is placed within the Ded servomotor mounted adjacent to the bed will rotate a securement tad 59 its final position is perpendiculer to the longitudinal axis of t
34. High Power Rocketry Code for High Power Rocketry Tripoli Rocketry Association This High Power Rocketry Safety Code is the product of many years of effort on behalf of the hobby by those who care about it and whose prime interest is safety It is not a perfect standard but adequate This minimum requirement if followed will preserve the hobby in a safe environment for all who participate and for spectators Tripoli s Prefectures and other launch sponsors should be aware that wisdom should dictate what is safe and what is not at each launch site With this standard as the minimum it will be your responsibility to regulate your own launches within reason You should be cautious not to over restrict the activity Our members who sometimes travel great distances to attend launches will expect this Safety Code to be the standard at Tripoli sanctioned launches This version of the safety code will appear much terser than prior versions This version is intended to augment NFPA 1127 Code for High Power Rocketry with codes that are specific to Tripoli The foundation of the Tripoli High Power Safety Code is NFPA 1127 as that has been adopted by many Authorities Having Jurisdiction and define the minimum set of codes required Tripoli codes cannot relax NFPA codes we can only add codes that are intended to increase safety at our sanctioned launches General Requirements 1 1 Scope 1 1 1 This code shall apply to safe operation of High Power rocket lau
35. Launcher Location My launcher will be at least one half the minimum launch site dimension or 1500 feet whichever is greater from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour not including traffic flow related to the launch It will also be no closer than the appropriate Minimum Personne Distance from the accompanying table from any boundary of the launch site 12 Recovery System I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again and I will use only flame resistant or fireproof recovery system wadding in my rocket 13 Recovery Safety I will not attempt to recover my rocket from power lines tall trees or other dangerous places fly it under conditions where it may recover in spectator areas or outside the launch site or attempt to catch it as it approaches the ground MINIMUM DISTANCE TABLE Installed Total Equivalent Minimum Minimum Minimum Personnel Impulse N sec Motor Type Clear Personnel Distance Distance ft Distance ft omplex Rocket ft 0 320 00 Horsmaller 5 X 200 320 01 640 00 1 so 10 20 640 01 1280 00 3 5o 1280 01 2560 00 75 2560 01 5120 00 300 5120 01 10 240 00 125 um 0 10 240 01 20 480 00 20 480 01 40 960 00 Note A complex 128 E 2 TRA Code for
36. Protection Not ordinarily required If sized and sufficient vapor or fumes are being generated during heating or curing of this product use a NIOSH approved organic vapor respirator If sufficient dust or fibers are generated during use or when machining grinding or sawing the cured product use a NIOSH approved dust respirator Ventilation Use local exhaust sufficient to control vapor fumes fibers or dust generated If exhaust ventilation is not available or is inadequate use a NIOSH approved respirator as appropriate General Hygiene Recommendations Before eating drinking smoking or using toilet facilities wash face and hands thoroughly with soap and water Remove any contaminated clothing and launder before reuse Use vacuum equipment to remove fibers and dust from clothing and work areas Compressed air is not recommended 150 MSDS Number 439 3227 00SU C000 12 Date October 1 2002 Page 4 of 6 Section 9 PHYSICAL AND CHEMICAL PROPERTIES Appearance and Odor Black fibers woven into fabrics of varying weight width and thickness depending on the style with and without sizing with no distinctive odor Melting Point 6512 F 3600 C Specific Gravity 1 1 5 1 9 pH of Undiluted Product Not determined Volatile Percent by Weight 0 Parcent Not determined Selsbility in Water Negligible Section 10 STABILITY AND REACTIVITY Stab
37. Rockets participation in the 2014 2015 Student Launch can be seen below in Table 25 The full scale component of this budget is further detailed in Table 26 Table 25 Navy Rockets Comprehensive Budget Expected Costs 2014 2015 Full Scale 7 786 66 500 00 Testing and Development 600 00 13 152 00 500 00 22 538 66 100 Table 26 Full Scale Itemized Budget Full Scale Itemized Budget Subsystem Rocket Structure Avionics and Recovery Payload Bay AGSE Propulsion Item 11oz 2x2 Twill Weave Carbon Fiber Cloth West System 205b Fast Hardener West System 105b Epoxy Resin Aero Mat Soric LRC Honeycomb Foam 10oz E Glass G10 4 Glass Epoxy Sheet Nylon Shear Pins Garmin Astro Bundle Astro 320 and T5 Device Garmin T5 Device Large Capacity Ejection Canisters Snap Action Switch StratoLoggerCF Altimeter Fruity Chutes Iris Ultra 72 Parachute Fruity Chutes Iris Ultra 60 Parachute Fruity Chutes 24 Classic Elliptical Parachute 18 Chute Protector 9 16 Tubular White Nylon Black Diamond Positron Screwgate Carabiner Eyebolt Hitec HS 422 Servo Motor Arduino Micro Microcontroller 12V Battery 1 4 Threaded Steel Rod MaxStream xBee Pro 900HP Wireless Serial Modem Accuride 3832C Full Extension Slide 8 11 935 Aluminum Beam 32P Beam Gear Rack Beam Bracket S Pair Beam Attachment Block B 1 50 Aluminum Channel 16 Tooth 32 Pitch 4mm Bore Pinion Gear 6 32 Nylock Nuts 6 Washers Actobotics 32 RP
38. This was corrected by cutting off these couplers and epoxying in couplers made from PVC The PVC couplers were lathed down to fit the inner diameter of the tubes and allow for separation Another change was to the fin and bulkhead material This was originally going to be made from carbon fiber however G10 Epoxy Glass was used The G10 Epoxy Glass is very strong and durable and is easily able to withstand the forces applied during launch This material is pre fabricated so also allowed for a quicker build process 2 1 1 Payload A change to the launch vehicle payload section has been the selection of a new DC motor that drives the rack and pinion system Previously at CDR a Pololu Micro Metal Gearmotor HP had been selected Now Navy Rockets will be using an Actobotics 32 RPM Precision Planetary Gearmotor This new selection was made to ensure better mechanical fit and operation of the motor within the payload section Additionally this motor is more powerful than the previously selected motor which will ensure that the motor has enough power to properly address any contingencies A second change to the payload section is the use of one quarter inch threaded steel rods instead of three eighths inch aluminum rods for supports in the payload section This change was made to facilitate easier installation and maintenance of the payload section components while still remaining strong and light as support rods 12 2 1 2 Recovery 2 1 2 1 Ej
39. air breathing components and the presence of gravity will allow the AGSE to function similarly to how it would on Earth This is to be considered a small scale test compared to the size of the rocket needed to escape Mars atmosphere and rendezvous with a transport spacecraft The payload would theoretically be delivered by a rover programmed to return to the launch site after acquiring samples 4 1 2 AGSE Mission The Autonomous Ground Support Equipment will insert the payload with the use of a Scorbot ER V and remotely secure the payload within the payload compartment Then the AGSE system will erect the rocket from the horizontal position to the final launch position which is 5 degrees from the vertical plane Upon securing the rocket in the launch position with latches the AGSE system will then begin to insert the rocket motor igniter Once the igniter has been inserted the rocket will be ready to launch 4 1 3 Mission Success Criteria In order for the project to be successful the rocket must accomplish certain criteria which will be graded during the competition These graded events can be found in Table 14 and will determine how success of the project and performance of the team 64 Table 14 Success Criteria Altitude Reached 3000 feet Timing of System 10 minutes Launch Angle 5 degrees Safety Controls All working Capture of First attempt Sample Sample First attempt Containment Erection of First attempt Rocket Ig
40. and secured on the outside of the body with epoxy 47 3 5 3 Flight Reliability and Confidence Theoretical Open Rocket altitudes were compared to empirically measured altitudes during three previous high powered rocket launches Empirical data varied by less than 3 indicating that the theoretical values represent a reliable estimate of true performance This small error gives a good expectation to the performance for the final rocket during testing and competition Also when the rocket is tested before the competition it will be checked against the predicted values in order to ensure that it meets the requirements and expectations 3 6 Mission Performance Predictions 3 6 1 Performance Criteria In order for this year s REPTAR project to be a success Navy Rockets will deliver an autonomous ground support element capable of loading the specified payload into a rocket launch the rocket to 3000 feet AGL and return both the main rocket body and the jettisoned payload section safely to the ground while meeting all specified mission criteria listed above 3 6 2 Subscale Flight Results Three members of Navy Rockets are high power rocketry certified with one being a level two One of the subscale testing rockets was used in a level two certification flight This flight was predicted by Open Rocket to reach 2100 feet and on launch day the rocket reached 2041 feet in altitude This gives the team an idea on how precise the Open Rocket program
41. and then the material will be laid and secure with epoxy Once the materials were correctly laid it then underwent vacuum bagging to help the material set properly Figure 8 Tubing Mold Shape Half Circle 23 Figure 9 Tubing Connections Full Circle For the carbon fiber the connection points of the tubing have an additional layer of carbon fiber to secure them For the fiberglass sections the overlapped areas were epoxied together A window was cut out of the main electronics section that allows a panel to be removed and allow access to the components A fiberglass flange shown in Figure 10 was created using the tube mold then epoxied internally to allow the window to rest on the edges Figure 10 Avionics Flange Window Open and Closed 24 The fins and bulkheads which are be 0 125 inches thick created by using G10 Epoxy Glass This material is fabricated to have a high mechanical strength The nose cone was created by an extruded foam mold of two halves of the nose cone shown in Figures 11 and 12 Once both halves were created they were epoxied together and secure with additional fiberglass strips Figure 11 Nose Cone Mold Halves Figure 12 Nose Cone Mold Final Construction 25 3 2 1 3 Motor Mount The motor mount for the rocket was created from a smaller carbon fiber tube that has an inner diameter equivalent to the motor retention tube The mount has two centering rings one on both ends of the tube to ens
42. and weighing approximately 4 oz and capped with domed PVC end caps Each launch vehicle must be able to seal the payload containment area autonomously prior to launch Payload 3 2 4 2 Teams may construct their own payload according to the above specifications however each team will be required to use a regulation payload provided to them on launch day Payload 3 2 4 3 The payload will not contain any hooks or other means to grab it A diagram of the payload and a sample payload will be provided to each team at time of acceptance into the competition Payload 3 2 4 4 The payload may be placed anywhere in the launch area for insertion as long as it is outside the mold line of the launch vehicle when placed in the horizontal position on the AGSE Payload 3 2 4 5 The payload container must utilize a parachute for recovery and contain a GPS or radio locator 124 Avionics Payload amp Recovery Req t Designated Subsystem Verification 1 1 Structures amp Propulsion Ans E Testing 1 2 Avionics Design 12 1 Avionics Design 122 Avionics amp Recovery Design 1 2 2 1 Avionics 22 2 Avionics Design 2 2 3 Avionics 1 2 3 Avionics Testing 1 2 3 1 Avionics Testing 1 2 3 2 Avionics Testing 23 3 Avionics Testing 1 2 3 4 All Testing 155 Structures amp Recovery Testing 1 4 Structures Design 1
43. attention immediately flush eyes with plenty of water for at least 15 minutes Get medical attention DO NOT induce vomiting unless directed to do so by medical personnel Keep Individual calm Get medical attention 5 FIRE FIGHTING MEASURES gt 93 C gt 199 4 F Tagllabue closed cup Not available Not avaliabie Not avaliabie Water spray fog foam dry chemical or carbon dioxide Wear self contained breathing apparatus and ful protective clothing such as tum out gear In case of fre keep containers with water spray Oxides of carbon Oxides of nitrogen Ammonia Amines Nitric acid Nitrosamines Imitating organic fragments 6 ACCIDENTAL RELEASE MEASURES Use personal protection recommended in Section 8 Isolate the hazard area and deny entry to unnecessary and unprotected Environmental precautions Clean up methods personnel Do not empty into drains surface water ground water Remove all sources of Ignition Store in a closed container until ready for contact disposal emergency personnel Scrape up as much material as possible Clean residue with soap and water 7 HANDLING AND STORAGE Keep away trom heat spark and flame Keep container closed Avoid breathing vapors or mists of this product Avold contact with eyes skin and clothing Wash thoroughly after handling For safe storage store at or below 37 8 100 F Store in original container until ready to use Keep In a cool we
44. be used to simulate the payload mass Recovery 112 2 2 The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass Payload 1 14 2 3 If the payload changes the external surfaces of the rocket such as with camera housings or external probes or manages the total energy of the vehicle those systems shall be active during the full scale demonstration flight Payload 1 14 3 The full scale motor does not have to be flown during the full scale test flight However it is recommended that the full scale motor be used to demonstrate full flight readiness and altitude verification If the full scale motor is not flown during the full scale flight it is desired that the motor simulate as closely as possible the predicted maximum velocity and maximum acceleration of the competition flight Payload 1 14 4 The vehicle shall be flown in its fully ballasted configuration during the full scale test flight Fully ballasted refers to the same amount of ballast that will be flown during the competition flight All 1 14 5 After successfully completing the full scale demonstration flight the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range Safety Officer RSO All Each team will have a maximum budget they may spend on the rocket and the Autonomous Ground Support Equipment AGSE All
45. considered ready for launch During the actual launch process the igniter insertion device will receive the command from the AGSE control element and insert the igniter into the rocket motor Ensure igniter insertion device is secured to sled Ensure threaded rod is secured to actuator Visually inspect threaded rod to ensure that it is not bent Ensure that any exposed igniter wire does not come into contact with any metal Fee eS 5 1 7 Launch Procedure Payload insertion Payload securement Nose cone closure Tower erects Igniter inserted Rocket launches DS OS Epsum 5 1 8 Troubleshooting Any problems that occur during the set up and launch of the rocket will be discussed with the team our faculty representative and our rocketry mentor With each team member focusing on a specific area it allows Navy Rockets to have an idea on all of the topics that require work By utilizing the faculty representative and also the rocketry mentor it enables more knowledge to be used in order to fix the problem 1 Locate the cause of failure Ensure that the igniter is removed and electronics disarmed before working on the problem 3 Section expert discusses problem with faculty and mentor to determine the plan of attack After Problem Corrected 1 Check AGSE connections and system launch progress 2 Check igniter insertion and continuity before launching 85 5 1 9 Post flight Inspection Locate sections of the rocket Record
46. flight of the full scale rocket which is where disturbances are most detrimental to stability of the rocket The Reynolds number was limited by the maximum free stream Reynolds number of the wind tunnel and the overall size namely the height and width of the test section The goal of the wind tunnel testing was to model the pressure distribution along the rocket However because the pressure in the nose cone was unable to be transferred via the tunnels the pressure along the rocket was not measured Without the pressure distribution data the only data taken from the rocket was drag data at varying Reynolds numbers and angles of attack Because the full scale rocket was made out of carbon fiber and the scale rocket was made of a plastic nose cone PVC body section and HDF fins the skin friction drag coefficient will be different For this reason the difference in skin friction coefficient of the scale model and the full scale rocket was not taken into account Therefore the significance of the drag calculated by the sting balance was attributed to profile drag due to the geometry of the rocket and placement of the fins and not the difference in skin friction drag due to the material of the rocket 3 7 1 5 Results The original goal of measuring the pressure distribution was to prove the center of pressure found by OpenRocket However without this data only the coefficient of drag Cp was proven by means of the wind tunnel testing The d
47. insertion calibrated 25 Mar Tower motor calibrated 27 Mar Wireless integration of AGSE and laptop 27 Mar Full wireless system test Andy Igniter Insertion 25 Mar Calibrate actuator 26 Mar Integrate actuator to AGSE 26 Mar Connect to main power source 27 Mar Full system test 103 The team also plans on completing another full scale launch and competition test 28 March 2015 This launch will integrate the AGSE system and launch the rocket with the payload section The goal is to simulate the competition and determine if anything needs changed before reporting to the Student Launch The team will focus on the time constraints and simulate the competition launching environment 6 4 Educational Engagement Navy Rockets intends to involve itself in the community through educational outreach events The main targets of outreach events will be primary and secondary school students interested in the areas of Science Technology and Mathematics STEM In general Navy Rockets participation in the outreach events will be supplementary to the overall goal of the event All STEM events involve the rotation of interested young scholars through a myriad of engineering and technological disciplines Navy Rockets plans to provide an opportunity for under represented populations to experience design and engineering processes This is to be done outside of a classroom setting through selected STEM events where part
48. is compared to actual flight data This knowledge allows the team to account for a possibly lesser altitude compared to the Open Rocket simulation Navy Rockets complete multiple subscale launches on 18 January 2015 at Higgs Sod Farm with MDRA These launches were to test different aspects of the full scale launch The first test rocket was a one half scale rocket to the full scale rocket shown in Figure 31 The rocket was a modified LOC Precision Hi Tech and flew on a Cesaroni Tech 1242 motor The 1242 motor was used because it was as close as possible to half the thrust of the full scale motor The rocket had mass simulators in it to equal half of the full rocket and to ballast the weight positions The CG and CP of the test rocket followed closely that of the full scale rocket The rocket flew to an altitude of 1124 feet which was close to the predicted 1100 feet altitude The rocket successfully launched and recovered while fully intact 48 Figure 31 Half Scale Rocket Launch The second test rocket was flown twice on launch day It was also a modified LOC Precision Hi Tech and flew on a Cesaroni Tech 1242 motor This rocket had the GPS and dual deployment recovery system that will be incorporated into the full scale rocket The rocket flew to 4113 feet and 4125 feet in the two launches The purpose for such a high altitude was to determine if the avionics systems fully work on the boundaries of the launch The systems were successful in b
49. launch the rocket to 3000 feet AGL and return both the main rocket body and the jettisoned payload section safely to the ground while meeting all specified mission criteria listed above 3 1 3 Subsystem Success Criteria The REPTAR launch vehicle has multiple subsystems and components that work into the design as shown in Table 1 15 Table 1 Subsystem Criteria Subsystem Description Function The design construction and testing Shall integrate and retain the sample Payload of payload sample integration and into the rocket body and deliver it associated recovery system safely back to the surface Materials and The design validation construction and testing of the materials and Shall effectively support and retain all internal hardware from both atmospheric and internal effects and Structures dimensions used in the rocket body eon fins nosecone 51 launch to landing The selection and integration of all al ne ODE the vehicle s position after launch as Flight Avionics GPS systems and flight data recorders well as provide the flight data for SL as well as associated power systems imd Centennial scorns qudecs Shall safely deliver both the payload ano sume oO and main body sections Be Gite Recovery ground in a timely and controlled E Opens tor ETO manner while allowing both to A EEE maintain their structural
50. material if the rocket motor being launched uses titanium sponge in the propellant 127 8 Size My rocket will not contain any combination of motors that total more than 40 960 N sec 9208 pound seconds of total impulse My rocket will not weigh more at liftoff than one third of the certified average thrust of the high power rocket motor s intended to be ignited at launch 9 Flight Safety I will not launch my rocket at targets into clouds near airplanes or on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site and will not put any flammable or explosive payload in my rocket I will not launch my rockets if wind speeds exceed 20 miles per hour I will comply with Federal Aviation Administration airspace regulations when flying and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site 10 Launch Site I will launch my rocket outdoors in an open area where trees power lines occupied buildings and persons not involved in the launch do not present a hazard and that is at least as large on its smallest dimension as one half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet whichever is greater or 1000 feet for rockets with a combined total impulse of less than 160 N sec a total liftoff weight of less than 1500 grams and a maximum expected altitude of less than 610 meters 2000 feet 11
51. not In use 8 0 EXPOSURE CONTROLS PERSONAL PROTECTION Engineering Controls Use adequate explosion proof ventilation to keep airbome concentrations low equipment and working surfaces must be grounded Wear appropriate protective eyeglasses or chemical safety goggles as described by OSHA s eye and face protection regulations 29 CFR 1910 133 or European Standard EN166 Clothing should be appropriate for handing pyrotechnic substances Ciothing should be appropriate for handing pyrotechnic substances A respirator Is not typically necessary Follow the OSHA respirator reguiations found 29CFR1910 134 or European Standard EN 149 Always use a NIOSH or European Standard EN 149 approved respirator when necessary 30 PHYSICAL AND CHEMICAL PROPERTIES Physical State solid Appearance rubber cylinders Inside plastic parts Odour none Odour Threshold Not available Not avatabie Vapour Pressure Not available Vapour Density Not available E Not available Evaporation Rate Not avalabie Boling Pont Not available Freezing Melting Point Not available Coefficient of wateriol distribution available Auttoigniton T 280 C Flash Point Not available Explosion Limits lower LELY Not avatabie Explosion Limits upper FE Not avalabie Sensitivity to Mechanical Impact unprotected biack powder can be ignited by impact Sensitivity to Static Discharge unprotected black powder can be ignited by static disc
52. on over 270 participants Navy Rockets was able to positively influence middle school participants After submitting the Preliminary Design Review Navy Rockets started interacting with the community through educational platforms Navy Rockets proudly shared a role in shaping the minds of young students that attended MESA Day 107 6 4 6 Outreach Update Since the submission of the CDR Navy Rockets has led 40 boy scouts through the process of obtaining Space Exploration Merit Badges This outreach event involved scouts learning about NASA missions astronauts and most importantly NASA rockets The members of Navy Rockets had an excellent time sharing their passion for rocketry and learning with the young boy scouts Originally it was written in the proposal that Navy Rockets would go beyond the requirements for the project and make each member perform direct outreach with a certain amount of people However as building has intensified all hands on the project have been asked to focus on other areas Because the NASA requirement for the outreach has been reached further educational engagement will only be supplementary and only focused on if group members feel that they have extra time 108 7 Conclusion Navy Rockets will produce an autonomous system that will move a soil sample into a high powered launch vehicle The system will then seal the rocket and erect itself to five degrees from vertical After the rocket is erected an igniter w
53. shall be fully functional during the official flight at the competition launch site Avionics 2 11 The recovery system electronics shall not be adversely affected by any other on board electronic devices during flight from launch until landing Recovery 2 11 1 The recovery system altimeters shall be physically located in separate compartment within the vehicle from any other radio frequency transmitting device and or magnetic wave producing device Recovery 2 11 2 The recovery system electronics shall be shielded from all onboard transmitting devices to avoid inadvertent excitation of the recovery system electronics Recovery 2 423 The recovery system electronics shall be shielded from all onboard devices which may generate magnetic waves such as generators solenoid valves and Tesla coils to avoid inadvertent excitation of the recovery system Recovery 2 11 4 The recovery system electronics shall be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics Recovery 3 2 11 12 The rocket will launch as designed and jettison the payload at 1 000 feet AGL during descent Payload amp Recovery 3 2 4 1 Each launch vehicle must have the space to contain a cylindrical payload approximately 3 4 inch in diameter and 4 75 inches in length The payload will be made of x 3 inch PVC tubing filled with sand
54. tubing The upper piece is also composed of two vertical pieces of square tubing and two horizontal rungs However only the lower rung on the upper piece is welded into place The upper rung on the upper piece is held into place by a pair of flange bearings The upper rung will serve as the idler shaft in the system There are two gears on the idler shaft and three gears on the drive shaft The ladder structure and gear placement on the idler shaft can be seen below in Figure 41 Figure 41 Ladder Design of Tower Structure Two chains will run in vertically oriented loops from the two gears on the idler shaft or top rung to the two outer gears on the drive shaft or bottom rung The middle gear on the drive shaft will support a horizontal chain running to the tower motor located on the aft portion of the tower feet As the tower motor powers the drive shaft the vertical chains will rotate When these chains rotate they will lift the head of the tower sled upward and the tail end of the sled will roll toward the base of the tower structure This will erect the sled from horizontal to the launch position The initial and final configurations are shown below in Figures 42 and 43 67 Figure 42 Loading Configuration Figure 43 AGSE Launching configuration 4 2 2 Tower Motor and Amplifier The NPC T74 was selected based on durability size and power output The motor is advertised
55. 045 3047 15 1554 3022 2731 3037 20 2370 3009 3458 3024 Lateral Wind Drift vs Wind Speed 4000 x 3000 3 x 2000 B 1000 2 E 5 10 15 20 25 1000 Miles per Hour MPH X Worst Case Downwind Best Case Upwind Figure 37 Lateral Wind Drift vs Wind Speed for the Best and Worst Case Scenarios To better understand the wind drift problem the launch vehicle s flight profile was modeled at 11 different wind angles through each of the wind speeds from 12 to 20 mph This created a 3 D matrix of values that allowed the team to pinpoint the specific wind conditions that push the launch vehicle out of its drift boundaries This data visualized as a surface plot can be seen below in Figure 38 55 Lateral Wind Drift ft Wind Speed mph Wind Direction deg Figure 38 Surface Plot of Wind Drift with Respect to Direction and Speed This plot allows the team to do is to gauge the wind conditions at launch and determine whether or not to utilize the High Wind Parachute configuration to adjust the launch vehicle s flight profile Both the 72 in torroidal parachute on the main body section as well as the 60 in payload parachute will be reefed in this configuration to decrease the diameter of the parachute and the effective surface area available to the air This will decrease the coefficient of drag of the parachute significantly and allow the payload section to descend faster and remain
56. 1 3 SCORBOT Testing 3 4 1 Tower Components Acquisition 3 5 1 Laptop Acquisition 2 4 1 3 Payload Section Assembly 3 6 1 Battery Acquisition 13 1 Write CDR 2 3 1 4 Main Body Contruction 2 6 1 3 Construct Test Model 1 3 2 Proofread CDR 2 1 4 2 Avionics Bay Acquistion 2 2 1 2 Recovery Harness Construction 3 21 Components Acquisition 13 3 Post CDR to Website 2 2 3 Recovery Harness Testing Wind Tunnel Testing 3 42 Tower Construction 2 2 1 4 Recovery Harness Integration 2 5 2 2 K1200 Acquisition 3 2 2 IID Construction 3 3 1 Tower Motor Modification 13 4 Rehearse CDR Conference 2 3 4 2 Avionics Bay Construction 2 1 3 2 Ejection Cannister Testing 2 1 3 3 Ejection Cannister Full scale integration 2 6 2 2 Wind Tunnel Data Reduction 3 5 2 Laptop Modification 13 5 CDR Teleconference 3 6 3 Battery Integration 3 3 2 Tower Motor Testing 3 2 3 IID Internal Setup 32 4 IID Testing 2 2 1 5 Recovery Harness Full Scale Testing 2 6 2 3 Wind Tunnel Test Report 2 4 1 5 Payload Section Testing 34 3 Tower Testing 14 1 Write FRR 2 1 1 3 GPS Full scale integration 2 1 2 3 Altimeter Full scale integration 3 5 3 Laptop Testing Full Scale Launch 14 Proofread FRR 143 Post FRR to Website 7 144 Rehearse FRR Conference 145 FRR Teleconference Rehearse LRR and Safety Briefing Travel to Huntsville j LRR and Safety Briefing A Rocket Fair 3 LAUNCH DAY A Return to Annapolis Write PLAR Proofread PLAR Post PLAR to Website
57. 1 of 6 Supersedes MSDS 439 3227 00SU C000 11 Manufacturer Emergency Telephone Number Hexcel Schwebel 800 433 5072 24 Hour 2200 South Murray Avenue P O Box 2627 Information Telephone Number Anderson SC 29621 864 260 5799 Normal Business Hours ET Product Identification Carbon Fabric Sized or Unsized Chemical Family Woven Carbon Fabric with various types of Sized and Unsized Carbon Fibers Section 2 COMPOSITION INFORMATION ON INGREDIENTS Component cas by OSHA PEL ACGIH TLV Number Weight Carbon fiber 7440 44 0 985 100 15 mg m Total 10 mg m Total synthetic 5 mg m Respirable 3 mg m Respirable This product is not classified as a Hazardous Chemical as defined by the OSHA Hazard Communication Standard 29 CFR 1910 1200 Where specific exposure limits for component dusts are not established the levels provided for Total Inhalable dust and Respirable fraction reflect the classification of Particulates Not Otherwise Regulated PNOR by OSHA or Specified PNOS by ACGIH Section 3 HAZARDS IDENTIFICATION EMERGENCY OVERVIEW Appearance and Odor Black fibers woven into fabrics of varying weight width and thickness depending on the style with and without sizing with no distinctive odor Statement of Hazard Warning May cause temporary mechanical irritation of the eyes skin or upper respiratory tract If sized vapor or fumes generated from heating or curing this product may cause eye an
58. 2 30 00 119 99 129 99 125 00 355 00 39 00 138 00 97 64 259 99 40 00 40 00 A 9 9 o AJA A Ug Ugo o o o on OQ o o o AJA o o o o Oo o o A A AJA o o o o UG A G C XC o o Quantity 7 32 8 o 5 RR ee RP ee Total Cost 304 50 33 35 82 05 64 20 34 75 26 95 5 90 599 99 249 99 12 50 13 50 98 92 201 16 166 92 62 06 19 98 23 00 99 50 9 36 9 99 23 95 9 95 7 96 39 00 7 67 7 99 5 99 1 49 4 99 2 99 7 99 1 59 0 89 27 99 4 99 2 59 2 000 00 505 55 340 00 32 00 150 00 18 53 156 00 156 00 10 64 5 74 76 64 76 72 266 70 6 57 150 48 60 00 119 99 129 99 125 00 355 00 156 00 138 00 97 64 85 80 40 00 40 00 101 Launch Vehicle Total 2 678 02 AGSE Total 4 891 55 TOTAL 7 575 57 6 2 Funding Plan For the 2014 2015 Student Launch competition Navy Rockets has received funding from the Defense Advanced Research Projects Agency DARPA
59. 2 REVISION Sections I II VII X The information in the Material Safety Data Sheet has been compiled from our experience and from data presented in various technical publications It is the user s responsibility to determine the suitability of this information for the adoption of the safety precautions as may be necessary We reserve the right to revise Material Safety Data Sheets from time to time as new technical information becomes available The user has the responsibility to contact the Company to make sure that the MSDS is the latest one issued 178 MATERIAL SAFETY DATA SHEET EFFECTIVE DATE CHEMICAL FAMILY CHEMICAL FORMUA SECTION Il HAZARDOUS INGREDIENTS HAZARDOUS COMPONENTS SECTION Ill PHYSICAL DATA BOILING POINT F FREEZING POINT F VOLATILITY VOLUME 3c MELTING POINT VAPOR PRESSURE mmHg VAPOR DENSITY Air 1 SOLUBILITY IN H20 APPEARANCE ODOR SPECIFIC GRAVITY H20 1 ACIDITY SECTION IV FIRE AND EXPLOSION HAZARD DATA FLASH POINT LOWER FLAME POINT HIGHER FLAME POINT EXTINGUISH MEDIA FOR FIRE UNUSUAL FIRE HAZARD SECTION V HEALTH HAZARD DATA HEALTH HAZARD THRESHOLD LIMIT VALUE OVER EXPOSURE EFFECTS SECTION VI REACTIVITY DATA CHEMICAL STABILITY CONDITIONS TO AVOID December 19 1997 April 8 2011 Laminate Cured Epoxy Resin and Glass Grade G 10 Amine Curing Agent This product consists of cured epoxy resin on glass substrate TVL has not been established by the
60. 20 shows the four attachment points without the internal components of each section It is important to note that the eyebolts were modeled as closed designs as the open bolts used in the REPTAR system will be epoxied shut Through each of the bulkheads are 316 stainless steel eyebolts that serve as the main interface between the recovery harness and the launch vehicle body The eyebolts dedicated to the forward drogue main parachute and payload harnesses are single 5 16 inch eyebolts The aft drogue harness utilizes two 4 inch eyebolts mounted on either side of the motor tube as seen below in Figure 21 The hardware used on each of the five eyebolts is stacked as follows hex nut lock washer flat washer bulkhead flat washer lock nut This hardware was used both to ensure a secure fit through the bulkhead as well as distribute any forces incurred during recovery across the entire bulkhead to avoid a singular point of failure All hardware was then coated in a coat of epoxy as an extra safety precaution to mitigate the risk of the nuts backing out The eyebolt was also epoxied shut again as an added measure to ensure that the eye would not open during recovery 37 Figure 21 Drogue Attachments in Motor Tube The harness itself consists of 9 16 inch tubular nylon with loops tied in either end as attachment point The drogue harness measures 8 feet forward and 10 feet aft The aft drogue harness however is a 20 foot length that is doubled b
61. 250 4 1 000 4 750 Thrust Altitude 500 UOnE18 a22e JEIPAA AIO aA BIMANA 0 50 0 25 0 00 0 25 0 50 0 75 1 00 1 25 1 50 175 2 00 Time s Thrust N Altitude ft Vertical velocity fs Vertical acceleration ft s7 Figure 30 K1200 Trust and Vertical Motion vs Time 3 5 2 Motor Mount Design The motor mount was designed using carbon fiber and fiber glass laminate A carbon fiber tube of 2 12 inches in diameter was cut to a length of 25 inches to accommodate for the length of the motor 3 centering rings and 2 harnesses for the recovery system During launch operations the motor casing with the motor in it will be able to be removed and inserted to the motor mount during the preparation process on launch day On the aft most centering ring is the retention system for the motor which consist of a metal ring that was screwed into the centering ring itself with a screw on outer ring This system will prevent the motor from moving in either the forward or aft directions The fins are 0 125 inches thick and have an area of 47 5 square inches The complete component sizes can be found in Appendix B The fins were secured with epoxy directly on to the carbon fiber motor mount casing each fin 120 apart 3 slots each 120 apart and approximately 0 14 inches wide were cut into the aft section of the body to account for the width of the fins The motor mount was then inserted into the aft section
62. 3 1 1 Requirements eise ce RO sella RS aa 15 3 1 25 Mehicle SUCCESS CHIENS a eo edu Die EU MD UM d d dae 15 31 3 ASUS Velen SUCCESS Criteria d p poveri SSSR 15 321 4 V Publ Profile sotto bu ent e uie dcdit ce 16 3 2 JDesipH and CODSIUCHONR rrisin eee t t Sep tei A eR t uisa sas 17 3 2 1 Structural Elements gt e Ee ERU als 20 3 2 1 1 Material Selection Anessa ece 20 3 21 25 Body T b6s re AL E ern ee a 22 3 271 3 Motor MoN ententen dta cte ete a tie ree t e ote eade lue tet et tup 26 3 2 1 4 SectioriSec rernent eines eren eset repe retinere tee abb esee E SNE E 27 3 2 2 3 Electrical 28 EAE nam E 28 924 Pullscale Festing coctis roa ONE noni to es e pa eat 28 92 2 Workmanship anna RAUS 29 2 2 55 Safety and Failure Analysts io oo ite a a dietis eese 20 3 227 Mass STALE MGI Dt poa 30 3 3 Payload 31 3 3 1 4 OSCULO UL 32 3 3 2 gt 33 3 33 ASSEMBLY say 35 334 Component oh 35 3 3 29 lt Safety and Failure Analysts dedo s tto Do LEM 35 34 Recovery SUBSYSTEMS AAS a 36 3 4 1 Structural Elements oe e e IA PARS
63. ACGIH N A N A Non Volatile N A N A Natural yellowish green to green with no odor 1 75 1 85 Non Volatile Water CO2 or Foam Appropriate respiratory equipment atmosphere supplying should be used when entering burning area Carbon Monoxide may be released while burning Stable Will decompose from exposure and heat as function of time over 140 C 550 Mallory Way Carson City NV 89701 775 283 4400 800 475 2214 www potymerplastics com 179 MATERIAL SAFETY DATA SHEET SECTION VI REACTIVITY DATA CONTINUED INCOMPATIBLE MATERIALS DECOMPOSITION PRODUCTS HAZARDOUS POLYMERIZATIONS Will not occur POLYMERIZATION AVOID SECTION VII SPILL OR LEAK PROCEDURE FOR SPILL N A WASTE DISPOSAL METHOD Landfill SPECIAL VIII SPRECIAL PTOTECTION RESPIRATORY PROTECTION Processing equipment should be equipped with an adequate exhaust system Dust from machining should not be inhaled VENTILATION PROTECTIVE GLOVES EYE PROTECTION Protect from flying chips when machining OTHER PROTECTIVE EQUIPMENT HANDLING AND STORAGE Protective gloves and clothing can be used to prevent coming in contact with the skin SECTION IX SPECIAL PRECAUTIONS HAZARD CLASS DOT SHIPPING NAME REPORTABLE QUANITY RQ UN NUMBER NA PACKAGING SIZE Notes All information recommendations and suggestions appearing herein concerning this product are based upon data obtained from the manufacturer and o
64. ASS nut etose Fiberglass FAA re Federal Aviation Administration GET IT and GO Girls Exploring Technology through Innovative Topics Girls Only iE eM Ground Support Equipment GONG uci ee M ted Guidance Navigation Control CIE cessat ON Apto Global Positioning System HDE esse Oe REA High Density Foam TIMSAFE Illness Medications Stress Alcohol Fatigue Eating SR tdeo sete Intelligence Surveillance and Reconnaissance Matrix Laboratory Maryland Delaware Rocketry Association MESA Maryland Mathematics Engineering Science Achievement MSL Mean Sea Level MURS Multiuse Radio Service NAR A oreste eode ME National Association of Rocketry NASA M National Aeronautics and Space Administration iive npe National Eagle Scout Association Polyvinyl Chloride OFDD Debt cns isi Quality Function Deployment eS Rocket Equipped Payload Transportation and Autonomous Release NIS Range Safety Officer SEBIJSS SA Stiff Fiberglass DCN E NE Safety Reliability and Quality Assurance STEM eiit iet e bet esee Science Technology Engineering and Mathematics TRA osi dotate o Tripoli Rocketry Association TD Video teleconferencing and communication UST uoo eto University Student Launch Initiative USNA cT United States Naval Academy USNA MSTEM Unite
65. Data Sheet according to Directive EC 1907 2006 Revision 21 11 11 Page 3 of 3 Product Lantor Soric XF SF TF LRC 9 Physical and chemical properties Appearance the colour of the product as supplied Off white Odour Neutral pH not applicable Boiling point boiling range not applicable Melting point meling range 250 265 C PES fibres jon temperature 450 C Flash point n Flammability nct easily flammable see section 10 Autoflammability temperature gt 450 Oxidizing properties not applicable Vapour pressure not applicable Relative density nct applicable Solubility water solubility insoluble in water fat solubility nct applicable Partition coefficient n octanol water not applicable 10 Stability and reactivity The material is chemically stable 11 12 13 Under thermal decomposition flammable and toxic fumes be generated The generation of Cleavage and oxidation products is subject to fire conditions Non burned residues and contaminated water after fire fighting should be disposed of in compliance with official regulations Molten material should not be allowed to be contact with the skin to which it can cause burns Toxicological inf t Acute toxity None Local effect None Chronic short and long term toxity None Note Under decomposition conditions toxic fumes and contaminated water see section 10 Ecological infe There is no indication that thi
66. Flight Readiness Review 13 MAR 15 Navy Rockets United States Naval Academy Annapolis Maryland 1 C Midshipmen Capstone Aerospace Engineering Department Team Mission The mission of Navy Rockets is to provide an expansion and application of classroom knowledge through a unique project based engineering opportunity Navy Rockets also strives to develop members morally and mentally by imbuing them with the highest ideals of engineering leadership and practice During this year s Student Launch program Navy Rockets will deliver a rocket and ground support element that incorporates a payload delivery system that meets all required criteria as defined by NASA and Centennial Challenges guidelines Overall Navy Rockets is committed to excellence in practice delivery and conduct Navy Rockets Charter The vision of Navy Rockets is to gt Supplement academic material in both the aerospace and engineering fields Expand each midshipmen s knowledge and experience to become more proficient and well rounded members of the engineering community Provide leadership opportunities in a technical environment to better serve midshipmen as future leaders in today s Navy As a team we strive to gt Seek out projects that can benefit the aerospace community and reinforce our own educational objectives Deliver quality research and products on time based in sound engineering and business practices and operate to a level above cli
67. From this calculation the kinetic energy values for the two separate sections is well under the required 75ft lb requirement 3 6 6 Drift Analysis Due to the large size of the Navy Rockets launch vehicle wind has a significant impact on the recovery portion of the flight profile According to simulation data at no point will the wind affect the target altitude of the rocket as the 3000 foot mark is consistently met However the lateral drift due to the wind does become as problem When modeled using the OpenRocket and the best case scenario with regards to wind 5 launch angle oriented into the wind the launch vehicle stays within the required 2500 feet of lateral drift in wind speeds up to 20 mph When modeled using the worst case scenario 5 launch angle oriented with the wind the launch vehicle crosses this 2500 foot mark at winds of roughly 13 mph It is important to note at this point that all drift values are unique to the main body section that is jettisoned at 1000 feet AGL In all simulations this section drifted farther than the payload section The drift data at both the best and worst case scenarios at various wind speeds is seen in the Table 10 and Figure 37 54 Table 10 Wind Drift Values at the Best and Worst Case Scenarios Upwind Best Case Downwind Worst Case Wind Speed Lateral Drift Altitude ft Lateral Drift Altitude ft mph ft ft 0 644 3089 644 3054 5 83 3072 1341 3046 10 823 3052 2
68. GSE When the run button is pressed the laptop will send commands to the Scorbot to initiate the payload insertion process When the Scorbot has completed its series of events the laptop will send a command to the payload bay after a 10 second delay The signal will be sent via radio frequency transmitter When this signal is received by the payload bay the payload will be secured and the payload bay will close There will be a 10 second delay once the payload bay 15 closed At the end of the 10 second delay the laptop will send a command to the motor system via transmitter to erect the rocket Contained within the motor driver system will be an encoder unit that will relay information back to the laptop including a signal to indicate when the rocket has reached its final position The number of motor wheel rotations required to erect the rocket will be determined during the testing phase When this completion signal is received by the laptop a signal will be sent to the igniter insertion device via RF transmitter A micro switch on the igniter insertion device will return a signal indicating completion of the igniter insertion process Pressing the pause button at any time during this series of events will stop all processes Lights will indicate when the AGSE is carryout out the assigned tasks as well as when the process is complete and the system is ready for launch The use of several transmitters ensures that any unwanted communication between sepa
69. Lantor Soric SF TF LRC 3 Composition Information on ingredients Identification of the type of nonwoven product 3 1 Nonwoven Carded web chemically bonded 3 2 Nature of the fibre s Polyester PES 3 3 Web surface treatment Concentration above 1 n 3 4 5 roars CAS nr 38742 70 0 Iso pentane CAS nr 78 78 4 3 6 Other major components Concentration above 1 None None 3 7 Chemicals in relevant concentration that are in the list of dangerous substances None 4 First aid measures 41 Inhalation By inhalation of microspheres move person to fresh air Skin contact No specific measure to be taken 43 Eyes contact de 5 Fire fighting measures 5 1 Suitable extinguishing media Water water foam CO 5 2 Extinguishing media not to be used Water in case short circuiting is the cause of the fire 5 3 Special exposure hazard For flammable and toxic fumes as well as skin contact with molten materials see section 10 5 4 Special protective clothing for fire fighter No special requirement 6 Accidental release measures Not applicable 7 Handling and storage Keep Lantor Soric in the original package Store in a cool and well ventilated area The temperature should be above 0 but must not exceed 30 42 44 8 Exposure controls personal protection ventilation is recommended General room 182 oon Material Safety
70. M Precision Planetary Gearmotor Planetary Gearmotor Mount A 0 625 L x 6 32 Zinc Plated Alloy Steel Socket Head Cap Screw Scorbot ER V Lenovo ThinkPad 11e Aluminum Square Tubing 2 x2 x1 8 Aluminum Round Tubing 1 Dia Aluminum Stock and Plating Steel Spur Gear 20 Pitch 15 Teeth Roller Chain ANSI Number 35 3 8 Pitch 20ft length Roller Chain ANSI Number 35 3 8 Pitch 10ft length Roller Chain Attachment Link Tab Syle for ANSI 35 Chain Connecting Link for ANSI 35 Chain T Handle Push Button Quick Release Pin 3 16 x 2 T Handle Push Button Quick Release Pin 3 16 x 2 1 4 Steel Machinable Bore Sprocket for ANSI 35 Roller Chain Rubber Wheel 4 Diameter Steel Flange Mounted Ball Bearing 1 Shaft Diameter Aluminum Channel 6063 2x1x1 8 16 ft Firgelli Automations Light Duty Rod Actuator 1501b 24 Power Sonic 12V 75AH Battery Roboteq SDC1130 Brushed DC Motor Controller NPC T74 Electric Motor MaxStream xBee Pro 900HP Wireless Serial Modem Cesaroni K 1200 54mm Motor Cesaroni 54mm 5 Grain Case Tube Fabric 2 125 x2 253 x72 Pro 54 Rear Closure P54 CL Retainer 54mm Flanged AP54 Unit Cost 43 50 33 35 82 05 21 40 6 95 26 95 2 95 599 99 249 99 12 50 2 70 49 46 201 16 166 92 62 06 9 99 1 15 9 95 1 56 9 99 23 95 9 95 7 96 39 00 15 33 7 99 5 99 1 49 4 99 2 99 7 99 1 59 0 89 27 99 4 99 2 59 2 000 00 505 55 85 00 32 00 150 00 18 53 78 00 39 00 2 66 7 00 19 16 19 18 44 45 6 57 37 6
71. Mass 1 6 Ib Mass 1 75 lb Mass 2 lb Mass 0 097 Ib Mass 0 Ib Mass 1 71 lb Mass 0 382 Ib ig Len 120m Len 5 5 in Mass 0 108 lb Mass 0 496 lb ____________48 Len 20 in SS sss Ogive 1 85 gem Diasa 2 in PVC Diasa 4 843 in 1 89 Dia 4 843 Leni ami Diasa 5 in Diaew 1 5in Dias 4 25 in Dias 4 843 in 1 85 aiem PVC Dia 4843in 1 08 Diasa 4 843 in Fiberglass Dia 4843in 2 80 arene Diasa 5 in 7 Tubular nylon Lines 6 14 mm 9 16 in Tubular nylon 14 mm 9 16 in Tubular nylon Limes 6 14 mm 9 16 in Tubular nylon 14 mm 9 16 in Fiberglass Dia 4843in 2 88 Diaew 5 in PVC Dia 4843in awe Diasa 4 843 in Dias 3 984 in PVC Dia 4 843 n Diaew 4 843 Fiberglass Diasa 4 843 in Len 180 in Len 14 5 in Len 6 5 in Len 6 5m Len 0 079 in Mass 0 161 Ib Mass 2 4 Ib Mass 0 lb Mass 4 7 lb Mass 0 lb Mass 0 097 lb abe Trapezoidal fin set 3 Fiberglass Ripstop nylon 7 gmt Tubular nylon 14 mm 9 16 in 28 am 1 59 Carbon fiber 1 78 gem Diasa 4 843 in Dia O lin Diaew 0 1 in Diae 4 843 n 5 in Dia 2 126 in Diaew 2 165 in Diasa 24 in Lines 6 Dia 2 165 in Diasa 4 843 in Dia 4 843 Diasa 4 843 in Dia 2 165 i
72. Number 439 3227 00SU C000 12 Date October 1 2002 Page 3 of 6 Section 4 FIRST AID MEASURES Continued Ingestion Ingestion of this product or the dust from it is unlikely If swallowed get medical attention immediately Section 5 FIRE FIGHTING MEASURES Flash Point Method of Determination Not determined Means of Extinction Use water spray dry chemical or to extinguish fires Special Fire Hazards Avoid exposure through use of a self contained positive pressure breathing apparatus Section 6 ACCIDENTAL RELEASE MEASURES Procedures in case of Accidental Release or Leakage Avoid contact with skin eyes or clothing See Section 8 Clean up material put into a suitable container and dispose of properly See Section 13 Section 7 HANDLING AND STORAGE Precautions to be taken in Handling and Storage Store in a cool dry place Maintain sealed against contamination from dirt and moisture Section 8 EXPOSURE CONTROLS PERSONAL PROTECTION Eye Face Protection Avoid eye contact Wear safety glasses with side shields as necessary when using this product or when machining grinding or sawing the cured product Skin Protection Protective clothing such as a loose fitting long sleeved shirt that covers to the base of the neck long pants and gloves as necessary to prevent irritation Skin imitation is known to occur primarily at pressure points such as around the neck wrist waist and between the fingers Respiratory
73. Parts 170 179 These regulations cover packaging labeling and the safety testing and classification that is required prior to shipment These regulations are of great concern to manufacturers and dealers and there are severe penalties for non compliance Basically it is illegal to send rocket motors by UPS mail Federal Express or any other common carrier or to carry them onto an airliner except under exact compliance with these regulations The reality of these regulations and the shippers company regulations is that it is virtually impossible for a private individual to legally ship a rocket motor of any size Transportation of motors on airlines is very difficult to do legally and should be avoided if at all possible It takes weeks of advance effort with the airline and in the post September 11 worlds is probably not even worth attempting Insurance Most property owners whether government bodies or private owners will demand the protection of liability insurance as a precondition to granting permission to fly sport rockets on their property The NAR offers such insurance to individual fliers to chartered NAR sections and to flying site owners Individual insurance is automatic for all NAR members It covers only the insured individual not the section or the site owner Under the current underwriter this insurance runs for a 12 month period coincident with NAR membership Sections are insured as a group fora year remember that sec
74. RQA Safety Reliability amp Quality Assurance Chief e Materials Structures Chief Joe Astronautical Engineering 15 e Technology Officer e Propulsion Chief Richie Astronautical Engineering 15 e Financial Officer e GSE Ground Support Equipment Chief Thor Astronautical Engineering 15 e Acquisitions Officer e Payload Design Chief Sam Astronautical Engineering 15 e AGSE Coding Chief e Tower Erection Lead Troy Aeronautical Engineering 15 e Public Affairs Outreach Officer e Aerodynamics Chief Andy Astronautical Engineering 16 e Project Assistant e Igniter Insertion Lead 11 2 Changes to the Critical Design Review 2 1 Vehicle The overall rocket length changed from 103 inches to 108 inches During the building process the sections were cut slightly longer than first planned so that the sections could be tested While verifying if everything would fit properly it was determined that 5 additional inches would be required to ensure that none of the equipment was damaged By jamming equipment into the rocket it causes a safety concern and potential failure mode however it was fixed by this increased length The rocket body tube mold originally had its own coupler built into the tube The idea was that each piece would have a 4 inch shoulder that was one continuous piece of tubing However while attempting to connect sections together the designed couplers did not fit perfectly inside the other tubes
75. UE d cta a 83 9 15 LAUNCHER Mna d bees cL es 84 5 1 6 InstalldBolrg ii op eode dae dedi ota le nega pam d e dune 84 5 1 7 Launch Procedute isis e ER ERES RASA T ASI BESSER ANN MR Ra TA REN EU Ue Uu S 85 5 1 9 Troubleshooting sooo Er uet Te ot pec t vt iuda 85 5 1 9 Post fisht TAS BSC OB scaena edd ee a RN Ioab eques euentu AL 86 5 2 Safety and Q a lity ASS TANCE ecela 86 5 2 1 Safety and Quality Inspector SEDA SESSA 86 5 2 2 Safely ANALYSIS NE EE 86 5 2 2 1 O SESS aso o s qo REIN 86 5 2 22 MSDS errira EEEE ee a EA e E E sete 87 5 2 3 Operational Risk etae terno E ea eee Dens 87 2 4 4 Personnel Hazards e pU P Oe E URP e VON 94 2 22 Environmental CONC EMS 97 AS iube luu a ctp E Lo Dee a aet Re 100 6 1 Budget Plan 100 6 2 sso ense 102 6 3 juo fe RETI pM ES 102 6 4 Bd cauonal amp DID Gest ot EP inueni aee 104 GT STEM COOIGIBlloR suis t UR XH aaa aS 104 6 4 2 Team Participation cesses aA e Rasa a WE ere epa 105 LS STEM LSVEHS eoi ebat Duos atta ta bita nu cot RRS 105 6 43 1 MESA DAY irri tete aes tange eek tee
76. above 14 500 feet within 5 miles of the boundary of any airport into cloud cover greater than 50 or visibility less than 5 miles within 1500 feet of any person or property not associated with the operation or between sunset and sunrise Both NFPA Code 1127 and the NAR high power safety code require compliance with all FAA regulations Deviation from these FAR limits for unmanned rockets requires either notification of or granting of a waiver by the FAA Such a waiver grants permission to fly but does not guarantee exclusive use of the airspace The information required from the flier by the FAA is detailed in section S 101 25 of the FAR 14 CFR 101 25 If the rockets are no more than 1500 grams with no more than 125 grams of propellant no notification of or authorization by the FAA is required Larger rockets require a specific positive response from the FAA Regional Office granting a waiver before flying may be conducted and the waiver will require that you notify a specific FAA contact to activate a Notice to Airmen 24 hours prior to launch The waiver is requested using FAA Form 7711 2 available from any FAA office or the FAA website This form must be submitted in triplicate to the nearest FAA Regional Office 30 days or more in advance of the launch and it is advisable to include supplemental information with it including copies of the Sectional Aeronautical Chart with the launch site marked on it and copies of the high power safety cod
77. ack to the two eyebolts mounted in the motor centering ring This configuration was used to ensure that the deployment force was better distributed across the entire motor mount instead of a single off center point The main recovery harness measures 15 feet and the payload harness measures 12 feet Each length of tubular nylon is attached to both the eyebolt and its associated parachute shroud swivel via a Black Diamond Positron screw gate carabineer depicted in Figure 22 Each carabineer is rated for 1800 Ibf and as proved during the full scale launch can withstand any deceleration forces experienced during recovery Figure 22 Black Diamond Positron Screw gate Carabineer 3 4 2 Parachute Characteristics At lift off the launch vehicle weighs 27 7 1bs which translates to 24 8 Ibs at motor burnout After jettison the payload section weighs 15 34 165 and the main body weighs 10 75 16 The parachutes were chosen to withstand these weights and maintain appropriate rates of descent to meet the prescribed kinetic energy requirements as is discussed in Section 3 6 5 The drogue parachute used is a 24 inch diameter elliptical rip stop nylon parachute that will slow the rocket 38 down to an optimal descent rate 48 23 ft sec from 3000 feet AGL to 1000 feet AGL The main and payload parachutes are torroidal shapes with diameters of 72 inches and 60 inches respectively The toroid shape was chosen for its high drag drag coefficient 2 4 while
78. al systems for the systems will be discussed in their respective sections 3 2 3 Assembly The rocket consists of five sections the motor section main avionics main parachutes payload and nose cone The main avionics section has a coupler secured on both ends so that it assembles into the motor section and connects to the main parachute section The payload section also has two couplers on it so that it connects into the main parachute section and then will hold the nose cone 3 2 4 Full scale Testing Navy Rockets completed full scale testing of the rocket on 07 Mar 15 The rocket launching can be seen in Figure 16 This launch did not include the AGSE system or the payload securement system To account for the mass of the payload securement a mass simulator was secured into the payload section of the rocket This mass allowed the rocket to equal the weight of the full scale rocket At this weight and flying on the full scale motor Cesaroni K1200 the rocket was predicted to reach 3054 feet and reached 3023 feet The avionics were able to deploy the black powder charges and open the parachutes The recovery system brought the rocket back down to Earth with a gentle landing The GPS system was verified with the launch and sections were only five feet away from what the system outputted their location Figure 16 Full Scale Rocket during Launch 28 After the recovery the structural integrity of the rocket was inspected and only one sma
79. altitude off of main avionics Turn off electronics Check for extra black powder remove motor Secure all sections Examine structure Dy ur qe pr Once the launch vehicle payload section has landed and been recovered the control computer of the AGSE will be used to send an Open command to the payload section via wireless transmission This command will activate the DC motor to open the payload section and then activate the servomotor to retract the payload securement tab At this point the standardized payload sample will be removed from the payload section of the rocket The checklist for this procedure is as follows 1 Inspect launch vehicle payload section for integrity and proper orientation 2 Use AGSE control computer to send Open command to payload section 3 Inspect interior of payload section for integrity 4 Remove standardized payload sample After AGSE payload recovery 1 Debrief flight conduct 2 Performance overview 3 Lessons learned 5 2 Safety and Quality Assurance 5 2 1 Safety and Quality Inspector Navy Rockets Safety Reliability and Quality Assurance SRQA chief Cole will conduct all inspections of the rocket AGSE and environment Cole will conduct safety briefs to ensure that the team complies with all rules and regulations and also attempt to reduce any risk from working The SRQA chief has final say on operations that may become unsafe however the team is encouraged to alert everyone if th
80. am to indicate the position of the Scorbot arm throughout the insertion process Encoders the various motors used will indicate when they have completed their respective rotations or extensions The position repeatability of the Scorbot is advertised to be 0 5 mm or 0 02 inches at the tip of the gripper This satisfies the requirement that the payload is placed within 0 5 inches along the longitudinal axis of the rocket and 0 3 inches left or right of the centerline of the intended payload insertion position The AGSE shall erect the rocket to no less than 85 degrees to avoid improper locking of the gate latches If intended 85 degree mark is not reached the rocket sled will fail to lock into position If the tower sled is erected to more than 85 5 degrees the brackets securing the gate latches could be damaged The linear actuator incorporated by the igniter insertion must insert the igniter within 0 5 inches to avoid over insertion and potential damage to the insertion unit 4 4 Testing and Verification Plans The Scorbot testing phase will be done using only the full scale version of the AGSE system The Scorbot will initially undergo independent testing The testing will be conducted using a dummy payload composed of PVC pipe and sand filling designed and built from the engineering 75 drawings for the project shown in Figure 52 A mock payload bay will be constructed with PVC and wood The Scorbot positions will be determined and programmed Th
81. and jettison the forward payload section of the launch vehicle The main body will deploy a 72 inch torroidal parachute and the payload section will deploy a 60 inch torroidal parachute The Flysheet for the rocket can be found in Appendix A 1 3 AGSE Summary Project Title REPTAR Rocket Equipped Payload Transportation and Autonomous Release System The Autonomous Ground Support Equipment is designed to insert the payload with the use of a Scorbot ER V and remotely secure the payload within the payload compartment Following this the AGSE will move the rocket from a horizontal loading position to the final launch position which is 5 degrees from the vertical plane Upon placement of the rocket into the launch position the AGSE will insert the rocket motor igniter Once the igniter has been inserted the rocket will launch off of the 10 foot launch rail All AGSE tasks will be issued from a laptop computer through RF transmitter and receiver units The entire sequence will be completed from start to finish within a 10 minute window 10 1 4 Team Members Team Size 9 Midshipmen Hayes Astronautical Engineering 15 e Team Manager e GNC Guidance Navigation Control Recovery System Chief e Systems Engineering Integration Chief Alex Astronautical Engineering 15 e Administrative Officer e Chief Engineer e Drafting Chief e Avionics Chief Cole Aeronautical Engineering 15 e Document Manager e Safety Administration Officer e S
82. articular modem provides the best mix of these characteristics when compared to other similar products A wireless product was necessary for the payload bay because it eliminates the logistical issue of having a wire run from inside the rocket to an external point That arrangement could cause issues during erection and launch so the wireless modem was selected e 12 Volt Battery Power Source o This battery configuration will be able to provide power to all of the electrical components of the payload section of the rocket This particular power source was selected due to its weight cost availability and meeting of the minimum performance characteristics required for the payload bay e Arduino Micro Control Board o This microcontroller operates at 5 Volts It has 20 digital input output pins as well as a 3 3 Volt power output which is compatible with the xBee Pro The Arduino control board was selected for its small size low cost user friendliness and compatibility with other components It is shown below in Figure 19 z H o Le 4 Figure 19 Arduino Micro in Testing Configuration 34 3 3 3 Assembly Once the body tube and nosecone were completely constructed assembly of the payload section began First the two aluminum support rods were mounted through the aft bulkhead of the payload section Next all of the components except for the gear track and support slide were mounted to a fiberglass board which w
83. as subsequently mounted to the aluminum support rods both of these were done using mechanical fasteners and epoxy Finally the gear track was mounted to the nosecone and run through the gear in the payload section additionally the support slide was mounted to the interior of both the nosecone and the payload section tube These attachments were also done with mechanical fasteners and epoxy Following assembly of the finalized payload section an inspection was done to ensure proper assembly and mounting of all components before testing began on the actual full scale launch vehicle payload section 3 3 4 Component Testing As each component of the payload section was acquired it was tested to ensure that it met both manufacturer specifications and payload section requirements Once each component was individually verified it was integrated into the full scale payload section mock up for testing The mock payload section utilizes tubes made of the same fiberglass as the actual launch vehicle A full second set of payload section components is mounted in these tubes in flight configuration An external xBee Pro wireless transmitter sends a signal to the mock up s xBee Pro to begin test iteration The servomotor then rotates the securement tab over the payload and the brushed DC motor retracts the nosecone and seals it to the body of the launch vehicle This test was deemed a success when 23 of 25 consecutive iterations were successful Once this te
84. ata showed that the mean and median Cp of the rocket design was both 0 51 As shown in Table 11 the Cp did not change significantly at varying Reynolds numbers and stayed around 0 51 the whole time 58 Table 11 Cp Values from Wind Tunnel Renoyld Number million per foot Average Co 1 37 0 516 1 48 0 520 1 58 0 524 1 68 0 511 1 79 0 509 1 89 0 505 1 99 0 510 Average Cp 0 51 3 7 1 6 Analysis The Cp of wind tunnel scale model closely matched that of the coefficient developed the OpenRocket software From the Cp the determination of the height of apogee is simple based on the trust curve of the motor and the weight and drag of the rocket Because the drag coefficient given by open rocket can be trusted it can be assumed that the height of apogee determination is trustworthy as well Further testing on the full scale model will confirm the value given by OpenRocket software 3 7 2 Requirement Verification Navy Rockets have completed and verified all AGSE requirements for the project The list of requirements and verification methods can be found in Appendix D 3 8 Vehicle Safety 3 8 1 Safety Analysis Some of the major safety concerns for the vehicle can be found in Table 12 These safety concerns have been considered during the planning and building process to ensure that everything works safely These failures have been mitigated so that the rocket can launch and be recovered successfully 59 Table 12 V
85. based upon available data and believed to be correct however as such has been obtained from various sources including the manufacturer military and independent laboratories it s given without warranty or representation that it is complete accurate and can be relied upon GOEX Incorporated has not attempted to conceal in any manner the deleterious aspects of the product listed herein but makes no warranty as to such Further GOEX Incorporated cannot anticipate nor contro the many situations in which the product or this information may be used there is no guarantee that the health and safety precautions suggested will be proper under all conditions It is the sole responsibility cf each user of the product to determine and comply with the requirements of all applicable iaws and regulations regarding its use This information is given solely for the UC ae DIXI Any other of this information is expressly prohibited For further information contact GOEX Powder Incorporated P O Box 659 Doyline LA 71023 0659 Telephone Number 318 382 9300 Fax Number 318 382 9303 172 Steel Snaps Fiber Unaffected IMP T PA 16 Inches 1096 Point ELECTROSTATIC DISCHARGE TEST Bureau of Mines 0 8 Joules Confined 12 5 Joules Unconfined STABILITY 75 C International Heat Test 0 31 Loss Vacuum Stabiiity 0 5 100 C BRISANCE Sand Test 8 gm VELOCITY the open trai
86. be described including the application for which the tank was designed and the history of the tank including the number of pressure cycles put on the tank by whom and when Structures 121 1 45 teams shall successfully launch and recover a subscale model of their full scale rocket prior to CDR The subscale model should resemble and perform as similarly as possible to the full scale model however the full scale shall not be used as the subscale model All All teams shall successfully launch and recover their full scale rocket prior to FRR in its final flight configuration The rocket flown at FRR must be the same rocket to be flown on launch day The purpose of the full scale demonstration flight is to demonstrate the launch vehicle s stability structural integrity recovery systems and the team s ability to prepare the launch vehicle for flight A successful flight is defined as a launch in which all hardware is functioning properly i e drogue chute at apogee main chute at a lower altitude functioning tracking devices etc The following criteria must be met during the full scale demonstration flight All 1 1 14 1 The vehicle and recovery system shall have functioned as designed Recovery 1 14 2 The payload does not have to be flown during the full scale test flight The following requirements still apply All 1 14 2 1 If the payload is not flown mass simulators shall
87. be launch ready or not able to be launched again manufacturing of the rocket and strength testing to ensure it can withstand the required loads sustained all structural loads during test launches The payload section jams or will not secure properly The rocket will not be safe to launch and the payload could fall out Testing and inspecting the payload section to ensure that everything works properly 92 section separation Delayed section separation Bulkhead failure Systems lacking enough power Recovery system lines fail Avionics will not track The connection Rocket does not Testing of the Couplings points are not reach required connection points checked for strong enough to altitude or as well as full proper hold the rocket damages itself scale testing of connection together during flight the rocket friction to separating prevent early separation The connection Rocket will not Testing of the Couplings points are too deploy connection points checked for strong holding the parachutes at the as well as full proper rocket together proper altitude scale testing of connection and will not allow the rocket friction to it to separate separating prevent early separation The bulkhead Rocket will not Testing the Bulkheads breaks from the deploy strength secured with ejection canisters parachutes at the conditions of
88. chute to slow recovery Then at 1000 feet AGL a second recovery event occurs deploying both the main and payload parachutes as well as jettisoning the payload section The full recovery harness is attached to the launch vehicle body at four separate structural bulkheads two for the drogue and one for both the main and payload parachutes 3 4 1 Structural Elements The bulkheads are made of G10 Fiber Epoxy Laminate a material that was easier to cut the bulkheads from than carbon fiber without losing any strength or stiffness Three of the four bulkheads are mounted within the sectional PVC couplers as seen in Figure 15 Each coupler has a significant lip built within the inner waist It is against this lip that the bulkheads are mounted opposite the direction of parachute deployment and secured by epoxy This mounting technique allows a secondary normal force to act upon the bulkheads once the parachutes are deployed thus increasing the robustness of the connection point The aft attachment point for the drogue chute differs however due to its location The attachment bulkhead is the forward motor mount centering ring mounted to the inside of the body tube as well as the motor tube via the same epoxy This can be better seen below in Figure 20 It is important to note that the figure depicts molded eye bolts Navy Rockets employed open eye bolts that were sealed shut with epoxy 36 Figure 20 Recovery Harness Attachment Points Figure
89. course of the flight Using open rocket the CG and CP were calculated to be 56 8 inches and 80 1 inches from the nose cone respectively during flight c 9 gt a S o D D i Angle of attack o a siage ulbiew 41114615 w in 3 25 r 3 00 Time s Angle of attack Stability margin calibers Figure 36 K1200 Stability Margin and Angle of Attack vs Time 52 This plot helps predict the flight path of the rocket during testing which will lead to modifications and a change in motors if necessary Stability margin is measured in calibers and is defined as the ratio of the distance between the CG to CP and the diameter of the rocket Typically stability margin should be kept between one to two calibers from the original margin The main rocket the margin was an average of 4 15 This is high but the possible instabilities here are not nearly as worrisome as a stability margin below one caliber A stability margin of around 4 is typical in high power rocketry and additional simulations and flight observations proved the rocket would not be affected The high stability margin makes the rocket overly stable and results in a reduced chance of flight alternation from any external forces The overly stability of the rocket is not great enough to alter the flight path during the possible flight conditions The stability margin is high during the flight and the rocket will b
90. ctive harm or both 16 OTHER INFORMATION Changes made in Section 14 and 15 MSDS 105133 TE ees brated ony spec mula Geeta naten Wee Rem Ho mes no egal S ror or Tetanos upon mese 143 MATERIAL SAFETY DATA SHEET West System Inc aliphatic FORMULA applicable MANUFACTURER EMERGENCY TELEPHONE NUMBERS West System Inc Transportation 102 Patterson Ave CHEMTREC s 800 424 3300 U S PRIMARY ROUTE S OF ENTRY SKIN contact eye contact Inhalation POTENTIAL HEALTH EFFECTS ACUTE INHALATION respiratory tract irtatjon Coughing and chest pain may result CHRONIC INHALATION respiratory tract Imitation coughing sore throat shortness of breath or chest pain ACUTE SKIN CONTACT sss Cause strong irritation redness Possibile mild corrosion CHRONIC SKIN Prolonged or repeated contact may cause an allergic reaction and possible sensttzaton In susceptible Individuals Large dose skin contact may result In material being absorbed In harmful amounts EYE CONTACT trt MOderate to severe Imitation with possibile tissue damage Concentrated vapors can be absorbed In eye tissue and cause eye injury Contact causes discomfort and possible comes Injury or conjunctvitis INGESTION e SINGE 06 Oral toxicity Is moderate May cause gastrointestnal tract Imitation and pain Aspi
91. d respiratory tract irritation Carbon fibers or dust are electrically conductive and may create electrical short circuits which could result in damage to and malfunction of electrical equipment and or personal injury 148 MSDS Number 439 3227 00SU C000 12 Date October 1 2002 Page 2 of 6 Section 3 HAZARDS IDENTIFICATION Continued EMERGENCY OVERVIEW continued Primary Routes of Exposure Eye Yes Skin Yes Inhalation Yes Ingestion No HMIS Rating Health 1 Flammability 0 Reactivity 0 Special None Potential Health Effects Eye Contact may cause mechanical irritation to the eyes If sized vapor or fumes from exposure of this product to elevated temperatures may cause imitation to the eyes Dust from machining grinding or sawing the cured product may cause mechanical irritation Skin Contact may cause mechanical irritation to the skin and possible dermatitis Dust from machining grinding or sawing the cured product may cause mechanical irritation Inhalation May cause mechanical irritation to the upper respiratory tract If sized vapor or fumes from exposure of this product to elevated temperatures may cause irritation to the respiratory tract Dust from machining grinding or sawing the cured product may cause mechanical irritation Ingestion Ingestion unlikely under normal conditions of use If any of this product or the cured product dust is swallowed seek medical attention immediately Medical Conditions Ag
92. d States Naval Academy Midshipmen Science Technology Engineering and Mathematics 1 Flight Readiness Review 1 1 Team Summary Team Name Navy Rockets Institution United States Naval Academy Mailing Address Aerospace Engineering Department United States Naval Academy ATTN NASA Student Launch Capstone Mail Stop 11B 590 Holloway Road Annapolis MD 21402 5042 Project Mentor Robert Utley NAR Level 3 NAR 71782 TRA 6103 President Maryland Delaware Rocketry Association Due to other commitments Robert Utley will not be able to attend However Robert DeHate another team s mentor will be able to assist Navy Rockets if required Navy Rockets Safety Officer Cole who is a TRA Level 2 will be responsible for the rocket and motor 1 2 Launch Vehicle Summary The REPTAR launch vehicle will be 108 inches tall with a 5 inch diameter launching off of a Cesaroni K1200 motor The rocket will utilize a redundant dual deployment system upon the recovery stage of flight This system includes two identical PerfectFlite Stratologger altimeters and four black powder ejection charges Upon apogee both altimeters will simultaneously trigger two aft facing ejection charges pressurizing the aft recovery compartment and releasing an 24 inch elliptical drogue parachute Then at an altitude of 1000 feet AGL the altimeters will trigger a second ejection event in the forward recovery compartment This event will pressurize the compartment
93. d fragments if confined Gases produced may be toxic if exposed in areas with FIRE AND EXPLOSION DATA pphc Approx Range 392 F 887 F 1 200 C 464 C ignites approx 427 C 801 F ALL EXPLOSIVES DO NOT FIGHT EXPLOSIVES FIRES Try to keep fire from reaching explosives Isolate area Guard against intruders Division 1 1 Explosives heavily encased Evacuate the area for 5 000 feet approximately 1 mile if explosives are heavily encased Division 1 1 Explosives not heavily encased Evacuate the area for 2 500 feet approximately mile if explosives are not heavily encased Division 1 1 Explosives all Consult US DOT Emergency Response Guide 112 for further details 170 Unusual fire and explosion a deflagrating explosive t is very sensitive to hazards and can also be ignited by friction and impact unconfined it burns with explosive violence and will g slight confinement Black powder is a Division 1 1 Explosive and detonation may cause severe physical injury including death All explosives are dangerous and must be handled carefully and used following approved safety procedures under the direcbon of experienced persons in accordance with all applicable federal state and local laws regulation and ondinances None of the components of Black Powder are listed as a carcinogen by NTP IARC or OSHA Not a likely route of exposure If inhaled remove to fresh air If not breathing give artificial respi
94. d to this tube by placing the tube through the rings of the two eyebolts This freely rotating connection allows the sled to change angle and keep its wheels in the tracks as it is being brought up the face of the tower The launch rail and the igniter insertion device are bolted to the top of the sled with the igniter insertion device located at the end with the wheels 70 4 2 4 Scorbot ER V A Scorbot ER V will be integrated into the AGSE because of its durability and simplicity This particular Scorbot model is capable of lifting up to 2 2 pounds and has a wide enough range of motion to handle the payload insertion process The Scorbot s range of motion as advertised in the Scorbot ER V user manual is displayed below in Figures 47 and 48 Figure 47 Top down View of Scorbot Operating Range 1040mm 41 E o E E e o T Figure 48 Side View of Scorbot Operation Range 71 The Scorbot will be placed the ground and staked into place next to the opening of the payload bay A series of waypoints will be determined and programmed once the Scorbot is in place This programming phase will be completed each time the system is set up to ensure maximum accuracy in the payload insertion phase The Scorbot will pick up the payload and carry it through each waypoint before placing it into the payload bay The Scorbot will then return to the starting position after the payload has been inserted 4 2 5 Igniter Insertion Device
95. disorders Skin allergies exposure This material is considered hazardous by the OSHA Hazard Communication Standard 29 CFR 1910 1200 See Section 11 for additional toxicological Information 3 COMPOSITION INFORMATION ON INGREDIENTS Inhalation Move to fresh air If symptoms develop and persist get medical attention Skin contact immediately flush skin with plenty of water using soap If available Remove contaminated clothes If symptoms develop and persist get medical attention Eye contact case of contact with the eyes rinse Immediately with plenty of water for 15 minutes and seek immediate medical attention IDH number 1071248 Product name Loctite Epoxy Heavy Duty Resin Page 104 154 Ingestion Keep Individual calm DO NOT induce vomiting unless directed to do so by medical personnel If symptoms develop and persist get medical attention 5 FIRE FIGHTING MEASURES Flash point gt 249 gt 480 2 F Pensky Martens closed cup Autoignition temperature Not avaliable Flammable E xplosive limits lower Not available Flammabis Explosive limits upper Not available Extinguishing media Foam dry chemical or carbon dioxide Special firefighting procedures SS eee Unusual fire or explosion hazards case of fire keep containers cool with water spray Closed containers may rupture due to bulld up of pressure when exposed to extreme heat Hazardous combustion products Oxides of carbon irri
96. dous reactions Will not occur Hazardous decomposition products None Incompatible materials Strong acids Strong oxidizing agents Strong mineral acids Reactive metals Calcium hypochiorte Sodium hypochiorte Nitrous acid and other nitrosating agents Conditions to avold Excessive heat Store away trom Incompatibie materials IDH number 1137985 Product name Loctite Epoxy Heavy Duty Hardener Page 305 160 11 TOXICOLOGICAL INFORMATION mme 12 ECOLOGICAL INFORMATION Ecological Information Not avaliable 13 DISPOSAL CONSIDERATIONS Information provided is for unused product only Recommended method of disposal Follow all local state federal and provincial regulations for disposal Hazardous waste number Not a RCRA hazardous waste 14 TRANSPORT INFORMATION u s ient of T Ground Proper shipping name Amines liquid corrosive n o s Aminoethyipiperazine Aliphatic amines Hazard class or division 8 identification number UN 2735 Packing group 1 International Alr Transportation 1 Proper shipping name Amines liquid corrosive n o s Aminoethyipiperazine Aliphatic amines Hazard class or division 8 Identification number UN 2735 Packing group l Water Transportation IMOMMDG Proper shipping name AMINES LIQUID CORROSIVE N O S Aminoethyipiperazine Aliphatic amines Hazard class or division 8 identification number UN 2735 Packing group
97. e The FAA charges no fee Ignition Safety The NAR safety codes and the NFPA Codes both require that rockets be launched from a distance by an electrical system that meets specific design requirements Ignition of motors by a fuse lit by a hand held flame is prohibited and in fact both NFPA Codes prohibit the sale or use of such fuses All persons in the launch area are required to be aware of each launch in advance this means a PA system or other loud signal especially for high power ranges and all including photographers must be a specified minimum distance from the pad prior to launch This safe distance depends on the power of the motors in the rocket the rules are different for model rockets and high power rockets Both the field size and the pad layout at a rocket range particularly a high power range must take into account and support the size of the rockets that will be allowed to fly on the range For model rockets the safe distance depends on the total power of all motors being ignited on the pad 15 feet for 30 N sec or less and 30 feet for more than 30 N sec For high power rockets the distance depends on the total power of all motors in the rocket regardless of how many are 137 being ignited the pad and on whether the rocket is complex i e multistage or propelled by a cluster of motors The distance can range from 50 feet for a rocket with a single H motor to 2000 feet for a complex rocket
98. e Using carbon fiber for a majority of the rocket allows for level K motors to be used whereas it would require an L motor to power a fiberglass rocket to the same altitude Carbon fiber will be used throughout the body to save on weight and increase the strength of the rocket In the avionics section and the nose cone the rocket will be made from fiberglass The fiberglass is strong enough to endure the forces during a flight but it also allows signal to 21 transmit Using fiberglass throughout the entire body would greatly increase the weight and decrease the strength for the thickness of the material 3 2 1 2 Body Tubes The rocket consists of both carbon fiber and fiberglass materials The process of constructing the rocket with carbon fiber and fiberglass has been taught to the team by a composite specialist from the Machine Shop in Rickover Hall This specialist also supervised the manufacturing process in order to ensure that the components come out correctly For the body tube two circle in lay molds has been extruded from high density foam shown in Figures 6 and 7 Figure 6 Body Tube Molds 48 inches 22 Figure 7 Body Tube Mold Lip The two half circles slightly overlap each other with a small lip and come to a small taper at each end This lip allows each piece of the tube to interlock with the opposite side as shown in Figures 8 and 9 When producing the tubes a quick release agent was applied to the inside of the mold
99. e Scorbot will then run 50 cycles and the results for all of the iterations will be recorded In order to consider the testing to be a successful 45 of the 50 cycles must effectively insert the payload into the mock payload bay Power consumption by the Scorbot will be measured and analyzed When the testing is deemed successful the Scorbot will be ready for use with the tower and rocket An initial program designed to test the Scorbot s capabilities and range of motion has been successfully written and tested Figure 52 Payload Tube Once the tower structure has been completed it will initially undergo testing without the use of the Scorbot or rocket At least 10 rounds of testing will be done to ensure that the tower can successfully raise the rocket sled to the launch configuration and lock the rocket sled in place The tower must successfully erect the sled 10 consecutive times to be considered successful Upon determination of the tower s capabilities the rocket will be mounted to the sled The tower structure will then undergo another 10 rounds of testing with the added weight of the rocket Power consumption by the tower motor will be measured and analyzed for integration with the rest of the AGSE The igniter insertion device will initially undergo testing with a dummy rocket The rocket will have the same physical characteristics as the real rocket including motor bore diameter The igniter insertion device will be tested 10 times
100. e over 5 000 feet AGL Avionics 1 2 3 4 The rocket is not flown at the competition launch site All The launch vehicle shall be designed to be recoverable and Ce ETE 1 3 reusable Reusable is defined as being able to launch again on the a Recovery same day without repairs or modifications 1 4 The launch vehicle shall have a maximum of four 4 independent Structures 120 sections An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute 1 5 The launch vehicle shall be limited to a single stage Structures 1 6 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours from the time the Federal Aviation Administration flight waiver opens All 1 7 The launch vehicle shall be capable of remaining in launch ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on board component Avionics Payload and Recovery 1 8 The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system The firing system will be provided by the NASA designated Range Services Provider Propulsion 1 9 The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant APCP which is approved and certified by the Nat
101. e the areas of the launch site and oversee the safety of all spectators and participants Sanctioned Launch Also called Insured Launch Any launch of a rocket that meets ALL of the following constraints Responsible person of launch shall be member of Tripoli good standing Follows the appropriate Tripoli Safety Code Legal All AHJ e g FAA waiver requirements regulations met and any required Landowner permission constraints Shall Indicates mandatory requirement Should Indicates a recommendation or that which is advised but not required ag Spectator A nonpartiicipant whose primary purpose 15 to view a high power rocket launch Spectator Area An area designated where spectators view a lugh power rocket launch Tripoli TRA Tripoli Rocketry Association Inc Requirements for High Power Rocket Operation Operating Clearanees A person shall fly a high power rocket only in compliance with a Thi code b Federal Aviation Administration Regulations Part 101 Section 307 72 Statute 749 Title 49 United States Code Section 1348 Airspace Control and Facilities Federal Aviation Act of 1958 and c Other applicable federal state and local laws rules regulations statutes and ordinances d Landowner permission 7 31 2012 130 2 Participation Participation and Access at Tripoli Launches shall be limited to the following 2 2 2 3 2 4 2 5 2 6 HPR Fliers may access a
102. e with bolts Loop chains from gears on top rung to outer gears on lowest rung Secure with connecting link to form full loop Adjust chain tighteners as need to remove slack Place motor on back portion of tower feet and secure with 4 quick release pins 83 8 Loop chain from middle gear on lowest rung to the motor gear Secure with connecting link to form full loop 9 Slide the rocket onto the launch rail 10 Connect sled to chains Tighten connector nuts to secure the sled Ensure that each wheel is on its respective track 11 Place Scorbot on ground 12 inches from payload bay Secure with 4 stakes 12 Place Scorbot driver as far from the Scorbot arm as the cable will allow 13 Run igniter wire through insertion tube 14 Connect all systems to the power source 5 1 5 Launcher Setup Setup of the AGSE will begin with the assembly of the tower structure The upper and lower components of each tower will be pinned together The rocket sled and track will then be put into position between the two sides of the tower structure The igniter insertion system is permanently attached to the sled The tower rungs and chains will be pinned into place connecting the two sides of the tower structure and fixing the sled track into place Next the tower motor will be pinned to the back of the tower structure All chains will be properly mounted on their respective gears When this is complete the rocket sled will be connected to the verticall
103. ecome less overly stable as it reaches apogee as the CG and CP move closer together This less overly stable flight will result in a continued successful balance of the degrees of freedom and an efficient rocket flight 3 6 5 Kinetic Energy The final kinetic energy of the sections was determined using several calculations beginning with the masses of the sections at different point in the flight The masses are listed below in Table 8 Table 8 Mass of Sections During Flight Sections Total Weights Pre Launch 27 70 Post Burnout 25 51 Payload 10 73 Main Body 14 78 The next step is finding the velocity of the section as it comes down By rearranging the equation to find the parachute surface area the terminal velocity V can be found for once the parachute is fully deployed using Equation 2 where S is the effective drag area of the chute Cd is the coefficient of drag p is the air density averaged to be 0 00200 slug ft and W is the weight of the rocket in Ibs 2_ _ 2 X S Cd p Equation 2 Once the final velocity was found the kinetic energy could be calculated using Equation 3 The values can be found in Table 9 53 1 mv 2 Equation 3 Table 9 Kinetic Energy Values for Sections Vehicle Section Wb Cd S fD V ft s KE ft lb Full With Drogue Deployed 25 51 1 5 3 02 62 97 1884 97 Main Body 14 78 2 2 27 14 14 45 47 94 Payload 10 73 2 2 18 85 14 58 36 34
104. ection Canisters Previously Navy Rockets has employed the use of pre fabricated ejection canisters with installed resistive e matches These canisters although convenient and easy to use typically were not capable of holding enough black powder for effective separation of rocket sections This often required the use of multiple canisters per separation event especially with redundant charges Pre fabricated ejection canisters were difficult to arrange within the section and typically laid in close proximity to one another Occasionally the heat generated by the combustion of the primary charge would cause the secondary charge to combust prematurely This created over pressure within the pressurized section which could result in a separation of the section from the recovery harness or parachute Therefore Navy Rockets has installed four permanent ejection charge receptacles on the two bulkheads of the avionics section These receptacles which are each a two inch length of 3 inch PVC pipe will be filled with the appropriate amount of black powder topped off with traditional paper wadding and capped with wind tunnel Mach tape 2 1 2 2 Wiring Diagram After reassessment of the redundancy in our system Navy Rockets determined that a common point of failure was present in electrical configuration of the primary and secondary altimeters PerfectFlite StratoLoggers are still being employed but they will be wired to electrically independen
105. ed operations can be safely conducted The information shall include for each type of Class 2 rocket expected to be flown 1 Estimated number of rockets 2 Type of propulsion liquid or solid fuel s and oxidizer s 3 Description of the launcher s planned to be used including any airborne platform s 4 Description of recovery system 5 Highest altitude above ground level expected to be reached 6 Launch site latitude longitude and elevation and 7 Any additional safety procedures that will be followed 134 b Class 3 Advanced High Power Rockets When a Class 3 Advanced High Power Rocket requires a certificate of waiver or authorization the person planning the operation must provide the information below for each type of rocket to the FAA at least 45 days before the proposed operation The FAA may request additional information if necessary to ensure the proposed operations can be safely conducted The information shall include for each type of Class 3 rocket expected to be flown 1 The information requirements of paragraph a of this section 2 Maximum possible range 3 The dynamic stability characteristics for the entire flight profile 4 A description of all major rocket systems including structural pneumatic propellant propulsion ignition electrical avionics recovery wind weighting flight control and tracking 5 A description of other support equipment necessary for a safe operation 6
106. ed to rate the hazards and failure modes for Navy Rockets Each situation requires a probability and severity which can be seen in Figure 54 The probability assigns a letter A D with A being highly probable and D most likely not occurring The severity column assigns a number I IV with I 1 being extremely dangerous and IV 4 being no threat of danger The ORM is then complete by using the risk matrix shown in Figure 55 The number value and letter that were found from Figure 55 are then used in the risk matrix to determine the risk assessment code This code is assigns a number 1 5 and is color coded to ensure that the assessment is known For the code a value of 1 is red and a critical situation which means that it is high probability of a high severity A value of 5 is almost no risk and means that it is not sever or probable The hazards and failure modes can be found in Tables 18 24 87 Probability Severity Likely to occur immediately I May cause death loss of or within a short period of time facility asset II May cause severe injury B Probably will occur in time i ess property damage C Mav occur in time May cause minor injury illness property damage D Unlikely to occur IV Minimal threat Figure 54 ORM Values Risk Matrix Probability A B C D 1 Risk Assessment Code 1 Critical 2 Serious 4 Lal c v gt v u 5 Negligible Figure 55 ORM Risk Matrix
107. ehicle Safety Analysis Failure Mode Cause Likelihood Severity Mitigation Practicing packing the Parachute fails to parachutes Poor packing or damage during deploy Low Medium and ensuring launch that all equipment is functional Ground testing and Sections fail to f Improperly connected sections Low High verification separate of the rocket sections Ensuring careful Low High building and transportation practices Defect from building process or Structural failure damage from transportation Testing the Not enough power or faulty wiring Medium High system and systems using new batteries Altimeter fails to deploy parachutes Testing and verifying that the system closes properly Payload section Section jams or will not secure all Medium High does not close the way 3 8 2 Personnel Hazards Safety during building and launching of the rocket is a major consideration for Navy Rockets The team has practiced safe procedures to ensure that no one gets injured during the competition Some of the potential concerns for the team can be found in Table 13 Navy Rockets will continue to practice safe building and launching procedures 60 Table 13 Personnel Hazards Failure Mode Cause Likelihood Severity Mitigation Poor handling of dangerous PTa enr wile burns Low High using dangerous chemicals chemicals bijuty
108. emoved The DC motor is pre mounted on the linear actuator 4 3 AGSE Configuration The initial tower configuration will have the rocket lying horizontally with the payload bay open The Scorbot shall be placed so that the edge of the base is 12 inches in the horizontal direction from the centerline of the rocket near the payload bay A diagram of the Scorbot is shown below in Figure 51 73 Figure 51 Scorbot ER V This will provide ample space for the tower to erect the rocket without coming into contact with the Scorbot The Scorbot will begin with the arm facing away from the rocket and the tip of the gripper shall rest no more than 4 inches above the ground The payload will be on the ground directly below the Scorbot gripper The longitudinal axis of the payload shall be parallel to the longitudinal axis of the rocket body All components of the AGSE excluding the laptop and corresponding transmission devices will be powered by a high performance 12 volt 75 AH battery The power supply will be regulated to meet the needs of the Scorbot tower motor and igniter insertion device The power drawn from the supply by each device will be measured during the testing phases of each respective component A voltage indicator will be used to monitor the status of the battery An added benefit of running each system individually during the AGSE sequence of events is minimizing the amount of power being drawn from the supply at any given time
109. ent expectation As representatives of the armed services we will gt Conduct ourselves in a professional manner and bring credit to both the United States Naval Academy and the United States Naval service We are committed to excellence in practice delivery and conduct Table of Contents Team MISSION C EASES ya cat Cina Nae 1 Navy ROCKS IS CAME Rye oie 1 BIST OF FIGUFES ASSES REAR SSS odis 6 LISE OF VAD ES P 8 List of A DbreviatiOnis PCI aS MTM ERREUR aS 9 bL sph Readiness REVIEW Geter 10 1 1 Tean Summary enn cures e pep lut a cip tbt bp tA Cun due 10 1 2 Launch Vehicle Summary 10 1 3 AGSE SUITEIS oia anaes 10 1 4 Team MEDES SMSO 11 2 Changes to the Critical Design Review uo aba DAI Be MD 12 2 1 C Sea 12 DAA Payload c MER 12 2 1 2 mee t ae A EE Dass usta bac oca od dM UI 13 2 1221 Ejection Canisters eae RSS em A is 13 251 252 Wirlng DETAR SDRC ERAS OA CARs 13 22 AGSE a 14 23 PPO sd MC NEM CUTEM REN 14 2 4 Sugsested CHANGES Ue YR eM dg 14 3 gt Vehicle Criteria A 15 3 1 Launch mem 15
110. esting Configuration 34 Figure 20 Recovery Harness Attachment Points itor die 37 Figure 21 Drogue Attachments in Motor Tube eese netten 38 Figure 22 Black Diamond Positron Screw gate Carabineer see 38 Figure 23 Recovery Electronics 39 Figure 24 Ejection Canisters on Avionics Section 40 Figure 25 The Launch Vehicle in Recovery Configurations after Ejection Event 1 left and Ejection Event 2 elg Jessie roe e et a a clea eee aa eld cue Mei e 42 Figure 26 Recovery Test s o eei deett rod eiut Sors hd edema du is 43 Figure 27 K600 Veritcal Motion vs THO oe tice io tentes 45 Figure 28 K 750 Vertical Motion vs Tinie 45 Figure 29 K1200 Vertical Motion vs ien 46 Figure 30 K1200 Trust and Vertical Motion vs Time 47 Figure 31 Half Scale Rocket Launch iden de ee UE Ud arido ede 49 Figure 32 Vertical Motion vs Time at 5 50 Figure 33 Vertical Motion vs Time at 10 mph aoreet gei iain 50 Figure 34 Vertical Motion vs Time at 15 ded eeu eds 51 Figure 35 Vertical Motion vs Time at 20 ire recie Eraser eds 51 Figure 36 K1200 Stability Margin and Angle of Attack vs Time
111. ey feel something becoming unsafe 5 2 2 Safety Analysis 5 2 2 1 Laws The Navy Rockets team understands the laws that govern high power rockets This includes the FAA regulation on airspace the Federal Aviation Regulation 14 CFR Subchapter F Part 101 Sub part C the Code of Federal Regulation 27 Part 55 and the code for the use of low 86 explosives NFPA 1127 Code for High Power Model Rocketry This information be found in Appendix E All of the flight testing and some ground testing for the project will be done with MDRA at their launch sites MDRA has a FAA flight waiver for an altitude of 17 000 feet every weekend of the year This allows Navy Rockets to be able to launch whenever testing needs to be completed on both the sub scale and full scale launches MDRA has a goal for zero injuries to occur during their launches the group has multiple qualified Range Safety Officers that ensure everyone is adhering to the rules 5 2 2 2 MSDS Many of the material used during the competition have hazards associated with them A list of potential material hazards can be found in Appendix F on the material hazards before they are used on any part of the project by the Safety Officer 5 2 3 Operational Risk Management Although the team focuses on safety some of the activities can still be dangerous to the team or equipment Due to the team s military ties the United States Navy s Operational Risk Management ORM system was us
112. f any for use of this product is limited to the terms contained in our sale terms and conditions We do not in any way warrant expressed or implied including any implied warranty for merchantability or fitness for a particular purpose the data contained or the product described in this MSDS Additionally we do not warrant that the product will not infringe any patent or other proprietary or property rights of others Contact David M Rubin Hexcel Schwebel Environmental Health and Safety Manager 153 Material Safety Data Sheet Revision Number 001 2 Issue date 07 10 2013 Product name Loctite Epoxy Heavy Duty Resin IDH number 1071248 Product type 2 Component epoxy adhesive Reglon United States Company address Contact Information Henkel Corporation Telephone 800 624 7767 One Henkel Way MEDICAL EMERGENCY Phone Poison Control Center Rocky Hill Connecticut 06057 1 877 571 4608 toil tree or 1 303 592 1711 TRANSPORT EMERGENCY Phone CHEMTREC 1 800 424 9300 toil free or 1 703 527 3887 WARNING MAY CAUSE ALLERGIC SKIN REACTION MAY CAUSE EYE AND RESPIRATORY TRACT IRRITATION Relevant routes of exposure San Inhalation Eyes Potential Health Effects inhalation Mid respiratory tract Irritation Skin contact Allergic skin reaction Moderate skin Irritation Itching Redness Eye contact Moderate eye irrtation Redness Ingestion Not expected under normal conditions of use Existing conditions aggravated by Skin
113. gation Pn Bua Defect in the tube from the building Low High Material process Testing Rocket Additional components or extra j Testing Overweight epoxy in the rocket MSU ocean Analysis Catastrophic The motor has a defect in which it Motor Failure explodes on the launch pad Me eee amen All of these failure risks in the launch vehicle will be mitigated and tested to ensure safety for the rocket the system and the bystanders 29 3 2 7 Mass Statement The mass for the rocket design can be found in Table 4 Completed sections were weighed individually as well as the additional components that are used in the rocket Table 4 Component Masses Fiberglass Nosecone Fiberglass Payload Section Parachute Section Main Avonics Section Motor Mount and Section 1 5 095 Launch lugs 2 0 200 0 400 TT15 Dog Device 2 0 455 0 910 Avonics Board 1 0 725 0 725 Black Powder Charges 4 0 025 0 100 Drogue Chute 24 inch 0 135 Main Chute 72 inch 0 790 Main Chute 60 inch 0 620 Shock Cord and Carbiners 1 050 Hitec HS 422 Servo Motor 0 100 Arduino Micro Microcontroller 0 030 12V Battery 1 000 1 4 Threaded Steel Rod 0 286 MaxStream xBee Pro 900HP Wireless Serial Modem 0 070 Accuride 3832C Full Extension Slide 8 1 500 11 935 Alumnium Beam 0 094 32P Beam Gear Rack 0 028 Beam Bracket S Pair 0 009 Beam Attachment Block B 0 009 1 50 Aluminum Channel 0 028 16 To
114. gravated by Exposure Preexisting eye skin or respiratory disorders may be aggravated by exposure to this product or to the dust from machining grinding or sawing the cured product Carcinogenic Information None of the components present in this material at concentrations equal to or greater than 0 1 are listed or regulated by IARC NTP OSHA or ACGIH as a carcinogen Other OSHA PEL Exposure limits for cured product dust as Particulates Not Otherwise 15 otal 10 mg m Inhalable Regulated PNOR by OSHA or 5 mg m Respirable 3 mg m Respirable Specified PNOS by ACGIH Section 4 FIRST AID MEASURES Eye In case of eye contact immediately flush eyes with large amounts of water for at least 15 minutes keeping the eyelids open Get medical attention immediately Skin In case of contact that causes irritation immediately wash skin with soap and room temperature to cool running water Use a washcloth to help remove the fibers To avoid further irritation do not rub or scratch irritated areas Rubbing or scratching may force fibers into the skin Get medical attention immediately if the irritation persists Inhalation If large amounts of dust fiber fumes or vapor are inhaled remove to fresh air If not breathing give artificial respiration preferably mouth to mouth If breathing is difficult qualified personnel may administer oxygen Get medical attention immediately 149 MSDS
115. h Initiative the Navy Rockets club is able to get continued funding and support through the USNA STEM program Other than that Navy Rockets has had a mutually beneficial relationship with the local AIAA student chapter and the local amateur rocket associations Similar to the Student Launch Initiative the local programs ask us to perform community outreach on their behalf Through outreach Navy Rockets is promoted along with promoting an interest in pertinent aerospace engineering communities and technological advances 106 The Navy Rockets team expends a lot of effort to ensure sustainability and interest in Navy Rockets Navy Rockets has attended multiple class meetings to promote rocketry mostly on an amateur level For example for the last few years members have attended aerospace open houses geared toward freshmen At these open houses Navy Rockets has a booth and hands out flyers with information about the team Aside from that Navy Rockets attends aerospace specific class wide pre registration briefs At these briefs classes are told about the classes they can register for in the oncoming semester Information about Navy Rockets and what the team does is also promulgated at these briefs 6 4 4 1 Major Sustainability Challenges and Solutions The major foreseeable challenge for Navy Rockets is team sustainability in the future It has the possibility of being difficult to find enough interest for future years to come Because all
116. harge Decomposition Temperature gt 400 C Solubility In water black powder 15 soluble In water Specific Gravity Density black powder 1 7 2 1 Propellant not available Molecular Formula Not applicable Molecular Weight Not applicable 10 0 STABILITY AND REACTIVITY 165 MSDS Prox Rocket Motor Reload Kits Page 45 Version 202 Farvisice Date Feb 2010 11 0 TOXICOLOGICAL INFORMATION Routes of Entry Skin contact not likely Sk not likely Ingestion not Effects of Acute Exposure to Product No data avalabie Effects of Chronic Exposure to Product No data avalable Exposure Limits Black Powder Pellets Ingredient Name CAS Number OSHA PEL ACGIH TLV Potassium Nitrate 7757 79 1 not established not estabisned Charcoal wa not established not established Sulphur 7704 34 9 not established not established Graphite 7782 42 5 2 5 mgm 15 mmpct TWA Propellant Ingredient Name CAS Number OSHA PEL ACGIH TLV Ammonium Perchlorate 7790 96 39 not established not established metal powder vanes vares Synthetic Rubber not established not estabisned Irritancy of the Product No data avalabie Sensitization to the Product No data avaiable Carcinogenicity Not listed by ACGIH IARC NIOSH NTP or OSHA Reproductive Toxicity No data avalable Teratogenicity No data avalabie Mutagenicity Environmental Data Ecotoxicity Data Not determined EcoFaTE Data Not determined Product As Sold Pack firmly In hole In gro
117. he bed This tab will securely hold the payload zampe in the bed during erection and fight motor will raise the rocket sled and four separate gate latches will latch onto the top and bottom of the launch sled when it reaches its launch position thus keeping it place The igniter instalation mechanim wil be mounted on a flat plate at the base of the rocket ded It wil consist of a linear actuator to which wil be affixed a flat circuler steel plate ated a thin steel tube The hear actuator and this steel tube wil both be aligned with the centerline of the rocket motor The thin steel tube wil have the ignition wire run into it and the igniter will stick out just beyond the end of the tube The tube will be initially located a short distance along the longitudinal axis of the rocket away from the motor The linear actuator wil then move the igniter up into its final ignition position within the moter CE Location of Launch Pad im inches When Rail is Horizontal Use Base of Rail as the Reference Point a 7 An initial moment ansiysis of the tower structure in the launch configuration plsced the center of gravity st approximately 40 inches above ground level This indicates that a point force of approximately 33 b5 at the top of the structure is required for the structure to begin to tip slong the plane perpendicular to the sied whee track Further analysis will De done during the built anc testing stages of project Test Plans Status and Result
118. he payload will be able to be retrieved using the same wireless signal to open the payload section again 31 3 3 1 Structural Elements The primary structural elements of the payload section and their specifications are detailed below e Hitec HS 422 Servomotor o This servomotor operates from 4 8 to 6 Volts At its slowest speed it rotates 60 degrees in 0 21 seconds and produces 46 ounce inches of torque A servomotor was selected for this portion of the payload bay due to its simplicity of use and design The HS 422 was selected due to its high durability and reliability in comparison to other servomotors It remains light weight and compact while providing the necessary performance characteristics e Actobotics 32 RPM Precision Planetary Brushed DC Gear Motor o This motor operates at 12 Volts It rotates at 32 RPM free run and provides up to 472 1 oz in of torque These component parameters satisfy the requirements of the payload section motor This particular brushed DC motor was selected for its relatively small size and low cost in comparison to other motors e Pinion Gear and Gear Track o The pinion gear and gear track being used in the payload section are produced by Actobotics to ensure full compatibility with the DC motor system The gear has a 4 mm bore to fit the DC motor shaft The gear and gear track are 32 pitch with a 20 degree pressure angle e Accuride 3832C Full Extension Slide 8 o This slide provides weight suppor
119. hould occur spontaneously keep alrway clear Get medical attention FIRE FIGHTING MEASURES PMAaMMME n E E 270 F PMCC EXTINGUISHING MEDIA ee _ Dry chemical alcoho foam carbon dioxide CO dry sand limestone FIRE AND EXPLOSION HAZARDS s _ During a fire smoke may contain the original matertais In addition to combustion products of varying composition which may be toxic and or Imitating Combuston products may Include but are not limited to axides of nitrogen carbon monoxide carbon dioxide volatile amines ammonia niic acid nitrosamines When mixed with sawdust wood or offer cellulosic material spontaneous combustion can occur under certain conditions Heat is generated as the alr oxidizes the amine i the heat Is not dissipated quickly enough If can ignite the sawdust SPECIAL FIRE FIGHTING PROCEDURES Use full body protectve gear and seif contalned breathing apparatus Use of water may generate toxic aqueous solutions Do not allow water run off from fighting fire to enter drains or other water courses 6 ACCIDENTAL RELEASE MEASURES equipment Dike and contain spil Ventilate area Large spil dike and pump into appropriate container for recovery Small recover or use Inert non combustible absorbent material e g sand clay and shovel Into suitable container Do not use sawdust wood chips or other cellulosic materials to absorb the spill as the possibility for spontaneous combustion e
120. ial or in any process The information above a buleved to be accurate and represents the best information curenfy evalabie to us However we make o warranty cf merchartalslty of Bird pany o for lost profits or any speciai indirect incidentai consequenti or exerplary damages howsoever even f the compery hes been achten of the possibly of such damages 168 Goex Powder Inc Material Safety Data Sheet MSDS BP Potassium Nitrate Revised 3 17 09 PRODUCT INFORMATION Black Powder RCE ETETE The prevention of accidents in the use of explosives is a result of careful planning and observence of the best known practices The explosives user must remember that he is dealing with a powerful force and that various devices and methods have been developed to assist him in directing this force He should realize that this force if misdirected may either kill or injure both him and his fellow workers All explosives are dangerous and must be carefully transported handled stored and used following proper safety procedures either by or under the direction of competent experienced persons in accordance with all applicable federal state and local laws regulations or ordinances ALWAYS lock up explosive materials and keep away from chidren and unauthorized persons If you have any questons or doubts as to how to use any explosive product DO NOT USE IT before with your supe
121. icipants engaged and actively participating 6 4 1 STEM Coordination According to the USNA STEM website the outreach methodology is to utilize unique approach to recruiting and retaining technologists by actively engaging elementary middle high school students and teachers in a wide variety of science and engineering events camps mini camps competitions site visits short courses internships to initiate interest and enthusiasm for future STEM participation in academic and career choices Unique approach is defined by project based Navy relevant curriculum focusing on current topics and a pyramidal structure with practicing Navy technologists educators on top and near peer midshipmen acting as the interface with students using the outstanding USNA resources as a backdrop for the activities Navy Rockets will supplement the mission of the STEM Program by fulfilling its own requirements The shared goals of the USNA STEM program and Navy Rockets are e Outreach with local communities to influence students and teachers to increase focus toward STEM related studies and activities e Allow Navy Rocket participants to be intellectually challenged by creating programs for Midshipmen and other program participants that will facilitate problem solving and critical thinking while still developing a basic technical sense of the projects 104 e Create an interest in aerospace specifically and all aspects of systems engineering that it en
122. ility Stable under proper handling and storage conditions Incompatible Materials None Products evolved from Heat of Combustion or Decomposition The products of combustion and decomposition depend on other materials present in the fire and the actual conditions of the fire Burning will decompose the sizing system if appropriate and produce carbon and nitrogen oxides phenols aldehydes acrolein carboxylic acid traces of incompletely burned carbon products and other unidentified gases and vapors that may be toxic Avoid inhalation Hazardous Polymerization Will not occur under proper conditions of use Rapid heating of the product in bulk may produce an uncontrolled exothermic reaction that may char and decompose the sizing system if appropriate generating unidentified gases and vapors that may be toxic Avoid inhalation Section 11 TOXICOLOGICAL INFORMATION Component Toxicity Data Median Lethal Dose Species Oral LD Not determined Inhalation LC Not determined Dermal LDso Not determined Irritation Index Estimation of Irritation Species Skin Not determined Eyes Not determined Inhalation Not determined Section 12 ECOLOGICAL INFORMATION No ecological data has been determined 151 MSDS Number 439 3227 00SU C000 12 Date October 1 2002 Page 5 of 6 Section 13 DISPOSAL CONSIDERATIONS Waste Disposal Methods Material for disposal should be placed in appropriate sealed containers to av
123. ill be placed inside the motor and launched to an altitude of 3000 feet After apogee the system will deploy a parachute and slow the vehicle down as it approaches a target altitude of 1000 feet At the target altitude the soil sample and payload section will be ejected from the main launch vehicle deploy a parachute and return to the Earth without damage 109 APPENDIX A FRR Flysheet Milestone Review Flysheet em Motor Properties Ascent Analysis Ee _ Maximum vetocity re s center ot Gravity fin from nose _ Maximum mech Number os Static staility Mersin aies Maximum Acceleration rz ses e reget apogee stage mute sages 7 ov Recovery System Properties Recovery System Properties Drogue Parachute Main Parachute LL s anno O veedetDesoymemt w veodtystDepoymentini Hamexste mimez n sso Recovery Harness tengnt w Two steel eyebolts two feet of tubular nylon Single eyedolts Black Diamond Positron Bisck Diamond Pozitron Caradineers snc one Carabineers two feet of tubuler nylon 500 Ib test barrel swivel Garmin Astro anc 3 Dog Device ARimeter s Timer s ia Make Model aes aoe The Stratologgers will be Doth connected to the biack powder charge anc have their own switch Transmitting
124. in the power class These distances are specified in a table in NFPA Code 1127 and the NAR high power safety code Motor Certification Both NAR safety codes and both NFPA Codes require that fliers use only certified motors This certification requires passing a rigorous static testing program specified in the NFPA Codes The NAR safety codes and insurance require that NAR members use only NAR certified motors and since the NAR currently has a reciprocity agreement with TRA on motor certification this means that TRA certified motors also have NAR certification The NFPA Codes recognize certifications granted by any approved testing laboratory or national user organization but only the NAR and TRA can provide this service in most parts of the country The California Fire Marshal has his own testing program for motors in that state Motors made by private individuals or by companies without proper explosives licenses and motors not formally classified for shipment by the U S Department of Transportation are not eligible for NAR certification and may not be used on an NAR range Shipping of Motors Sport rocket motors generally contain highly flammable substances such as black powder or ammonium perchlorate and are therefore considered to be hazardous materials or explosives for shipment purposes by the U S Department of Transportation DOT There are extensive regulations concerning shipment in the DOT s section of the CFR Title 49
125. increase the chance of developing allergic symptoms to this product 3 COMPOSITIONINFORMATION ON HAZARDOUS INGREDIENTS CAS amp CONCENTRATION 25085 39 8 60 100 100 516 10 30 25054 14 4 1 10 FIRST AID FOR SKIN e Remove contaminated clothing Wipe excess from skin Apply waterless skin cleaner and then wash with soap and water Consul a physician If eects occur FIRST AID FOR INHALATION Remove to fresh air If effects occur FIRST Ss No acute adverse heath effects expected from amounts Ingested under normal conditions of use Seek medical attenton If a significant amount is ingested MSDS 105 13a Last Revised 26APR13 140 West System Inc Page 2 of 4 WEST SYSTEM 105 Resin S FIRE FIGHTING MEASURES PANEM enna EN ic a 200 F Tag Closed Cup EXTINGUISHING MEDHA sss FOAM Carbon dioxide CO dry chemical SPECIAL FIRE FIGHTING PROCEDURES Wear a self contained breathing apparatus and complete full body personal protective equipment Closed containers may rupture due to bulldup of pressure when exposed to extreme heat FIRE AND EXPLOSION HAZARDS fire smoke may contain the original matenas In addition to combustion products of varying comocerion whicn may be toxic andor Inrtating Combuszon products may Include but are not to pnenoics carbon monoxide carbon dioxide 6 ACCIDENTAL RELEASE MEASURES SPILL OR LEAK PROCEDURES e
126. ined herein are furnished for information only and are believed to be reilable However Henke Corporation and Its affiliates Henkel does not assume responsiblity for any results obtained by persons over whose methods Henkel has no control It is the user s responsibility to determine the suitability of Henkel s products or any production methods mentioned herein for a particular purpose and to adopt such precautions as may be advisable for the protection of property and seme megane In light of the foregoing all warranties express or implied meluding warranties of merchantability and fitness for a purpose MEME products Henkei further disclaims any liability for consequential or Incidental damages Of any kind incsuding lost pronis IDH number 1071248 Product name Loctite Epoxy Heavy Duty Resin Page 4 of 4 157 Material Safety Data Sheet Revision Number 004 0 Issue date 12 27 2011 Product name Loctite Epoxy Heavy Duty Hardener IDH number 1137985 Product type Epoxy Hardener Item number 193468 Region United States Company address Contact Information Henkel Corporation Telephone 860 571 5100 One Henkel Way MEDICAL EMERGENCY Phone Poison Control Center Rocky Hill Connecticut 06067 1 377 671 4608 toil free or 1 303 592 1711 TRANSPORT EMERGENCY Phone CHEMTREC 1 800 424 9300 toil free or 1 703 527 3887 internet www henkeina com 2 HAZARDS IDENTIFICATION
127. ing high power rocket flight and i Unless reasonable precautions are provided to report and control a fire caused by rocket activities 101 27 ATC notification for all launches No person may operate an unmanned rocket other than a Class 1 Model Rocket unless that person gives the following information to the FAA ATC facility nearest to the place of intended operation no less than 24 hours before and no more than three days before beginning the operation a The name and address of the operator except when there are multiple participants at a single event the name and address of the person so designated as the event launch coordinator whose duties include coordination of the required launch data estimates and coordinating the launch event b Date and time the activity will begin c Radius of the affected area on the ground in nautical miles d Location of the center of the affected area in latitude and longitude coordinates e Highest affected altitude f Duration of the activity g Any other pertinent information requested by the ATC facility 101 29 Information requirements a Class 2 High Power Rockets When a Class 2 High Power Rocket requires a certificate of waiver or authorization the person planning the operation must provide the information below on each type of rocket to the FAA at least 45 days before the proposed operation The FAA may request additional information if necessary to ensure the propos
128. integrity The selection and calculation of the Shall deliver the vehicle to the motor size and manufacturer to meet prescribed altitude and provide the Propulsion the flight requirements based on the vehicle design 3 1 4 Flight Profile initial phase of the recovery system in a controlled manner The rocket will follow a planned flight path This path will include apogee at 3000 feet and deployment of the drogue and payload at 1000 feet The flight plan can be seen in Figure 1 16 3 Rocket reaches apogee splits the main body from the avionics bay and deploys the drouge chute 2 Rocket accelerates j toapogee 4 Rocket descends to 1000 ft AGL jettisons the nose cone and Payload section together deploying two main parachutes for the two separated sections 1 Rocket launches Figure 1 Flight Profile 3 2 Design and Construction The rocket is 5 inches in diameter and 108 inches long made from both carbon fiber and fiberglass The entire structure has a constant thickness of 0 08 inches thick The nose cone and avionics section shown in Figure 2 hold electronic equipment and is made from fiberglass and high strength honeycomb foam The nose cone is 26 inches long shown in Figure 3 and will 17 hold the payload section s GPS and cover the sample payload The avionics section will hold the main body s GPS and altimeters Payload Payload Rocket Drogue Avionics Compartment Main Chu
129. inting Integration and Test Flow 117 Setup Test Parts Mission Readiness Review 2 Injector System Functional Test 2 1 Objectives The objective of this experiment is to analyze the aerodynamic stability of the rocket used for the NASA Student Launch competition 2 2 Criteria for Success The rocket shows static and dynamic stability at all Reynolds numbers tested at Forces and moments will be taken into account when analyzing stability The location of the center of pressure Cp matches that from simulation software OpenRocket 2 3 Facilities The scale model testing will be performed using the Eiffel Wind Tunnel in Rickover hall at USNA 2 4 Materials A 48 9 in scale model rocket 64 sections surgical tubing 1 16 in diameter B C 64 stainless steel surgical tubing connectors D 1 Pressure Systems pressure gage cluster 64 ports 2 5 Test Overview The test will involve turning the wind tunnel on while all pressure ports are connected TEST DATE TEST PERSON Initial Rocket Model Test Done Step Description Comment Y N Date Initial 0 Attach pressure tube to each port on the bottom of the nose cone through the inside of the rocket Attach tygon tubing through access holes in PVC 1 Attach scale model aft section to the sting balance 2 Run surgical tube through the sting balance attachment out to the pressure gages 3 Ensure sting balance is properly
130. ion areas upon approval of the RSO 2 6 2 An Invited Guest may be allowed the High Power Launch Area if escorted by a HPR Flier A HPR Flier may escort and be accompanied by not more than five 5 non HPR fliers in the High Power Launch Area The HPR flier escort is required to monitor the actions of the escorted non HPR fliers and the escort is fully responsible for those actions and for the safety of those escorted 2 6 3 Spectators who are not invited guests shall confine themselves to the spectator areas as designated by the RSO and shall not be present in the High Power Launch Area or Model Rocket Launch Area Referenced Publications The following documents or portions thereof are referenced within this code The edition indicated for each reference 15 the currentedition as ofthe date of the NFPA issuance of this document 3 1 NFPA Publications National Fire Protection Association I Batterymarch Park PO Box 9101 Quincy 02269 9101 NFPA 1122 Code for Model Rocketry NFPA 1125 Code for the Manufacture of Model Rocket Motors NFPA 1127 Code for High Power Rocketry 3 2 Government Publications Superintendent of Documents U S Government Printing Office Washington DC 20402 Federal Aviation Administration Regulations from the Code of Federal Regulations Federal 7 31 2012 131 Hazardous Substances Act from the United States Code re Airspace Control 3 3 TRA Publications Tripoli Rocketry Association Inc
131. ion to ease circumstances at ending damage competition to separation deployment altitude determine best connecting process and configuration 91 Parachute separates from rocket Altimeter fails to work Stability margin is too small Structural failure Payload section fails to close Poor packing damage on launch environmental circumstances at deployment altitude Rocket falls uncontrollably potentially causing project ending damage Ensure parachute is packed properly ensure separation works before competition test repeatedly before competition to determine best Parachute packed cautiously and under supervision packing configuration Not enough Rocket will not Redundant Learned from power or faulty deploy systems are previous wiring systems parachutes at the utilized in order altimeter proper altitude to ensure the failures and altimeters implemented function new methods properly to ensure proper use based on prior failures The CG shifts too The stability of Ensuring that the Weight close to the CP the rocket weight balance is balance double from bottom decreased which correct and checked prior loading the can harm the verified with to launch rocket flight path and Open Rocket performance data A defect during The rocket will Careful Rocket the building process or potential damage during launch operations not
132. ional Association of Rocketry NAR Tripoli Rocketry Association TRA and or the Canadian Association of Rocketry CAR Propulsion 19 1 Final motor choices must be made by the Critical Design Review CDR Propulsion 1 9 2 Any motor changes after CDR must be approved by the NASA Range Safety Officer RSO and will only be approved if the change is for the sole purpose of increasing the safety margin Propulsion 1 10 The total impulse provided by a launch vehicle shall not exceed 5 120 Newton seconds L class Propulsion Any team participating in Maxi MAV will be required to provide an inert or replicated version of their motor matching in both size and weight to their launch day motor This motor will be used during the LRR to ensure the igniter installer will work with the competition motor on launch day Propulsion Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria Structures 1 12 1 The minimum factor of safety Burst or Ultimate pressure versus Max Expected Operating Pressure shall be 4 1 with supporting design documentation included in all milestone reviews Structures 12 2 The low cycle fatigue life shall be a minimum of 4 1 Structures 12 3 Each pressure vessel shall include a solenoid pressure relief valve that sees the full pressure of the tank Structures 1 12 4 Full pedigree of the tank shall
133. irs 2 and 3 are the dedicated ejection event terminals Terminal pair 2 powers Ejection Event 1 at the default apogee setting and terminal pair 3 initiates Ejection Event 2 at the programmed height of 1000 feet AGL Stratologger B is programmed at staggered altitudes to provide a redundant system in the event that Stratologger A fails to properly separate the appropriate sections Stratologger B s altitudes are programmed for Apogee 3 sec for Event 1 and 900 feet AGL for event 2 Terminal 1 is used to supply battery voltage readings to either a beeper amplifier or an LED The REPTAR launch vehicle will use the terminal to light two through the wall LED s as a confirmation that power has indeed been supplied to both Stratologgers The ejection charges used will be PVC tubes that have been secured to the bulkheads around the avionics section as shown in Figure 24 This design allows for the black powder to be poured into the tubes and then covered by metal tape in order for quick and safe reuse of the charges Figure 24 Ejection Canisters on Avionics Section 40 This however will be more than enough capacity To determine a rough estimate on the amount of black powder needed Equation 1 can be used Black Powder 0 006 Dcompartment in compartment in Equation 1 Using this equation the compartment parameters in Table 8 and a margin of error of 150 to slightly overestimate the pressurization force the amount of black po
134. l causing other toxic effects E Corrosive CEPA Chemical Inventory Statue s All components are listed or are omeratse compilant with CEPA requirements SARA TITLE Ill SECTION 313 TOXIC CHEMICALS e THIS product contains mydroxybenzene phenol and is subject to the reporting requirements of Section 313 of Tite Ill of the Superfund Amendments and Reauthorization Act of 1986 and 40 CFR Part 372 STATE REGULATORY INFORMATION The following chemicals are spectically listed or otherwise regulated by individual states For detalis on your regulatory requirements you should contact the appropriate agency in your state COMPONENT NAME ICAS NUMBER CONCENTRATION STATE CODE Teraetnylenepentamine 112 57 2 MA NJ PA Tetraethylenetrramine 112 24 3 MA NJ PA Phenol 1086 95 2 NJ RI PA MA IL odi This information is furnished without warranty expressed or impiled except that It is accurate to the best knowledge of West System Inc The data inis sheet related to specife materiai designated herein West System Inc assumes no legal responsibilty for use or relance upon these MSDS 205 13a Last Revised 26APR13 147 Material Safety Data Sheet Section 1 PRODUCT AND COMPANY IDENTIFICATION MSDS Identification Carbon Fabric Sized or Unsized MSDS Number 439 3227 00SU C000 12 Date October 1 2002 Page
135. la a22e E2II8A Aj20Ja 0 10 20 30 40 50 60 70 80 90 100 Time s Altitude ft Vertical velocity 5 Vertical acceleration ft s7 Figure 29 K1200 Vertical Motion vs Time The K600 motor reaches 2 997 feet 3 feet below the required altitude of 3 000 feet However the desired margin of error of 100 feet makes choosing this motor too risky based on unforeseen weight and drag that will occur on the day of the launch The second motor K750 17 reached 3 534 feet in the simulation This is above the desired altitude of 3 100 feet by 434 feet This would be too great of a deduction to the final grade to justify having that much excess height in order to guarantee reaching 3 000 feet on launch day It would also be a safety risk and exceed the altitude requirement The last motor the K1200WT 16 was chosen because it reached close to the desired height with an apogee of 3 068 feet only 32 feet under the desired altitude of 3 100 feet It also has a given total impulse of 2011 N s After selecting the K1200 motor based on altitude calculations competition thrust requirements were considered Using Figure 30 below a maximum thrust of approximately 1 350 N was determined This value will be essential in developing a motor mount to sustain this force Due to the predicted performance of the K1200 motor it will be used in the final rocket design 46 Motor bumout 1 750 1 500 1
136. lass Woven Cloth SCHEDULE B NUMBER 7019 52 0000 SECTION II HAZARDOUS INGREDIENTS INGREDIENTS WGT CAS TLV PEL Fibrous Glass 98 09 05 65997 17 3 Respirable PEL 5 mg m Respirable ACGIH TLV 1 mg m Organic Bound Silanes lt 0 4 Supplier N A Trade Secret SECTION III PHYSICAL DATA APPEARANCE White to off white fibers SPECIFIC GRAVITY 2 5 VAPOR PRESSURE mmHG N Av BOILING POINT NE VAPOR DENSITY N ap EVAPORATION RATE Ethyl Ether 1 N Av VOLATILES BY WEIGHT None SOLUBILITY IN WATER Insoluble VOC Grams Liter None Lbs Gallon None 175 PAGE 2 of 4 Fiberglass Cloth SECTION IV FIRE AND EXPLOSION DATA FLASH POINT Non burning LOWER FLAMMABLE LIMIT N Av UPPER FLAMMABLE LIMIT N Av FIRE EXTINGUISHING MEDIA Carbon Dioxide Dry Chemical Foam SPECIAL FIRE FIGHTING PROCEDURES None known Use SCBA UNUSUAL FIRE AND EXPLOSION HAZARD None known SECTION V HEALTH HAZARD TOXICOLOGICAL PROPERTIES OVEREXPOSURE EFFECTS ACUTE EFFECTS EYES Contact with eyes can cause irritation redness tearing blurred vision and or swelling SKIN Contact with skin can cause irritation minor itching burning and or redness Dermatitis INHALATION Inhalation of dust can cause respiratory tract and lung irritation INGESTION Ingestion can cause gastrointestinal irritation nausea CHRONIC EFFECTS Overexposure to this material has apparently been known to cause the following effects in lab animals None k
137. litate rotation Middle three rungs are welded into place for maximum stability 5 The Scorbot shield has been removed from the design 6 Number of tests for everything has been reduced to 10 iterations with the exception of the Scorbot with a dummy payload and dummy payload bay The number of repetitions required before these changes were excessive and time consuming 2 3 Project Plan No plans have changed since CDR 2 4 Suggested Changes An additional switch was added to the avionics section to ensure redundant systems while controlling the altimeters 14 3 Vehicle Criteria 3 1 Launch Vehicle 3 1 1 Requirements The key requirements in this year s NASA Student Launch competition are as follows o Launch Vehicle Payload Sample Containment System Active GPS tracking Launch to 3000 feet AGL Jettison payload section at 1000 feet AGL Return both sections to ground with under 75 ft lb KE o Autonomous Ground Support Equipment AGSE Retrieve sample and place inside horizontal launch vehicle Erect launch vehicle to 5 from vertical Insert electronic igniter into motor Include pause function No human interaction or commands sent once process begins o Neither deliverable may cost over 5 000 for a total of 10 000 3 1 2 Vehicle Success Criteria In order for this year s REPTAR project to be a success Navy Rockets will deliver an autonomous ground support element capable of loading the specified payload into a rocket
138. ll instance of damage occurred to the rocket On the bottom coupler of the jettisoned payload section a small crack was developed By inspection it was due to the carabineer hitting the side of the coupler on ejection Navy Rockets does not feel that this damage was very critical because the coupler still worked properly in connecting to the next section To fix this problem however a thick PVC pipe was lathed down in order to fit the inner diameter of the coupler and was then epoxied into place thus greatly increasing the thickness of the coupler A change after the full scale launch is that the altimeters will be set to go off at different locations During the full scale launch the altimeters were set to both go off at apogee which caused a large explosion of black powder The new way is to have the altimeters deploy at apogee and then three seconds after apogee to ensure that the redundant system is effective for the flight 3 2 5 Workmanship Precision measurement and manufacturing techniques were used to properly construct the rocket Attention to detail and team supervision was used to ensure each part is correctly manufactured in the same way It was a team effort to build and assemble the rocket properly for launch 3 2 6 Safety and Failure Analysis The failure modes for the launch vehicle are presented below in Table 3 Table 3 Launch Vehicle Failure Modes Failure Mode Cause Likelihood Severity Miti
139. ll operations Personnel unknowingly approach the tower Lights on the tower clearly indicate the while it is powered on and igniter is state of the system warning any personnel inserted Conforming strictly to launch procedures will also mitigate this risk 4 7 3 Environmental Concerns The AGSE does not pose a threat to the environment so long as all components are retrieved after launch The stakes used will not damage the soil beneath the system All necessary precautions will be taken to ensure that any lubricant used does not spill onto the soil 81 5 Launch Operations 5 1 REPTAR Checklists 5 1 1 Pre flight Brief Before any rocket launch Navy Rockets will go over the Pre flight Brief This brief will be given by the Safety Officer and will discuss the flight plan and any concerns that arise that day 1 Launch Overview a Motor Selection b Launch Goals c Predicted Outcomes d Avionics Test 2 Weather a Launch Concerns 3 Rocket Performance a Weight b Predicted Altitude 4 Flight Conduct a Drogue Deployment b Main Deployment c Tracking Systems 5 Safety a IMSAFE Concerns b ORM Concerns c Safety Concerns 6 Emergencies a General Emergencies b Hazards and Mitigation c Emergency Contact a Location Rules b Launch Check 82 5 1 2 Recovery Preparation aS dx e O RE Lay out all parachute and recovery harness lines Inspect harness elements to ensure no tangles twist
140. ll ventilated area away from heat sparks and open flame Keep container tightly closed until ready for use For Information on product shelf life contact Henkel Customer Service at 800 243 4874 IDH number 1137985 Product name Loctite Epoxy Heavy Duty Hardener 159 8 EXPOSURE CONTROLS PERSONAL PROTECTION assessment to determine the 4 selection pina nba P need for and of proper exposure Eai E Use local ventilation general ventilation 15 Insufficient to maintain vapor concentration below established exposure limits Respiratory protection Use a NIOSH approved air purifying respirator If the potential to exceed established exposure limis exists Eyerface protection Safety goggles or safety glasses with side shields Skin protection Chemical resistant impermeable gloves 9 PHYSICAL AND CHEMICAL PROPERTIES Physical state Liquid Color Amber Clear Odor Amine Mercaptan Odor threshold Not avaliable pH Not available Vapor pressure Not avaliable Not avaliable Melting point range Not available Specific gravity 1 04 Vapor density Not available Flash point gt 93 gt 199 4 F Tagiabue closed cup Flammable E xplosive limits lower Not available EET Not available Solubility In water soluble Partition coefficient n octanol water Not avallabie VOC content 0 38 3 7 01 EPA Method 24 10 STABILITY AND REACTIVITY Stability Staple Hazar
141. lly not hazardous MSDS for nonwovens is not legally requested but must be considered as information It is inspired from the EC recommendation for MSDS EC 1907 2006 1 Identification of the product and the company 1 1 Identification of the product s Product name Lantor Soric XF Product Code XF1002 XF1003 XF1004 XF1005 XF1006 Product name Lantor Soric SF Product Code SF1002 SF1003 Product name Lantor Soric TF Product Code TF1015 TF1002 TF1003 Product name Lantor Soric LRC Product Code LRC115 LRC102 LRC103 1 2 Intended use of the product Liner core material in FRP applications 1 3 Company identification Lantor BV Lantor Ferdi Box 45 NL 3900 AA Veenendaal The Netherlands Phone number 31 0 318 537111 Fax number 31 0 318 537399 Department person responsible for the product safety Name Lantor B V Composites P O Box 45 NL 3900 AA Veenendaal The Netherlands Phone number 31 0 318 537111 31 0 318 537420 identification No hazardous product under normal conditions Accidental thermal decomposition or melting state can present hazards pues of Es customers and to the with respec e released from Ais duty to check safety retevaot properties of the caf obfigarbas by ONS Mariy Saer 181 2108 Material Safety Data Sheet according to Directive EC 1907 2006 Revision 21 11 11 Page 2 of 3 Product
142. ltitude the team will lose 1 altitude point The team s altitude points will be divided by 3 000 to determine the altitude score for the competition The official scoring altimeter shall report the official competition 1 2 1 altitude via a series of beeps to be checked after the competition Avionics flight Teams may have additional altimeters to control vehicle Avionics amp 122 electronics and payload experiment s Recovery 1221 At the Launch Readiness Review a NASA official will mark the NEM altimeter that will be used for the official scoring At the launch field a NASA official will obtain the altitude by 1 2 2 2 listening to the audible beeps reported by the official competition Avionics marked altimeter At the launch field to aid in determination of the vehicle s apogee 1 2 2 3 all audible electronics except for the official altitude determining Avionics altimeter shall be capable of being turned off The following circumstances will warrant a score of zero for the ee 12 3 i Avionics altitude portion of the competition The official marked altimeter is damaged and or does not report 1 2 3 1 ns Avionics an altitude via a series of beeps after the team s competition flight The team does not report to the NASA official designated to 1 2 3 2 record the altitude with their official marked altimeter on the day Avionics of the launch 1 2 3 3 The altimeter reports an apogee altitud
143. maintaining a low packing volume and weight These rip stop nylon parachutes will slow the main body and payload sections down to 14 45 ft sec and 14 58 ft s respectively which projects them to land well within the prescribed 75 ft lbf limit Calculations for the sizing and descent speeds are further discussed in Section 3 6 5 3 4 3 Electrical Elements The recovery system will utilize two identical flight altimeters to operate the launch vehicle s recovery system The PerfectFlite Stratologger SL100 is flight heritage hardware with Navy Rockets and continues to produce accurate expected results The REPTAR system will use two for redundancy of the ejection events A full schematic of the recovery electronics can be seen in Figure 23 f f LED1 Ejection Event 2 f Ejj Arming Switch 1 96008 T LED2 Arming Switch 2 an D 00088 9 V Source 9 V Source Ejection Event 1 0 g Figure 23 Recovery Electronics Schematic The SL100 offers 10 total terminals to be used for various applications The launch vehicle uses 9 of the 10 for both altimeters Two of the terminals terminal 5 are dedicated to the 9 volt power source Two more terminal 4 are dedicated to an arming switch that runs in series 39 between the ejection event terminals and the power source These dedicated arming switches provide through the wall capability to power and arm the recovery system Terminal pa
144. meable gloves IDH number 1071248 Product name Loctite Epoxy Heavy Duty Resin Page 2 of 4 155 9 PHYSICAL AND CHEMICAL PROPERTIES Physical state Color Transiucent Clear Odor None Odor threshold Not avaliable pH Not available Vapor pressure 0 03 mm hg Bolling point range 2602 C 500 4 F Specific gravity i tU Vapor density Not avaliable Flash point gt 249 gt 4802 F Pensky Martens closed cup Flammable Explosive limits lower Not avaliable temperature g Nol E Not avaliable Not avaliable Solubility In water E Partition coefficient n octanol water Nol antite VOC content 0 10 value for resin and hardener together 10 STABILITY AND REACTIVITY Stability Stable Hazardous reactions Will not occur Hazardous decomposition products None Incompatibie materials Strong oxidizing agents Strong bases Strong acids Amines Conditions to avold Excessive heat Store away trom Incompatible materials 11 TOXICOLOGICAL INFORMATION Dicnioronyd dir 12 ECOLOGICAL INFORMATION Ecological Information Not avaliable 13 DISPOSAL CONSIDERATIONS Information provided is for unused product only Recommended method of disposal Follow all local state federal and provincial regulations for disposal Hazardous waste number Not RCRA hazardous waste 14 TRANSPORT INFORMATION us ot Ground Proper shipping name Not regulated Hazard cla
145. ment System as seen in Table 2 The system allows the two materials to be tested on important characteristics for the project Each characteristic has a weighting of importance for the project a one weighting represents little importance to the project a three weighting represents medium importance and a nine weighting means that it is critical to the project This weighting allows the important factors to outweigh less desired characteristics If the material agreed with the material factor it was given a positive weighting score If the material completely disagreed it was given a negative weight score A score of zero was given when the material met the requirements but did not standout against the other Table 2 Material QFD Material Factors Weighting Carbon Fiber Fiberglass Factor NAT NES ad 3 3 3 3 E IUE ood or EE E od Carbon fiber was selected for its superior material strength low weight and relatively high availability Although the cost of carbon fiber was significantly higher than alternative materials such as fiberglass and cardboard the cost difference was not significant enough to push the design out of budget Due to the low density of carbon fiber the dimensions of the rocket were able to be greatly reduced as well as the motor size required to push the rocket to 3 000 feet in altitud
146. n 4 843 in Dia 0 315m Diasa 0 394 in Dia 0 315 in 0 394 in Thick 0 118 in 113 Len 0 079 in Len 0 5 in Len 37 in Len 26 in Len 180 in Len 1 5 in Len 24 in Len 0 125 in Len 0 197 in Len 0 125 in Len 1 181 in Len 1 181 in Mass 0 097 lb Mass 0 lb Mass 3 1 Ib Mass 0 222 lb Mass 0 161 Ib Mass 0 172 lb Mass 0 092 Ib Mass 0 lb Mass 0 092 Ib Mass 0 003 Ib Mass 0 003 Ib Mass 1 44 lb APPENDIX Wind Tunnel Test Plan USNA ROCKET PROPULSION PROGRAM FUNCTIONAL TEST PLAN USNA TP R001 20 AUG 2014 Approvals Project Engineer Date 114 RECORD OF CHANGES REVISION DATE TITLE OR BRIEF DESCRIPTION ENTERED BY LETTER A 20 SEP 14 Draft TM B 9 JAN 14 Draft TM 115 Introduction This Functional Test Plan describes the procedures used to operate the flow aerodynamic force test being performed on the University Student Launch Initiative USLI scale rocket in the Eiffel Wind Tunnel Pressure Variation along Rocket The purpose of this experiment is to test a scale model rocket at an array of incidence angles with varying Reynolds numbers This test will allow Navy Rockets to determine the aerodynamic forces present on the rocket throughout the flight Knowledge of the forces during flight will give way to more accurate analysis of rocket flight path trajectory especially in comparison to rocket trajectory simulatio
147. n 6 4 3 3 Girls Only STEM Day Part of the Girls Exploring Technology through Innovative Topics GET IT and go Program the girls only STEM day focuses on engineering design and development through a comprehensive competition The goal is to encourage female participation in STEM programs and studies because females are under represented in STEM communities At the competition female students will have the opportunity to compete and to attend workshops and meet female faculty members working on innovative technologies and sciences The girls only STEM day is a one time competition of the GET IT and GO Program 6 4 3 4 Space Exploration Merit Badge In conjunction with the National Eagle Scout Association NESA chapter at the Naval Academy Navy Rockets will counsel groups of Boy Scouts to achieve the Space Exploration Merit Badge on Martin Luther King weekend in January of 2015 The merit badge involves instruction about Newton s Laws model rocketry and much more The complete requirements for the badge can be found on the Boy Scouts of America s BSA website 6 4 4 Sustainability Because it is the first year in the competition for Navy Rockets extra measures will be taken in order to sustain the project for years to come While it is difficult for Navy Rockets to receive funding through commercial enterprises and other businesses the team is continually lobbying for community support in other areas Outside of the Student Launc
148. n as to not interfere with AGSE communications link Power issues or the interfaces are not working properly Cause failure of competition Test the igniter system to ensure that it functions properly 5 2 4 Personnel Hazards During the Student Launch Project potential hazards could and have developed These hazards and mitigations can be found in Tables 21 22 94 Table 21 Hazard Analysis for the Student Launch Project Hazard ORM Cause Effect Mitigation Verification Value Launch Rocket fails Faulty Rocket cannot Repeatedly test to be coding faulty be launched rocket erection prior erected motor power to competition so as source error not to have any issues etc on launch day Perhaps compose a checklist to ensure no important steps are forgotten Rocket fails Motor issues Rocket cannot Repeatedly test Stand to leave the power issues be launched launch procedures thoroughly stand prior to competition checked before so as not to have any launch issues on launch day Perhaps compose a checklist to ensure no important steps are forgotten Igniter fails Igniter issues Rocket cannot Repeatedly test Igniter to ignite motor issues be launched motors prior to placement motor power issues competition so as not double checked to have any issues on before launch launch day Perhaps compose a checklist to ensure no important steps are forgotten Catast
149. n software This work will be presented to complement the Navy Rocket research and development as a part of the NASA Student Launch competition 11 Philosophy of OPERATIONS The scale model testing will take place inside the Eiffel Wind Tunnel in Rickover Hall It will be mounted to the sting balance with pressure ports located along the nose cone and rocket body The nose cone and the fin section will be designed in Solid Works and 3D printed to an exact 0 475 1 scale The pressure ports will be 3D printed into the scale model nose cone and drilled into the body section The body section will be made of PVC The model will be run at varying Reynolds numbers The incidence angle of the scale model and the free stream flow will vary between 10 and 10 degrees 1 2 Participation Personnel responsible for the operations are listed in A 1 C 1 Wind Tunnel Test Personnel Name Organization Role Responsibility Contact Information USNA Aerospace Engineering Project Manager Instructor USAF 410 293 6403 clarkk usna edu Captain Kristen Castonguay USLI Aerodynamics 15471 T Troy McKenzie USNA Class of 2015 Lead m154716 usna edu 116 1 3 Flow Diagrams The Additive Printing integration and test flow is shown below Nose Cone Fin Nose Cone Section Printed Scale Designed Model Made Test Readiness Review Take Pictures of Flow Obtain Results Operations Perform Functional Test Additive Pr
150. nches It will also address some aspects of safe rocket design and construction as well as limitations of motor power for use by the certified user for education recreation and sporting use 1 2 Purpose 1 2 1 The purpose of this code shall be to establish guidelines for reasonably safe operation of high power rocket at Tripoli sanctioned insured launches both commercial as well as Research covered in a separate code 1 3 Definitions For the purposes of this code the following terms shall be defined as stated in this section Some of these may be redundant from NFPA 1127 High Power Rocket Flier HPR Flier A TRA member or a member of an approved insured rocketry organization that 15 18 years old or older Launch Director LD A Level 2 or Level 3 flier who has overall administrative responsibility for the launch Named Insured Individuals that are not Tripoli Members but are members of groups that have been submitted to and approved by the Tripoli Insurance Liaison Participants Persons that are either 7 31 2012 129 HPR Fliers Model Rocket Fliers Invited Guests of fliers Spectators General population of non fliers and non invited guests Range Safety Officer RSO A Level 2 or Level 3 flier whose responsibility and duty during the operation of high power rockets is to confirm a rocket s compliance with the applicable provisions of this code be confident that the rocket will fly m a safe manner designat
151. nd conduct flights from the High Power Launch Area and or Model Rocket Launch Area Non Inpol Members age 18 and over that are students of an accredited educational institution may participate in joint projects with Tripoli members These individuals are dicimns Bon eis Mida Wicked A a Tripoli member The maximum number of non member participant shall not exceed five 5 per Tripoli Member Non Tnpoli Members that are members of Named Insured Group may participate in joint projects with Tnpoli members These individuals are allowed m the High Power Launch Area and or Model Rocket Launch Area if escorted by Tripoli member The maximum number of non member participants shall not exceed five 5 per Tnpoli Member Tripoli Junior Members that have successfully completed the Tripoli Mentoring Program Traming may access and conduct flights from the High Power Launch Area while under the direct supervision of a Tripoli Senior member in accordance with the rules of the Tripoli Mentored Flying program The Tripoli Senior member may provide supervision for up to five 5 individuals that have successfully completed the Tripoli Mentoring Program Training at a time in the High Power Launch Area Children younger than 18 years of age may conduct flights from the Model Rocket Launch rea under the direction of a HPR Fher Attendance by Invited Guests and Spectators 2 6 1 An invited guest may be permitted in the Model Rocket Launch Area and preparat
152. ng Fire to extreme heat may cause ignition Fire During a fire irritating and highly toxic gases may be generated by thermal decomposition or combustion Fire Fighting Procedures Keep persons and hazardous materials away Allow material io burn Itself out As in any fire wear a self contained breathing apparatus in pressure demand MSHA NIOSH approved or equivalent and ful protective gear Special Instructions Notes These articles burn rapidly and generate a significant frame for a short period of time Black powder is a defiagrating explosive It is very sensitive to flame and spark and can also be ignited by friction and Impact Vinen ignited unconfined it burns with explosive violence and will explode If ignited under even slight confinement Do not Inhale exhaust products 6 0 ACCIDENTAL RELEASE MEASURES Safeguards Personnel Spills Clean up spills Immediately Replace articies In packaging and boxes and seal securely Sweep or scoop up using non sparking tools 79 HANDLING AND STORAGE Handling Keep away from heat sparks and flame Avold contamination Do not get eyes on skin or on clothing Do not taste or swallow Avoid prolonged or repeated contact with skin Follow manufacturer s Instructions for use 164 MSDS ProX Rocket Motor Reload Kits Page 36 Version 202 Faresice Date Feb 2010 Storage Store a cool dry place away from sources of heat spark or flame Keep In shipping packaging when
153. niter Insertion First attempt 4 1 4 AGSE Experimental Approach The process of designing programming and testing each subsystem individually before integrating them into the overall system provides the benefit of being able to ensure that all criteria are met By having a single subsystem responsible for its own stage in the overall sequence the process can be observed and altered as needed For example if it is determined that the Scorbot is drawing too much power from the source during the payload insertion sequence the programming can be altered so motion is only occurring on one axis at a time thereby decreasing energy consumption Using a single master code to control all subsystems will enables monitoring of the status of each subsystem as it runs as well as the status of the AGSE as a whole unit 4 1 5 Variable Control The process of designing programming and testing each subsystem individually before integrating them into the overall system provides the benefit of being able to ensure that all criteria are met By having a single subsystem responsible for its own stage in the overall sequence the process can be observed and altered as needed For example if it is determined 65 that the Scorbot is drawing too much power from the source during the payload insertion sequence the programming can be altered so motion is only occurring on one axis at a time thereby decreasing energy consumption Using a single master code to co
154. nmental Could alter Monitor weather Monitored temperature causes performance of forecast forecast rocket engine establish cutoff cause temperature components to overheat High Environmental Could decrease Monitor weather Monitored humidity causes performance of forecast be forecast rocket engine aware of due to density of potential air harmful effects of humidity Very low Environmental Could alter Monitor weather Monitored temperature causes performance of forecast forecast rocket engine establish cutoff cause temperature components to freeze 97 High winds Fog Pressure Delay launch Monitor wind Monitored differentials of scrub launch conditions prior forecast Earth s make rocket fly to launch atmosphere out of establish a hard recoverable cutoff wind range make limit that will rocket crash delay a launch knock rocket Always be over on stand aware of wind direction and velocity for recovery purposes Delay launch Monitor fog Monitored forecast Water vapor condenses at dew point temperature scrub launch make it difficult to track rocket in the air after launch conditions prior to launch as well as predicted conditions during the window of flight time If or scrub the fog will causes an issue delay launch 98 Table 24 Rocket Impact on the Environment Hazard ORM Value Cause Effect Mitigation Verification
155. nown CARCINOGEN YES NO TERATOGEN YES NO MUTAGEN YES NO d ROUTES OF EXPOSURE inhalation skin FIRST AID INHALATION If inhaled remove victim from exposure to a well ventilated area Make them comfortably warm but not hot Use oxygen or artificial respiration as required Consult a physician SKIN For skin contact wash promptly with soap and excess water EYES For eye contact flush promptly with excess water for at least fifteen minutes Consult a physician INGESTION If ingested do not induce vomiting Give victim a glass of water Call a physician 176 PAGE 3 of 4 Fiberglass Cloth SECTION V I REACTIVITY DATA STABILITY Stable CONDITIONS TO AVOID None known INCOMPATIBILITY MATERIALS TO AVOID None known HAZARDOUS DECOMPOSITION PRODUCTS None Known HAZARDOUS POLYMERIZATION Will not occur SECTION SPILL AND DISPOSAL PROCEDURE SPILLS LEAK OR RELEASE Sweep up remains manually or mechanically WASTE DISPOSAL Dispose of in accordance with local state and federal regulations SECTION PROTECTION INFORMATION RESPIRATORY PROTECTION If component TLV limits are exceeded use NIOSH MSHA approved respirator to remove contaminants VENTILATION Use adequate ventilation in volume and pattern to keep TLV PEL below recommended levels PROTECTIVE GLOVES Use of gloves to prevent irritation EYE PROTECTION Safety Glasses or goggles with splash guards or side shields OTHER PROTECTIVE EQUIPMENT Wear pro
156. ns of black powder bum very slowly measurable in seconds per foot Confined as in steel pipe speeds of explosions have been timed at values from 560 feet per second for very coarse granulations to 2 070 feet per second for the finer granulations Confinement and granulation will affect the values CHEMICAL DECOMPOSITION Use water to dissolve the potassium nitrate coepi eh sari the residue of sulfur and charcoal is non explosive ible when d SPECIAL REQUIREMENTS Black Powder is very sensitive to flame and spark and can also be ignited by friction and impact When ignited unconfined it burns with explosive violence and will explode if ignited under even slight confinement When dry it is compatible with most metals However 1 is hydroscopic and when wet attacks all common metals except stainless steel CAUTION Explosives must be tested for compatibility with any material not specified in the production procurement package with which they may come in contact Materials include other explosives solvents adhesives metals plastics paints cleaning compounds floor and table coverings packing menie and other similar materials situations and equipment Explosives includ ellants echnics 173 Product ProFire Igniter Synonyms Igniter initiator Proper Shipping Name Igniters Part Number INI 150 Product Use Igniter for solid fuel rocket motor Manufacturer Cesaroni Technology Inc P O Box 246 2561 Stouff
157. nsions must be free of tall trees power lines buildings and dry brush and grass The launcher can be anywhere on this site and the site can include roads Site dimensions are not tied to the expected altitude of the rockets flights According to the high power safety code high power rocket launch sites must be free of these same obstructions and within them the launcher must be located least 1500 feet from any occupied building and at least one quarter of the expected altitude from any boundary of the site NFPA Code 1127 establishes further requirements for the high power site it must contain no occupied buildings or highways on which traffic exceeds 10 vehicles per hour and the site must have a minimum dimension no less than either half the maximum expected rocket altitude or 1500 feet whichever is greater or it must comply with a table of minimum site dimensions from NFPA 1127 and the high power safety code While model rocketry and high power rocketry when conducted in accordance with the NAR Safety Codes are legal activities in all 50 states some states impose specific restrictions on the activity California being the worst example of this and many local jurisdictions require some form of either notification or prior approval of the fire marshal It is prudent and highly recommended that before you commit to a launch site you meet with the fire marshal having jurisdiction over the site to make him aware of what you plan
158. nting of components within the payload section as necessary 3 9 3 Housing Integrity The housing within the launch vehicle payload section for the standardized payload sample is made of a thin fiberglass sheet approximately 1 16 of an inch thick This housing shown below in Figure 39 is essentially a box without a lid with interior dimensions of 5 25 inches by 1 5 inches by 1 5 inches 62 Figure 39 Payload Housing This fiberglass housing provides sufficient strength while remaining lightweight Its function is to secure and protect the payload sample throughout launch and flight Its functionality has been proven through testing using a payload section mock up 63 4 AGSE Criteria 4 1 Science Value 4 1 1 AGSE Objectives The Autonomous Ground Support Equipment is responsible for the insertion of the payload into the rocket as well as the placement of the rocket in the proper launch configuration The entire sequence will be activated remotely and will have a pause function in place for safety reasons The AGSE shall be able to remain paused for at least one hour and still be able to complete its tasks once the pause ends The primary goal of the AGSE is to create a sample recovery system suitable for use on Mars The ability to retrieve Martian samples and study them in a laboratory environment on Earth will greatly increase our understanding of Mars The design of the AGSE is compatible for use on Mars because there are no
159. ntrol all subsystems will enables monitoring of the status of each subsystem as it runs as well as the status of the AGSE as a whole unit 4 2 AGSE Design 4 2 1 Tower Structure The AGSE Tower is composed almost entirely of aluminum and stands approximately 14 feet tall The tower structure mimics a ladder design and incorporates two four pronged feet to make it a free standing structure The feet and the vertical components of the tower are composed of 2x2 inch square tubing The rungs are made of 1 inch OD aluminum round tubing Each foot has four horizontal segments and one vertical component all welded at 90 degree angles The vertical component of each foot serves as fixing point for rung 1 which serves as a drive shaft This rung will be held in place by two flange bearings that have been bolted onto the vertical components of the tower feet The horizontal segments of the tower feet form a cross to maximize stability in all directions The tower foot design is displayed below in Figure 40 Figure 40 Tower Foot with Milled Coupler and Flange Bearing 66 The vertical portion of the tower is divided into two separate pieces the lower piece and the upper piece The lower piece is composed of two vertical pieces of 2x2 aluminum tubing as well as two rungs welded into place The lower piece is connected to the feet by placing it onto a pair of couplers that are made from aluminum stock that has been milled down to fit within the square
160. ny tual may be beaten in and une of any Henkes peasants ae the foregoing Henkel specificaly disciaims all warranties express or Impiled including warranties of merchantability and fitness for a particular purpose arising from any kind Including lost profits IDH number 1137985 Product name Loctite Epoxy Heavy Duty Hardener Page 5 of 5 162 MSDS ProX Rocket Motor Reload Kits Page 1 6 Venien 202 ProX Rocket Motor Reload Kits amp Fuel Grains 19 PRODUCT COMPANY IDENTIFICATION Product Name P1029 Pro38 Pro54 Pro75 and Pro8 Rocket Motor Reload Kits Synonyms Rocket Motor Proper Shipping Name Explosive N O S Ammonium Perchlorate Numbers P2GR Y 2G XX P38R Y amp G XX PS4R Y G XX P29R Y SGXL XX P38R Y GXL XXK PS4R Y EGXL XX Percentage 40 85 145 10 30 Percentage 70 76 8 18 9 20 trace 3 0 HAZARDS IDENTIFICATION Emergency Overview There articles contain cylinders of ammonium propefant encased in inert plastic perchiorate composite parts The forward closure also contains a few grams of black powder ProX Rocket motor reload kits are classified as explosives and may cause serious Injury Including death If used Improperly explosives are dangerous and must be handled carefully and used following approved safety procedures under the direction of competent experienced personnel In accordance with applicable federal
161. o hardwired to the AGSE to prevent any error that could stem from are wireless connection Visual confirmation of the state of these switches is included in the form of safety lights An amber orange light flashes at a frequency of 1 Hz to indicate that the AGSE is powered on and remains unlit when the power is off When the pause switch is engaged the light stays on constantly A green light is used to show that all the various systems on the rocket and tower have passed safety verifications and the entire system is ready for launch Along with this safety light system several controls have been put in place in the event of a system failure The most likely failures based on the AGSE design are shown in Table 16 Table 16 Failure Modes and Effects Analysis Failure Mode Cause Likelihood Severity Mitigation Sled Shearing of the two Bolts connecting the tube to the disconnecting bolts holding the chain are high strength stainless from tower connector tube to the Low High steel rated for over 500 Ib loads chains during chains rocket erection Ignition failure Igniter tube fails to Igniter tube is small enough in enter the rocket diameter to prevent choking and Low Low See motor properly the insertion is thoroughly tested to ensure functionality Tower falls or Unstable The small surface area and cross sways environmental section of the tower make it conditions such as highly unlikely that it will wind or severel top
162. ocess Feedback will indicate when the igniter has been fully inserted All processes will occur in this order one at a time The logic behind dedicating unit C solely to the Scorbot sequence is to eliminate the risk of crosstalk interfering with the idle state of the Scorbot If the Scorbot were to receive a command intended for a different AGSE component it will relay an error message and interfere with the feedback from the other Rx Tx units 78 4 5 2 AGSE Timeframe The AGSE will conduct its operations during several separate stages with delays in between stages The entire process shall take no more than 7 minutes excluding the countdown to launch A breakdown of the timeframe is shown below in Table 15 Table 15 AGSE Timeframe Event Event Event Time min sec Total Time Number Elapsed min sec oce oom e o oom 099 d om ome 4 6 Verification 4 6 1 Requirement Verification Navy Rockets have completed and verified all AGSE requirements for the project The list of requirements and verification methods can be found in Appendix D 79 4 7 AGSE Safety 4 7 1 Safety Analysis Several safety mechanisms are built into the integration plan in the event of a system failure A master switch is hardwired to the AGSE in order to control the battery power to the various systems Another switch is used to pause all actions performed by the AGSE during any point of the operation This switch is als
163. oid potential human and environmental exposure It is the responsibility of the generator to comply with all federal state provincial and local laws and regulations We recommend that you contact an appropriate waste disposal contractor and environmental agency for relevant laws and regulations Under the U S Resource Conservation and Recovery Act RCRA it is the responsibility of the user of the product to determine at the time of disposal whether the product meets relevant waste classification Section 14 TRANSPORT INFORMATION DOT Proper Shipping Name Not regulated Hazard Class Not regulated Identification Number Not regulated Packing Group Not regulated Label Required None Section 15 REGULATORY INFORMATION SARA Title III Section 302 304 Extremely Hazardous Substance None Section 311 Hazardous Categorization None Section 313 Toxic Chemicals None CERCLA Section 102 a Hazardous Substance None RCRA Information Currently the product is not listed in federal hazardous waste regulations 40 CFR Part 261 33 paragraphs e or f i e chemical products that are considered hazardous if they become wastes State or local hazardous waste regulations may also apply if they are different from the federal regulation It is the responsibility of the user of the product to determine at the time of disposal whether the product meets relevant waste classification and to assure
164. ontrol team to use procrastinate in obtained early other times could materials that obtaining as well as be a result of aren t the most materials Have backup procrastination ideal for a backup materials leading to limited certain part of materials options the project In a available worst case especially if scenario a they are crucial crucial material to the project s could be success unobtainable and the project could fail Variety of Could delay Have backup No damage potential causes project materials done yet but ranging from progress could available to fix backups unavoidable cause project to any damaged available to accidents to user fail if it happens ones Have vulnerable error at a crucial time alternate parts during the end designs or at the prepared in the competition event a Could force redesign is redesign necessary Machines not Could delay the Follow all Machine shop properly taken building and machine shop tools only care of or are manufacturing rules and operated under used improperly process of the ensure that the proper project correct supervision and machines are authority used for specific materials Schedule The team falls Have weekly Maintained becomes busy behind on meetings to open and then failure building and discuss what communication to update team on then misses each personis by meeting as a progress occurs deadlines for working on and team three times the project
165. oth 32 Pitch 4mm Bore Pinion Gear 0 016 6 32 Nylock Nuts 0 010 6 Washers 0 010 Actobotics 32 RPM Precision Planetary Gearmotor 0 221 Planetary Gearmotor Mount A 0 013 0 625 L x 6 32 Zinc Plated Alloy Steel Socket Head Cap Screw Motor Tube CTI 54mm K 1200 54mm Motor Retainer Miscellaneous Parts Additional Mass 30 3 3 Payload Securement Subsystem The payload section of the rocket utilizes the nosecone structure as an entry point to the payload bay Once activated via wireless transmission the nosecone slides away from the rocket body by a central rack and pinion system driven by a brushed DC motor exposing the payload bay This bay consists of a containment area in which the payload is placed and a servomotor driven tab that will rotate over the payload to secure it inside the rocket body This containment area is described further in section 3 9 3 The payload section also contains an Arduino Micro control board and an xBee Pro wireless serial modem This wireless modem receives commands from the AGSE control element The control board provides a link between this modem and both the brushed DC motor and the servomotor It is programmed using the native Arduino language There is also a 12 Volt battery power supply located in the payload section of the rocket to power all of the payload section components All of these elements are mounted on two central support rods made from one quarter inch threaded steel rods
166. oth launches proving that the avionics plan for the full scale will work properly during and after flight 3 6 3 Flight Simulations Varying weather conditions with will have an effect on the REPTAR launch vehicle on the day of the launch In order to predict possible consequences of varying weather a computer model of the launch was run through Open Rocket at wind speeds of 5 10 15 and 20 mph Graphs of the results are shown below in Figures 32 35 49 Altitude Altitude 3 000 2 750 2 500 2 250 2 000 1 750 1 500 1 250 1 000 750 Vertical motion vs time 30 35 40 45 50 55 60 65 70 75 80 85 Time s Altitude ft Vertical velocity fs Vertical acceleration 5 Figure 32 Vertical Motion vs Time at 5 mph Vertical motion vs time 35 40 45 50 55 80 85 Time s Altitude ft Vertical velocity ft s Vertical acceleration fus Figure 33 Vertical Motion vs Time at 10 mph 50 100 105 uoneJaja22e EIA 13018 E38 E3II8A Aj20Ja EHA Altitude 3 000 2 750 2 500 2 250 2 000 1 750 1 500 1 250 1 000 750 2 750 2 500 2 250 Altitude ig 3 Vertical motion vs time 50 55 65 70 75 Time s Altitude ft Vertical velocity fs Vertical acceleration 52 Figure 34 Vertical Motion vs Time at 15 mph Vertical motion vs time 46 50 55 60 65 70 75 80 85 Time s Altitude ft Vertical velocity fts
167. ple due to wind If the uneven ground i Low Meh ak at the launch site proves to be detrimentally uneven stakes will be used to hold the tower securely in place Chain system Loads on the chain The chain used on the tower snaps become too high and structure is rated for loads up to Pur UE Medium High 200 Ibs far heavier than the links rocket and sled combined Error in the coding Install a pause switch and test System S E Se or communication Low High the frequencies transmitting malfunction between sensors information 80 4 7 2 Personnel Hazards The AGSE personnel hazards can be seen in Table 17 These hazards have been considered dangerous but mitigation plans have been developed to ensure safety to all around and operating the equipment Table 17 AGSE Personnel Hazards Hazard Mitigation During setup the tower could collapse and The tower system is split into many parts to fall on a team member make it more manageable leaving no overly heavy or long sections Each piece is secured in place with either bolts or solid couplers making a collapse highly unlikely Launch rail or sled slips causing rocket to The launch rail is securely bolted to the point towards personnel during launch sled and highly unlikely to become loose The sled is securely held in place when it reaches the desired angle of 5 degrees from the vertical If all else fails the master switch would halt a
168. products are not considered Controlled Good In Canada under the Controlled Goods Reguiations United States of America TSCA Inventory Status All ingredients are listed on the TSCA Inventory Hazardous Chemical Lists CERCLA Hazardous Substance 40 CFR 302 4 i 3 eee Is included on the following countries chemical Inventories European Labelling in Accordance with EC Directives Hazard Symbols Explosive Risk Phrases R2 Risk of explosion by shock friction fire or other sources of ignition flammable R11 R44 RISk of explosion If heated under confinement Safety Phrases 512 Keep locked up and out of the reach of children 58 Keep container dry 15 away from heat 16 away from sources of ignition No smoking 167 MSDS Prox Rocket Motor Reload Kits Page 66 Version 2 02 Rasion Date Feb 2010 17 away from combustible material 18 Handle and open container with care 33 Take precautionary measures against static discharges 541 In case of fire and or explosion do not breathe fumes MSDS Prepared by Regulatory Affairs Department P O Box 246 2561 StoufiVille Rd Gormiey ON Canada LOH 1G0 905 587 2370 x239 Fax 905 887 2375 Web Sites 8 The data in Dis Material Safety Deta Street rotates oriy 1c the spectic or product designated herein end dows fof relata 15 use combination sih any othe mater
169. proper disposal WHMIS Canada Classification None This product has been classified in accordance with hazard criteria of the Controlled Products Regulations and this MSDS contains all the information required by the Controlled Products Regulations Ingredient Disclosure List None 152 MSDS Number 439 3227 00SU C000 12 Date October 1 2002 Page 6 of 6 Section 15 REGULATORY INFORMATION Continued California Safe Drinking Water and Toxic Enforcement Act of 1986 Proposition 65 Warning The state of California has determined that the following listed component chemicals in this product may cause cancer birth defects or other reproductive harm None U S EPA TSCA Information This product is an article as defined by TSCA and is not Tequired to be listed in the TSCA inventory Ozone Depletion Information This product does not contain or is not manufactured with ozone depleting substances as identified in Title VI Clean Air Act Stratospheric Ozone Protection and the regulations set forth in 40 CFR Part 82 Section 16 OTHER INFORMATION Special Precautions Airborne carbon fibers or dust are electrically conductive and may create electrical short circuits that could result in damage to and malfunction of electrical equipment and or personal injury Explanation and Disclaimer Wherever such words or phrases as hazardous toxic carcinogen etc appear herein they are used as defined or described under s
170. proved respirator with an organic vapor cartridge whenever exposure to vapor In concentrations above applicable Emits is likely Note West System Inc has conducted an alr sampling study using this product or similarty formulated products The results indicate that the components sampled for epichioronydrin benzyl alcohol were either so iow that they were not detected at all or they were significantly below OSHA s permissible exposure levels ADDITIONAL PROTECTIVE MEASURES Practice good caution and personal cleanliness to avoid skin and eye contact Avoid skin contact when removing gloves and omer protective equipment Wash torougnty after handling Generally speaking working and fotowng basic precaufionary measures es will greatly minimize the potential for harmful exposure to this product under noma use OCCUPATIONAL EXPOSURE Not established for product as whole Refer to OSHA s Permissible Exposure Level PEL or the ACGIH Guidelines for Information on specific Ingredients epoxy resin and hardener Refer to he hardeners MSDS for information about he total volatile content of the resinardener system 10 STABILITY AND REACTIVITY MSDS 105 13 Last Revised 26APR13 141 West System Inc Page 3 of 4 WEST SYSTEM 105 Resin HAZARDOUS POLYMERIZATION WI not occur by self but mass of more
171. r recognized technical sources is the user s responsibility to determine the Safety Toxicity and suitability of his her own use handing and disposal request Since actual use by others is beyond our control no warranty expresses or implied is made by Polymer Plastics Company L C as to effects of such use The results to be obtained or the safety and toxicity of the product nor does Polymer Plastics Company L C assume any liability arising out of use by others of the product referred to herein The data in this MSDS relate only to the specific material designated herein and do not relate to use in combination with any other material or in any other process REFERENCES N A Not Applicable N D Not Determined N D A No Date Available 550 Mallory Way Carson City NV 89701 775 283 4400 800 475 2214 www polymerplastics com 180 oon Material Safety Data Sheet according to Directive EC 1907 2006 Revision 21 11 11 Page 1 of 3 Product Lantor Soric XF SF TF LRC 0 Introduction This document provides a Material Safety Data Sheet MSDS for nonwovens on a voluntary basis according to EDANA recommendations Guidelines instructions relating to MSDS for nonwovens 10 GV8 422 The MSDS is a means of transferring essential hazard information including information transport handling storage and emergency actions from the supplier of a nonwoven product to the recipient of the product As nonwovens are genera
172. ranging from could cause members on safe only handled explosion unavoidable project to fail if handling of under accidents to user it happens at a motors and supervision error crucial time black powder during the end or Ensure a safety at the observer competition oversees all Could force handling of all redesign motors and black powder 96 5 2 5 Environmental Concerns Navy Rockets understands the impact of the environment when it deals with high power rocketry The rocket motors create ejection gases as the motor launches the rocket These gases are directed downwards during takeoff into the ground However a blast plate will be used to deflect the gas from entering directly into the ground All spent motors will be disposed of properly The environment also causes concerns to the rocket as well The humidity and temperature of the air can affect the way the motor functions If the motor is exposed to poor conditions it will not launch as expected This will be mitigated by keeping the motors in the proper conditions and ensuring they are not launched if anything is found to be wrong The complete analysis can be found in Table 23 and 24 The analysis scores the hazards using the ORM system Table 23 Environmental Impact on the Rocket Hazard ORM Cause Effect Mitigation Verification Value Environmental Concerns Environmental Impact on the Rocket High Enviro
173. rate subsystems will be avoided Limiting the AGSE to one task at a time will minimize the risk of compounding any errors and will simplify the troubleshooting process Any error can be traced back to the single subsystem that will be operating during the time of the incident Thus far no changes have been made to the integration plan The AGSE layout is displayed below in Figure 53 77 A Laptop MATLAB B Power Supply C D E F G H RF Transmitter Receiver 1 Tower Motor Microprocessor J Tower Motor Amplifier K Tower Motor L Scorbot Control Unit M Scorbot Unit N Igniter Insertion Motor Microprocessor O Igniter Insertion Motor Amplifier P Igniter Insertion Motor Figure 53 AGSE Schematic Unit C will communicate with unit E to relay commands to the Scorbot control unit Unit E will relay feedback back to unit C to signal when the Scorbot has completed motion sequence Unit D will communicate with units F G and H Commands to the payload bay concerning the securing of the payload and the closure of the payload bay will be sent from unit D to unit H Feedback stating when these tasks are complete will be returned Unit D will communicate with unit F to control the tower motor When the rocket has reached the 85 degree launch angle motor rotation will cease and unit F will relay a signal back to unit D stating that the process is complete Following this unit D will relay commands to unit G to begin the igniter insertion pr
174. ration preferably by mouth to mouth Qs eigen Seek prompt medical Eye and skin contact Not a likely route of exposure Flush eyes with water Wash skin with soap and water Nol a Ikely route of exposure f ingested CAPP DY ANNO Use appropriate personal protective equipment Isolate area and remove sources of friction impact heat low level electrical current electrostatic or RF energy Only competent experienced persons should be involved in clean up procedures Carefully Led up spilis with non sparking and non static i uting in water Open train buming by qualified personnel may be used for disposal of small unconfined quantities Dispose of in compliance w amp h Federal Regulations the authority of the Resource Conservation and Recovery SPECIAL PROTI ON 171 SPECIAL PRECAUTIONS Keep away from friction impact and heat and open flame Do not consume food drink or tobacco in areas where they may become contaminated with these materials Contaminated equipment must be thoroughly water cleaned before attempting repairs Use only non spark producing tools SHIPPING INFORMATION DRE LENE E UN Number A UN0027 UN Number D DOT Placard CS EXPLOSIVES 11 Limited quaniilies of GOEX black powder 1 cans only may be as en for 706 arms flammable solid The information contained in this Material Safety Data Sheet is
175. ration hazard SYMPTOMS OF OVEREXPOSURE Respiratory tract Imitation Skin irritation and redness Possible allergic reaction seen as hives and rash Eye irritation Possible liver and kidney disorders upon long term skin absorption overexposures MEDICAL CONDITIONS AGGRAVATED BY EXPOSURE _ Chronic respiratory disease asthma Eye disease Skin disorders and Reacton products of triethyinetetramine with phenouormaidenyde 32610 77 8 40 70 Polyethytenepolyaminas 58131 73 7 10 30 Trethyfenetetramine 112 24 3 5 20 108 95 2 1 10 Reacton products of triethytenetetramine and propytene oxide 26950 53 0 1 10 Tetraethylenepentamine 112 57 2 1 10 4 FIRST AID MEASURES FIRST AID FOR EYES mmediatety Sush with water for at least 15 minutes Get prompt medical FIRST FOR SKIN REMOVE contaminated cio hing Immediately wash skin with soap and water Do not apply greases or ointments Get medical attention if severe exposure MSDS 205 13 Last Revised 26APR13 144 West System Inc Page 2 of 4 WEST SYSTEM 205 Hardener REN PD a Move to fesh alr and consult physician If effects occur FIRST FOR INGESTION GIVE CONSCIOUS person at least 2 Glasses of water Do not Induce vomiting If vomiting s
176. rior to the initial Recovery subscale and full scale launches 23 At landing each independent section of the launch vehicle shall Recovery f have a maximum kinetic energy of 75 ft lbf 24 The recovery system electrical circuits shall be completely Recovery independent of any payload electrical circuits The recovery system shall contain redundant commercially 25 available altimeters The term altimeters includes both simple Recovery altimeters and more sophisticated flight computers One of these altimeters may be chosen as the competition altimeter A dedicated arming switch shall arm each altimeter which is 2 6 accessible from the exterior of the rocket airframe when the rocket Recovery is in the launch configuration on the launch pad PI Each altimeter shall have a dedicated power supply Recovery Each arming switch shall be capable of being locked in the ON 2 8 25 Recovery position for launch Removable shear pins shall be used for both the main parachute 2 9 Recovery compartment and the drogue parachute compartment An electronic tracking device shall be installed in the launch 2 10 vehicle and shall transmit the position of the tethered vehicle or Avionics any independent section to a ground receiver 123 2 10 1 Any rocket section or payload component which lands untethered to the launch vehicle shall also carry an active electronic tracking device Avionics 2 10 2 The electronic tracking device
177. rn 3 Is unmanned and 4 Does not create a hazard to persons property or other aircraft b The FAA may specify additional operating limitations necessary to ensure that air traffic is not adversely affected and public safety is not jeopardized 101 25 Operating limitations for Class 2 High Power Rockets and Class 3 Advanced High Power Rockets When operating Class 2 High Power Rockets or Class 3 Advanced High Power Rockets you must comply with the General Operating Limitations of 101 23 In addition you must not operate Class 2 High Power Rockets or Class 3 Advanced High Power Rockets a At any altitude where clouds or obscuring phenomena of more than five tenths coverage prevails b At any altitude where the horizontal visibility is less than five miles 133 Into any cloud d Between sunset and sunrise without prior authorization from the FAA e Within 9 26 kilometers 5 nautical miles of any airport boundary without prior authorization from the FAA f In controlled airspace without prior authorization from the FAA g Unless you observe the greater of the following separation distances from any person or property that is not associated with the operations 1 Not less than one quarter the maximum expected altitude 2 457 meters 1 500 ft h Unless a person at least eighteen years old is present is charged with ensuring the safety of the operation and has final approval authority for initiat
178. rophic Faulty motor Rocket Ensure properly Motor handled motor or destroys the storage and handling very carefully failure mishandling frame and of the motor during possibly traveling damages the system 95 Table 22 Safety Concerns for the Student Launch Hazard ORM Cause Effect Mitigation Verification Value Safety Chemical Poor handling of Could cause Educate all team Safety Burns dangerous severe injury to members on safe emphasized materials poor crucial team handling of before each oversight from members thus dangerous evolution leadership placing more materials responsible for workload on Ensure a safety safety lack of other members observer knowledge about decreasing the oversees all dangers of overall quality of handling of said materials the output of materials their work Injury Poor safety Could cause Educate and Proper safety from practices lack of severe injury to train all team measures Power knowledge about crucial team members on safe taken Equipment dangers involved members thus operation of with the power placing more dangerous equipment workload on equipment other members Ensure a safety decreasing the observer overall quality of oversees all the output of handling of said their work equipment Motor or Variety of Could delay Educate and Proper training black potential causes project progress train all team provided and powder
179. rvisor or the manufacturer if you do not have a supervisor If sor has any questions or doubts he should consult the manufacturer before use HAZARDOUS COMPONENTS tete or Components or aenalorComponens cano oorrs7 7e 1_ NE d EXE 915 NA NE 5 NE i m T 7782 42 5 ppc 2 5 mgim 6 Re Not contained in all grades of black powder P O Max 659 Doyline LA 71023 0659 318 382 9300 www goexpowder com 169 PHYSICAL DATA B gPon INA I SE E a Vapor Denstyy NA TT DAMEN ST GOA CELL Specific Gravity 1 70 1 82 mercury method 1 92 2 08 pycnometer MN ia ERN E E HAZARDOUS REACTIVITY sr Keep away from heat sparks and open flames Avoid impact friction and static electricity When dry black powder is compatible with most metals however it is hygroscopic and when wet attacks all common metals except stainless steel Black powder must be tested for compatibility with any material not specified in the production procurement package with which they may come in contact Materials include other explosives solvents adhesives metals plastics paints cleaning compounds floor and table coverings packing materials and and equipment Hazardous decomposition Detonation produces hazardous overpressures an
180. ry 126 APPENDIX E Laws and Safety Codes E 1 NAR High Power Rocket Safety Code NAR High Power Rocket Safety Code Effective August 2012 1 Certification I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing 2 Materials I will use only lightweight materials such as paper wood rubber plastic fiberglass or when necessary ductile metal for the construction of my rocket 3 Motors I will use only certified commercially made rocket motors and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer I will keep smoking open flames and heat sources at least 25 feet away from these motors 4 Ignition System I will launch my rockets with an electrical launch system and with electrical motor igniters that are installed in the motor only after my rocket is at the launching or prepping area My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch and will use a launch switch that returns to the off position when released The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position 5 Misfires If my rocket does not launch when I press the button of my electrical launch system I will remove the launcher s safety interlock or disconnec
181. s exting will De done to ensure the calculated Diack powder charge will actually pressurize the rocket correctly so that the parachutes deploy Ground testing ill entail a static firing of a 1 1 size test section at Bunch facility TESTING COMPLETE AND Charge Tests SUCCESSFUL Sub zcale rockets will be launched with scaled payloads weight snc motor size By analyzing the stability of the rocket through inspection the stability parameters such as the center of pressure anc the center of gravity a5 ratios of the total rocket length will be critiqued The normalized parameter were lated to be similar to that of the full scale in order to analyze the stability TESTING COMPLETE AND SUCCESSFUL Full scale testing will entail complete execution of the mission parameters set forth by the Student Launch Instruction sub systems will be tested to include autonomous insertion of the payload the AGSE anc the ejection of the payload at 1000 feet Deliverables include confirmation of altitude anc Full zcuie Test sra bility predictions ejection charge ceiculstionz and parachute drift calculations TESTING COMPLETE AND SUCCESSFUL Flights 111 4 H p F BbH e APPENDIX B Component Sizing Nose cone Payload Section Avonics I Len 25 in Len 0 125 in Len 10 in Len 0 079 in Len 4in Len 21 in Len 5 5 in Len 21 in Mass 1 35 Ib Mass 1 5 Ib Mass 0 116 Ib
182. s Table La Subsystem GE PRU acce vr om toi ove ERI A 16 Table 2 Material QFD aedes ctae Ni eode io Cu Soda 21 Table 3 Launch Vehicle Failure 29 Table 4 Component Masses sioe totales eost aaa es asda Hanae 30 Table 5 Payload Section Failure Analysis eese sees eene eene een nnne nnne enne 35 Table 6 Black Powder Charge Calculations aa pee sete 41 Table T GPS Characteristics es educat kN tea tue due 43 Table 8 Mass of Sections During Flight neon Ne Yn de casae e Ie es eaa 53 Table 9 Kinetic Energy Values Tor Sections 54 Table 10 Wind Drift Values at the Best and Worst Case Scenarios sss 55 Table 11 Cp Values from Wind UR MEE SEN PIU nee oa PA IR 59 Table 2 Vehicle Safety Analysis p EUG 60 Table 13 Personnel Hazards berti tt ere Kaa 61 SUCCESS Nolet alas ii eor tere ee coins baa e EI Hed gs cu suae a ea tea rre se ead oases 65 Table 15 REE aR RS On un edo ed 79 Table 16 Failure Modes and Effects Analysis esee enne enne enne 80 Table L7 AGSE Persounel Hazards oe rS e OR Da cede eg Ven MN ETE uH
183. s or tears in parachute cloth shrouds or harness lines Assemble full harness by attaching all carabineers harness loops and parachute swivels Ensure parachute protectors are in correct location on harness Roll parachutes and lines in an orderly pre determined fashion to eliminate tangles upon deployment Check all connection points and carabineer screw gates Position the protectors inside parachute housing compartments Install new 9V batteries into altimeter power clips Ensure each altimeter powers on 10 Ensure each GPS unit powers on and is transmitting 11 Seal avionics compartment 12 Following all safety precautions load black powder into ejection canisters Before Launch l 2 Engage master arming switch in locked armed position Ensure both exterior LED lights function and flash correct battery voltage 5 1 3 Motor Preparation Toup Remove ejection charge from motor Insert K1200 motor into casing Insert the motor and casing into the motor retention Ensure that the igniter insertion receives the igniter 5 1 4 AGSE Assembly Setup po D Slide track coupler into short segment of foot A Secure with bolts Slide other side of track coupler into short segment of foot B Secure with bolts Slide tower segment C onto the stock couplers protruding from both foot A and foot B Secure with bolts Slide tower segment D onto the stock couplers protruding from the top of ladder segment C Secur
184. s material is a risk to the environment This material is water Di As on hazardous solid waste nonwovens can be disposed of depending on local legislation through recycling incineration or landfill 183 APPENDIX G Gantt Chart USNA Student Launch Planner Il Complete beyond plan Actual beyond plan Complete Date WBS ID ACTIVITY September October November December January February March April Updated as of 1 Determine and Rocket Design 1 1 1 Establish Team Web Presence 1 1 2 Write Proposal 113 Proofread and Finalize Proposal 114 Submit Proposal to NASA 2 6 1 2 Submit Work Order 12 1 Write PDR USNA STEM Girls Day Outreach Event 2 6 1 1 Write Wind Tunnel Test Plan 1 2 2 Proofread PDR SCORBOT Internal Setup Build Subscale Model 123 Post PDR on Website 124 Rehearse PDR Conference USNA STEM MESA Outreach Event 12 5 PDR Teleconference USNA MINI STEM Outreach Event 2 1 1 1 GPS Acquisition 2 2 2 1 Altimeter Acquisition 2 1 3 2 Ejection Cannister Acquisition 2 2 1 1 Recovery Components Acquisition 2 3 1 1 Main Body Material Acquisition 2 4 1 2 Payload Section Components Acquisition 2 5 2 2 1242 Acquisition 32 3 Modification d 2 3 1 2 Main Body Fabrication Material Test 24 14 Payload Section Internal Setup Integrate Subscale Test Components 2 1 1 2 GPS Testing 2 1 2 2 Altimeter Testing 2 3 1 3 Main Body Fabrication Subscale Launch 3
185. ss or division None Identification number None Packing group None IDH number 1071248 Product name Loctite Epoxy Heavy Duty Resin Page 3 of 4 156 Proper shipping name Environmentally hazardous substance liquid n o s Bisphenol A Epichiorhydrin resin Hazard class or division 3 identification number UN 3082 Packing group Water Transportation IMOMMDG Proper shipping name ENVIRONMENTALLY HAZARDOUS SUBSTANCE LIQUID N O S Bisphenol A Epichiorhydrin resin Hazard class or division 3 Marine pollutant Bisphenol A Epichiorhydrin resin 15 REGULATORY INFORMATION United States Regulatory Information TSCA 8 b Inventory Status All components are listed or are exempt from listing on the Toxic Substances Control Act Inventory TSCA 12b Export Notification None above reporting de minimus CERCLA SARA Section 302 EHS above reporting de minimis CERCLA SARA Section 3111312 Notavalabie ARA 313 None above reporting de minimis California Proposition 65 This product contains a chemical known In the State of Callfomia to cause cancer This CEPA DSL NDSL Status All components are listed on or are exempt from listing on the Canadian Domestic Substances List 16 OTHER INFORMATION This material safety data sheet contains changes from the previous version sections Not available Prepared by Donna Houston Regulatory Affairs Specialist DISCLAIMER The data conta
186. ssociation of Rocketry 139 APPENDIX F MSDS MATERIAL SAFETY DATA SHEET West System Inc PRODUCT NAME SYSTEM 105 Epoxy Resin PRODUCT CODE 105 WARNING May cause skin tation May cause eye Imitation May cause allergic reaction Clear viscous liquid with mild odor PRIMARY ROUTE S Sin contact POTENTIAL HEALTH EFFECTS ACUTE INHALATION es PRO Gust Is heated vapors generated can cause headache nausea dizziness and possible respiratory tation If Inhaled in high concentrations Cres NP Lh Ls Repeated exposure to high vapor concentrations may cause imitation of ung urges ane rarum thn usas of Gp ay pupa to ACUTE SKIN CONTACT ee _ May cause allergic skin response in certain Individuals May cause moderate Imation to the skin such as redness and fiching CHRONIC SKIN _ May cause sensitization In susceptibie Individuals May cause moderate imtaton to fne skin May cause Imitation INGESTION eerte LOW SOULE Oral toxicity SYMPTOMS OF OVEREXPOSURE _ Possible SENSRIZATON and subsequent allergic reactons usually seen as redness and rasnes MEDICAL CONDITIONS AGGRAVATED BY EXPOSURE _ Pre existing skin and respiratory disorders may be aggravated by exposure to this product Pre existing lung and skin allergies may
187. st was complete the second set of payload section components was mounted in the actual launch vehicle payload section 3 3 5 Safety and Failure Analysis The failure modes for the payload section of the rocket are presented below in Table 5 Table 5 Payload Section Failure Analysis Failure Mode Cause Likelihood Severity Mitigation O Servomotor malfunction Low Low Testing secured Payload section DC motor malfunction Low High Testing fails to close Mechanical fault Low High Testing 35 All of these failure risks in the payload section are being mitigated and addressed through extensive testing of both individual components and the system as a whole The main safety risk involved with the payload section of the rocket is failure to close the payload section This failure would result in an improperly sealed or seated nosecone This could greatly affect the aerodynamics or structural integrity of the rocket as a whole which could result in erratic and dangerous flight of the rocket This main safety risk is a result of the second failure mode presented in the above table and as such it will be mitigated through extensive testing of the payload section using both mock ups and the full scale rocket body 3 4 Recovery Subsystem The Navy Rockets Launch Vehicle will use a robust and well tested dual deployment recovery system The first recovery event will take place at 3000 feet AGL deploying a drogue para
188. sting Complete Mar 07 Full Scale Launch Successful Mar 11 Payload Section Complete Mar 13 FRR Completed and Submitted 102 In order to ensure rocket and AGSE completion a project punch list has been created shown in Table 28 This punch list is a list of the final jobs that must be completed before the competition Table 29 Project Punch List Completion Item Date Alex Avionics 23 Mar Install new low drag switches and LEDs 25 Mar Receive USB cord 25 Mar Reprogram deployment altitudes Cole Rocket Body 23 Mar Create organization and securement for avionics boards 23 Mar Test shear pin strength for final configuration 25 Mar Integrate nose cone with payload bay 27 Mar Balance rocket weight with predicted values 29 Mar Sand and paint rocket Thor Payload Bay 22 Mar Mount all components on mockup 23 Mar Mockup testing 24 Mar Complete Arduino Code 25 Mar Integrate nosecone with payload bay 27 Mar Full scale testing Richie AGSE 25 Mar Complete tower and sled 25 Mar Construct Scorbot Plate 25 Mar Integrate Igniter insertion unit to sled 26 Mar Attach motor to tower 26 Mar Attach gate latches 26 Mar Setup safety lights 26 Mar Connect all systems to power 27 Mar Integrate wireless communication 27 Mar Full system test oo Sam Coding i 25 Mar Scorbot calibrated 25 Mar Igniter
189. t for the nosecone while it is extended away from the rocket body It is rated to support 75 pounds which is more than sufficient to meet payload section requirements e 1 4 Threaded Steel Rods o Threaded steel support rods were selected for the payload bay due to the high ease of installation of the rods and the support tray for the components These rods maintain a low weight and high strength which makes them an excellent choice for support rods in the payload section The DC motor its mounting bracket and the associated gearing system are shown in Figure 17 32 Figure 17 DC Motor and Gearing System 3 3 2 Electrical Elements The overall electrical schematic of the payload section is shown below in Figure 18 Arduino Micro Control Board a Power Supply O Voltage Indicator Data Transfer Figure 18 Payload Section Electrical Schematic The switch shown in the above diagram will either supply or deny power to the entire payload section when turned on or off respectively It will be placed in an easily accessible location 33 within the payload section to allow for great ease of use The primary electrical elements of the payload section and their specifications are detailed below e MaxStream xBee Pro Wireless Serial Modem 900HP o This wireless serial modem was chosen for its simplicity low cost and small size Each of these characteristics is important to the design of the payload bay This p
190. t its battery and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket 6 Launch Safety I will use a 5 second countdown before launch I will ensure that a means is available to warn participants and spectators in the event of problem I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations I will check the stability of my bitore cd img oir i F it cannol be sordes bedahe When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA 1127 7 Launcher I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight and that is pointed to within 20 degrees of the vertical If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher I will use a blast deflector to prevent the motor s exhaust from hitting the ground I will ensure that there is no dry grass within a clear distance of each launch pad determined by the accompanying Minimum Distance table and will increase this distance by a factor of 1 5 and clear that area of all combustible
191. t screw top terminals on the outside of the avionics section bulkheads This will create true redundancy throughout the entire altimeter system The primary altimeter will be programmed to initiate a charge intended to deploy a drogue parachute at flight apogee then initiate a charge intended to simultaneously separate the sample section and deploy a main parachute at 1000 feet above ground level The secondary altimeter will be programmed to initiate a charge intended as a backup to the first primary altimeter charge This event will occur 3 seconds after flight apogee The secondary altimeter will then initiate a charge intended as a backup to the second primary charge This event will occur at 900 feet above ground level 13 2 2 1 The joints between the horizontal and vertical components of the tower feet have been reinforced with triangular aluminum plating This will ensure that the welds will not crack if a moment is exerted upon the structure during any portion of the sequence 2 The sled will have two wheels on the lower end as opposed to one The tower structure will have to two tracks one for each wheel This will increase the stability of the sled as it is raised to the launch position 3 The battery has been changed to a 12 volt 75 AH battery The increase in capacity will increase the possible loiter time 4 Rungs are no longer pinned into place The upper and lower rungs are mounted onto flange bearings to faci
192. t the time of the proposal 6 4 3 1 MESA DAY Done in collaboration with Maryland Mathematics Engineering Science Achievement MESA MESA day is one of the primary recurring USNA STEM events that Navy Rockets plans on doing MESA day is a full day of involved activities that keep elementary students from local counties and Baltimore City involved and interested in STEM related activities Along with a plethora of age appropriate interactive activities in different STEM areas groups are encouraged to participate in a mini engineering design competition Navy Rockets involvement in MESA day would consist of creating aerospace specific activities that will keep the students engaged and attentive MESA day occurs monthly 105 6 4 3 2 Mini STEM At the Naval Academy high schools from around the country have students come visit USNA for an overnight visit or a long weekend This is known as a Candidate Visit Weekend During these candidate visits the students tour the technical majors but more importantly spend time engaged in interactive science and engineering activities Navy Rockets plans to bolster the candidate s visits with helpful science and engineering activities Navy Rockets has the ability to conduct wind tunnel experiments load cell experiments and much more with the mini STEM groups Candidate visits are held a handful of times during a semester so there are an abundance of mini STEM opportunities for Navy Rockets to pick up o
193. tails Through hands on utilization of technology and computer programs Navy Rockets hopes to foster interest in the future of aerospace engineering and space flight 6 4 2 Team Participation It is of utmost importance that each active member of Navy Rockets participates in outreach such that they have direct educational interaction with at least 100 different participants This will ensure that the Student Launch minimum requirement of 200 participants at least 100 being middle school is surpassed 6 4 3 STEM events Navy Rockets plans to be involved in unique STEM events where different populations are targeted There are four types of events that Navy Rockets plans on doing All four events involve direct interaction with the participants The four types are e Direct Educational interaction involving Aerospace Engineering e Direct Outreach interaction involving aerospace engineering e Direct Educational interaction not involving aerospace engineering e Direct Outreach interaction not involving aerospace engineering The four types of events will encompass Navy Rockets educational outreach Of that the events where Navy Rockets is interacting through aerospace engineering topics will be the majority of the events attended by Navy Rockets Navy Rockets plans on impacting the following STEM events The events are not a comprehensive list of the events the team members attend but they are a list of the major events that are scheduled a
194. tal sled as shown below in Figure 45 Figure 45 Tower Sled 69 For strength and transportation purposes the sled including the square tube spine is split into two equal pieces each 6 5 feet in length The two pieces are connected together by an aluminum stock coupler milled down to fit within the square tubing Once inside the tube the coupler is secured using several stainless steel bolts At the end of the sled where there are 6 inches of sheet metal not covered by the 12 5 feet spine there are two standard caster wheels each bolted to the aluminum sheet 1 inch from the centerline These wheels run in the two tracks attached to the tower structure On the other end of the sled are fixed two eyebolts with the rings 1 0625 inches in diameter These eyebolts are attached to the sled connector tube which is shown below in Figure 46 Figure 46 Sled Connector The connector tube shown in Figure 46 is made of 1 inch OD aluminum round tubing and is 8 inches in length Eight circular holes have been drilled through the wall of the tube The holes are located 1 inch from both ends of the tube and are spaced at 90 degree intervals The top and bottom holes through which the chain runs are 0 5 inches in diameter An 8 32 bolt 1 5 inches long is placed through the two smaller horizontal holes also passing through a link in the chain inside the tube These two bolts serve to hold the tube to that place on the chain The sled is attache
195. tate employee right to know laws Federal OSHA laws or the direct sources for these laws such as the International Agency for Research on Cancer IARC the National Toxicology Program NTP etc The use of such words or phrases should not be taken to mean that we deem or imply any substance or exposure to be toxic hazardous or otherwise harmful exposure can only be understood within the entire context of its occurrence which includes such factors as the substance s characteristics as defined in the MSDS amount and duration of exposures other chemicals present and preexisting individual differences in response to the exposure The data provided in this MSDS is based on the information received from our raw material suppliers and other sources believed to be reliable We are supplying you this data solely in compliance with the Federal OSHA Hazard Communication Standard 29 CFR 1910 1200 and other Federal and state laws as described in Section 15 Regulatory Information The information contained in this MSDS is proprietary and confidential to Hexcel Corporation This MSDS and the information in it are not to be used for purposes other than compliance with the Federal OSHA Hazard Communication Standard If you have received this MSDS from any source other than Hexcel Corporation or its authorized agent the information contained in it may have been modified from the original document and it may not be the most current revision Liability i
196. tating organic fragments 6 ACCIDENTAL RELEASE MEASURES Use personal protection recommended in Section 8 Isolate the hazard area and deny entry to unnecessary and unprotected Environmental precautions Do not allow product to enter sewer or waterways Clean up methods Remove all sources of ignition Immediately contact emergency personnel Scrape up as much material as possible Clean residue with soap and water Store a partly filled closed container until disposal 7 HANDLING AND STORAGE Handling Do not breathe gas fumes vapor spray contact with eyes skin and clothing Wash thoroughly after handling Keep container closed Storage Store In original container until ready to use Keep a cool well ventilated area away from neat sparks and open flame Keep container tightly closed until ready for use For Information on product shelf life contact Henkel Customer Service at 800 243 4874 8 EXPOSURE CONTROLS PERSONAL PROTECTION Employers should complete an assessment of all workplaces to determine the need for and selection of proper exposure Engineering controls Provide adequate local exhaust ventiation to maintain worker exposure below exposure limits Respiratory protection Use a NIOSH approved air purifying respirator If the potential to exceed estabished exposure limis exists Eyeiface protection Safety goggles or safety glasses with side shields Skin protection Chemical resistant imper
197. te Chute REESE Payload Avionics Main Chute Section Figure 2 OpenRocket Design and Solid Works Model The rest of the rocket body is made from carbon fiber The payload compartment will be 10 inches long and hold the mechanical equipment that will control the payload system The parachutes are housed in a 20 5 inch long section with the entire recovery harnesses for both the payload and the main body The avionics section of the rocket will be 14 5 inches long The lower section of the rocket will be 37 inches long and hold the motor casing and motor retention The motor mount will be 25 inches long and 54 millimeters in diameter shown in Figure 4 in order to accommodate the correct motor 18 26 0 10 0 20 5 108 0 14 9 37 0 Figure 3 Rocket Dimensions The three fins are connected to the motor mount and held between centering rings The fins are 0 125 inches thick and have an area of 47 5 square inches The complete component sizes can be found in Appendix B and the completed rocket can be seen in Figure 5 19 Figure 4 Fin and Motor Dimensions Figure 5 Full Scale Rocket 3 2 1 Structural Elements 3 2 1 1 Material Selection Carbon fiber and fiberglass are common materials used in high power rocketry In order to determine which material is the better product a house of quality is used The house of quality 20 uses the Quality Function Deploy
198. tective clothing as required to prevent skin contact SECTION IX HANDLING AND STORAGE PRECAUTIONS STORAGE AND HANDLING Use with adequate ventilation Avoid contact with eyes and skin Avoid breathing fibers SECTION X ADDITIONAL INFORMATION SHIPPING INFORMATION Not regulated HMIS RATING 0 4 Extreme Fire 0 3 High Reactivity 0 2 Moderate 1 Slight 0 Insignificant Personal Protection See Section V 177 PAGE 4 of 4 Fiberglass Cloth SECTION 313 SUPPLIER NOTIFICATION This product contains the following toxic chemicals subject to the reporting requirements of the Emergency Planning and Community Right To Know Act of 1986 and 40 CFR 372 CHEMICAL NAME CAS BY WGT Not Applicable THIS INFORMATION MUST BE INCLUDED IN ALL MSDS THAT ARE COPIED AND DISTRIBUTED FOR THIS CHEMICAL ABBREVIATIONS IARC Intemational Agency for Research on Cancer ACGIH American Conference of Governmental Industrial Hygienists NIOSH National Institute of Occupational Safety and Health TLV Threshold Limit Value PEL Permissible Emission Level DOT Department of Transportation NIP National Toxicology Program N AV Not Available N AP Not Applicable NE Not Established ND Not Determined PREPARED BY US CHEMICAL amp PLASTICS Alco Industries Companies 600 NOVA DRIVE SE MASSILLON OH 44646 TELEPHONE NBR 330 830 6000 FAX NBR 330 830 6005 DATE REVIEWED September 14 2012 DATE REVISED September 14 201
199. teria shows tat it is not hazardous waste elther by listing or characteristics In Its purchased form It is the responsibility of the user to determine proper disposal incinerate recycle fuel blending or reciaim may be preferred methods when conducted In accordance with federal state and local regulations MSDS 105 13a Last Revised 26APR13 142 WEST SYSTEM 105 Resin M PACKING GROUP ER ggg gg gg NM 15 REGULATORY INFORMATION OSHA STATUS TSCA COmponents are listed on TSCA inventory or ofhenatse comply with TSCA requirements Canada WHMIS Classification 02 material causing other toxic effects EEE REESE All components are listed or are otherwise compilant with CEPA SARA TITLE IIE SECTION 313 TOXIC CHEMICALS None deminimus STATE REGULATORY INFORMATION The following chemicals are specfically Ested or otherwise regulated by Individual states For detalis on your regulatory requirements you should contact the appropriate agency In your state COMPONENT NAME ICAS NUMBER CONCENTRATION STATE CODE Epichioronydrin 106 89 8 lt Sppm CA Benzy alcohol 100 51 6 MA PA NJ 3 These substances are known to the state of Callfomia to cause cancer or reprodu
200. than one pound of product plus an aliphatic amine wl cause irreversible polymerization wiin significant heat bulidup INCOMPATIBILITIES e cssc STONY BOIS bases amines and mercaptans can cause polymerization DECOMPOSITION PRODUCTS ss _ Carbon monoxide carbon dioxide and phenolics may be produced during uncontolled exothermic reactions or when otherwise heated to decompositon 11 TOXICOLOGICAL INFORMATION No specific oral Inhalation or dermal toxicology data is known for this product Specific toxicology information for a bisphenol A based epoxy resin present in this product is Indicated below nena gt 8000 mg rats inhalator _ m IER T is 20 000 skin adsorption In rabbits TERATOLOGY Diglycidy ener bisphenol A DGEBPA did not cause birth defects or other adverse m pregnart rabbis were exposed by skin contact the most likely route of exposure or when pregnant rats or rabbits were REPRODUCTIVE In animal studies has been shown not to interfere wiih reproduction Ragas DGEBPA In animai mutagenicity studies were negative In v ro mutagenicty tests were negative In some cases and positive In others CARCINOGENICITY 7 Product not sted E Product not Ested e 1 E No ingredient of tnis product present at levels greater tnan or equat to 0 1 Is as
201. the epoxy pressurizing the proper altitude or bulkheads to tube or from the will split into ensure they can recovery system pieces and be a withstand heavy causing too much hazard while loads stress landing The batteries are The rocket Test the circuitry not fully powered or wired incorrectly systems will not function properly and may cause damage to the rocket and also put in new batteries before launch Cord and wires Rocket will not Test and check are not secured be safe when it all of the components of properly or are deploys recovery recovery damaged parachutes harnesses prior to system double causing the launch checked and landing to be reinforced hazardous Possible loss of Unsuccessful Test the GPS GPS rocket due to rocket recovery system to ensure functioned winds that it is perfectly on functioning testing properly 93 Table 20 Hazard Analysis for the AGSE System Hazard ORM Cause Effect Mitigation Verification Value AGSE AGSE drops Poor coding Cause failure Repeatedly test sample motor issues of AGSE operation power issues competition work out all environmental issues before issues competition day AGSE loses Power issues AGSE stops Ensure nearby communications external wireless working wireless radios link interference causes failure are turned off so Igniter does not insert of competitio
202. then put into Open Rocket rocket simulation software For our design a motor diameter of 2 13 inches was chosen This narrowed the choices to mostly K motors and a few L motors Finally the motor was chosen based on the required apogee of 3 000 feet with a buffer zone of 100 feet This led to the selection of a K1200WT motor by Cesaroni Technology Inc There were other motors that came within 15 of the targeted 3100 foot goal notably the 2130 K600 WH and the K750 17 motors Figures 27 29 below are graphs generated from Open Rocket depicting vertical motion vs time in the K600 K750 and K1200 motors respectively 44 Altitude Vertical motion vs time 3 000 2 750 2 500 2 250 2 000 1 750 1 500 1 250 1 000 750 500 250 250 Time s Altitude ft Vertical velocity fs Vertical acceleration ft s7 Figure 27 K600 Veritcal Motion vs Time Vertical motion vs time 3 500 3 250 3 000 2 750 2 500 2 250 2 000 1 750 1 500 1 250 1 000 750 500 250 Altitude uonela a33e ANIO aA JEIH3A 250 Time s Altitude ft Vertical velocity fs Vertical acceleration ft s7 Figure 28 K750 Vertical Motion vs Time 45 UOneJa a22e JEJA AIO AA BIMANA Vertical motion vs time 3 000 2 750 EE amp 550 2 500 E n 2 250 450 2 000 8 400 1 750 amp 350 3 1 500 3 1260 E 250 1 000 4 Uone
203. tion To ensure full interoperability of the payload section with the remainder of the rocket body the payload lead is working closely with the chief engineer and the structures lead throughout the entire process of design and development 3 9 1 2 Vehicle to Ground Interface The payload section of the rocket body interfaces with the AGSE through the use of wireless transmissions Within the payload bay there is a MaxStream xBee Pro wireless serial modem which operates at 900 MHz The MaxStream xBee Pro within the payload bay interfaces with another MaxStream xBee Pro which will be connected to the control segment of the AGSE This link between the two modems allows for commands to be sent from the AGSE to the payload bay and for feedback from the payload bay to be sent back to the AGSE To ensure the flawless operation of this interface the payload and AGSE leads are working hand in hand throughout the design and development stages 3 9 2 Element Compatibility All components of the payload section are fully compatible with the remainder of the rocket body All of the components are mounted on two aluminum support rods which are then secured through the aft bulkhead of the payload section This creates full compatibility between the payload components and the rocket body Any additional securement that may be needed in the payload section will be done with epoxy or mechanical fasteners namely brackets This will allow for a firm and secure mou
204. tion insurance is coincident with the section charter and expires on April 4 each year Site owner insurance is available to all active sections for free Each site owner insurance certificate covers only a single site launch 138 field or meeting room NAR insurance covers only activities that are conducted in accordance with the NAR safety code using NAR certified motors It provides 2 million aggregate liability coverage for damages from bodily injury or property damage claims resulting from sport rocket activities such as launches meetings or classes and 1 million coverage for fire damage to the launch site It is primary above any other insurance you may have References NFPA Code 495 Explosives Materials Code National Fire Protection Association 1 Batterymarch Park Quincy MA 02269 NFPA Code 1122 Code for Model Rocketry NFPA Code 1127 Code for High Power Rocketry Code of Federal Regulations Title 14 Part 101 Federal Aviation Regulations by the FAA for unmanned rockets Code of Federal Regulation Title 16 Part 1500 85 a 8 Consumer Product Safety Commission exemption for model rockets Code of Federal Regulations Title 27 Part 55 Bureau of Alcohol Tobacco and Firearms regulations Code of Federal Regulations Title 49 Parts 170 177 Department of Transportation hazardous material shipping regulations Model Rocket Safety Code National Association of Rocketry High Power Rocketry Safety Code National A
205. to determine if it can successfully insert a wire into the dummy rocket 10 of the 10 rounds must result in successful wire insertion Although the power consumed by the igniter insertion device will be miniscule by comparison to the rest of the AGSE components it will still be measured and analyzed to ensure compatibility Once all three components of the AGSE have been deemed fully functional they will be tested together to mimic the actual scenario First the Scorbot will insert the payload into the payload bay The rocket will then seal the payload bay The tower structure will then erect the rocket 76 When the rocket sled is locked into place the igniter insertion device will insert the igniter into a dummy motor that has been temporarily placed within the rocket All aspects of the AGSE including the safety functions and status indicator lights will be tested during this phase This process must be completed successfully at least 10 times in order to deem the AGSE compliant with all requirements and ready for use with a live rocket 4 5 AGSE Integration 4 5 1 Integration Plan components of the AGSE will be controlled via a laptop computer running MATLAB and by extension a switch box with three buttons The first button will control the power supply to all elements of the AGSE The second button will activate the AGSE payload insertion and rocket erection process The third button will temporarily terminate all functions of the A
206. to do there and build a relationship with him just as you did with the land owner The fact that NAR rocketry is recognized and its safety and launch site requirements are codified in Codes 1122 Model Rockets and 1127 High Power Rockets by the National Fire Protection Association will be a very powerful part of your discussion with any fire marshal Airspace Clearance The Federal Aviation Administration FAA has jurisdiction over the airspace of the U S and whatever flies in it Their regulations concerning who may use it and under what conditions are known as the Federal Aviation Regulations FAR which are also called Title 14 of the Code of 136 Federal Regulations 14 CFR Chapter 1 Subchapter F Part 101 of these regulations 14 101 1 specifically exempts model rockets that weigh 16 ounces or less and have 4 ounces or less of propellant from FAA regulation as long as they are operated in a manner that does not create a hazard to persons property or other aircraft When operated in this safe manner model rockets may be flown in any airspace at any time and at any distance from an airport without prior FAA approval Rockets larger than these specific limits i e all high power rockets are referred to as unmanned rockets by the FARs and are subject to very specific regulations Such rockets may not be flown in controlled airspace which is extensive in the U S even at low altitudes and includes all airspace
207. to produce anywhere from 26 to 1214 lb ft of torque and has a durable 20 1 ratio gearbox The motor itself weighs 14 4 pounds The amplifier selected for use is an HDC2450 Motor 68 Controller This amplifier is capable of controlling the NPC T74 motor and be programmed in the field if need be The HDC2450 comes with all necessary equipment for operation and can be controlled using the AGSE s laptop computer This amplifier is compact and light weighing just 3 3 pounds The challenge of using this subsystem lies within being able to halt the motor s rotation when the rocket has reached the launch position The most probable solution will be recording the number of cycles completed by the motor during the time it takes to move the rocket from horizontal to 85 degrees This process will be repeated several times and the results will be averaged to create a standard number of cycles to use within the program The motor will be bolted to a detachable plate located on the aft portion of the tower structure shown in Figure 44 The plate will be held in place by 4 pins attached to the cross feet of the tower structure Figure 44 Motor Mount Drawing 4 2 3 Tower Sled The tower sled upon which the rocket is placed is comprised of inch aluminum sheet metal The sled is 13 feet long and 6 inches wide In order to maintain stability and prevent bending a 2 x 2 inch aluminum square tube 12 5 feet long is welded to the bottom of the sheet me
208. tron Learn about Pose Poor safety practices and lack of Medium Kedun equipment and power tool safety knowledge work with a Equipment partner Ensure that black powder is stored Black Powder Electronics armed too early or Medium High properly and that Misfire current near black powder excess powder is disposed of after launch Ensure proper Catastrophic storage and motor failure EEE Eo Hen transportation for the motor Ensure safety Failure to set up equipment check and follow planned M Low Medium proper launch flight path Eb procedures are followed 3 8 3 Environmental Concerns Navy Rockets does not have any environmental concerns that have been deemed likely to happen The team will ensure that materials are properly disposed of so that we do not damage the environment 3 9 AGSE Integration 3 9 1 Integration Plan 3 9 1 1 Payload to Rocket Body The payload section of the rocket is a main compartment of the rocket body Therefore it is critical that the payload section falls within any constraints placed on the rocket as a whole most notably size and mass and is co developed with the remainder of the rocket body The interface between the payload section and the remainder of the rocket consists of mechanical fasteners 61 such as brackets or bolts and epoxy The payload bay components are attached to support rods which are mounted through the aft bulkhead of the payload sec
209. und with nozzle pointing up Ignite motor electrically from a safe distance and walt 5 minutes before approaching Dispose of spent components trasn Product Packaging Dispose of used packaging materials In Inert trash Special Considerations Consult local regulations about disposal of explosive materials 166 MSDS ProX Rocket Motor Reload Kits Page 55 Version 202 Rasion Date Feb 2010 TDG Classification Class 1 4 Proper Shipping Name Articles Explosive N O S Mode Rocket Motors UN Number 0351 UN Classification Code 14C Packing Group u UN Packing Instruction 101 Shipping information USA IMO Proper Shipping Name Articles Explosive N O S Mode Rocket Motors UN Number 0351 UN Classification Code 14C DOT IMO Label Class 1 Explosive Division 1 4C Shipping Information IATA Proper Shipping Name Articles Explosive N O S Mode Rocket Motors UN Number 0351 UN Classification Code 14C 1 Labels Class 1 Explosive Division 1 4C Cargo Aircraft Only This product has been classified according to the hazard criteria of tne Canadian Controlled Products Regulations CPR and the MSDS contains of Me Information required by the CPR WHMIS Classification Not Controfed explosive Domestic Substance List DSL Status Ingredients are listed on Canada s DSL List Canadian Explosives Classification Class 725 This product Is an authorized explosive In Canada These
210. under an LEUP must thereafter be stored in a magazine that is under the control of an LEUP holder A Type 3 portable magazine or Type 4 indoor magazine described under NFPA Code 495 is required and it can be located in an attached garage must inspect such magazines 135 Federal permits can be obtained from using their Form 5400 13 5400 16 available from the ATF Distribution Center 7943 Angus CT Springfield VA 22153 These are issued only to U S citizens age 18 and older who have no record of conviction of felonies and who pass a background check conducted by the BATF This check includes a personal interview by a agent Launch Site Requirements The first requirement for any launch site is permission of the owner to use it for flying rockets Use of land even public property without permission is usually illegal and always a bad way for a NAR member to demonstrate responsible citizenship The NAR will issue site owner insurance to chartered sections to cover landowners against liability for rocket flying accidents on their property such insurance is normally required The NAR safety codes and NFPA Codes establish some minimum requirements for the size and surroundings of launch sites Model rocket launch sites must have minimum dimensions which depend on the rocket s motor power as specified in Rule 7 of the model rocket safety code and its accompanying table The site within these dime
211. ure the tube was completely centered while it was inserted into the rocket Each centering ring is 0 125 inches thick of the G10 Epoxy Glass The motor mount can be seen in Figure 13 Figure 13 Mount Mount The carbon fiber tube will hold the motor and its casing and at the bottom end be secured by a twist on bolt for a cap to ensure that the motor does not separate from the body shown in Figure 14 The fins will be secured by epoxy onto the motor mount in between the two centering rings This motor mount section will then be able to be inserted into the bottom of the main body section through slits have were individually cut for the fins Since each fin will be 0 125 inches the slits will only be slightly larger to allow the fins to be inserted The mount will be secured with epoxy to the body tube 26 Figure 14 Motor Retention System 3 2 1 4 Section Securement Couplers were fabricated from 4 inch inner diameter PVC pipe couplers shown in Figure 15 The pieces were turned on a lathe and reduced in outer diameter until a custom fit was reached for each composite tube G10 Epoxy Glass bulkheads with installed 1 inch eye bolts were secured inside each coupler using composite epoxy Couplers were then installed in the appropriate composite tubes using composite epoxy Figure 15 PVC Couplers Installed 27 3 2 2 Electrical Elements The only electrical systems in the rocket are the avionics and payload sections The electric
212. ville Rd Ont oon LOH 1G0 Telephone Numbers Product Information 1 905 887 2370 24 Hour Emergency Telephone Number 1 613 926 6666 CANUTEC 20 COMPOSITION INFORMATION ON INGREDIENTS 10294 40 3 31 32 7430 95 4 42 43 26 27 of when i uaa propellant motor All explosives are dangerous must metam ot a eet or wen procedures under the direction of competent personnel in accordance with applicable federal state and local laws and General Appearance Cardboard tubes containing one igniter Igniter has coiled wire leads terminating in the ignition device itself Ignition device consists of a small electrical initiator fuse head dipped in a rubbery silver grey composition parts are essentially odourless solids though trace odors of process solvents may be present Potential Health Effects Not a likely route of exposure May cause eye irritation a Low hazard for usual industrial handling pea Inhalation Not a likely route of exposure May cause respiratory tract irritation 174 PAGE 1 of 4 Fiberglass Cloth CARGROOM RETAIL U S Chemical amp Plastics For Chemical Emergency Alco Industries Companies 600 Nova Drive SE CHEMTREC 1 800 424 9300 Massillon OH 44646 PH 330 830 6000 FAX 330 830 6005 SECTIONI IDENTIFICATION OF PRODUCT PRODUCT NAME FIBERGLASS CLOTH PRODUCT CODE 77080 SYNONYM CROSS REFERENCE Continuous Filament Fiberg
213. wder for each charge is calculated as 1 575 grams 1 50 rounded and 0 99 grams 0 50 rounded This amount of black powder is the baseline test to ensure that the nylon shear pins that hold the sections together are sheared and the sections fully separate However after testing the full scale recovery system it was found that to ensure full separation of the sections these amounts needed to be doubled Table 6 Black Powder Charge Calculations A Drogue B Main Dcompartment 1n 5 0 5 0 LCompartment in 35 0 22 0 Calculated Amount g 1 575 0 99 Experimental Amount g 3 0 2 0 To prevent any damage to the parachutes from the ejection charge 2 18 inch Nomex fire resistant protective barriers will be utilized One will be placed along the harness in the drogue assembly while the other will be placed along the harness in the main parachute assembly Also each ejection charge will be topped with a different colored powder paint to identify which charge pressurized during deployment 3 4 4 Recovery Schematic The two recovery configurations following the two ejection events can be seen in Figure 25 Note All components are to scale with exception of the recovery harness lengths which were shortened in Solid Works to provide productive figures Also shoulders between sections and the nylon shear pins are not displayed 41 Figure 25 The Launch Vehicle in Recovery Configurations after Ejection Event 1 left and Ejection Event
214. witches the black powder charges and the avionics themselves are fully redundant With regards to the recovery hardware each item has been carefully selected for either its flight heritage in the case of the ejection canisters and altimeters or has a significant margin of error in its rated strengths The 5 16 inch Type316 Stainless Steel eyebolts are rated for a 1000 pound working load and the tubular nylon harness is rated for 1500 pounds of tensile force Each eyebolt was epoxied shut to increase its working load and will be epoxied in place with its backing nut and a locking washer to ensure neither back out The main and payload parachutes will be supporting close to half their maximum loads of 28 and 19 pounds respectively With regards to safety the single item that needs mention is the black powder charge The canisters will be loaded last as a safety precaution and the master switch prevents any accidental discharge before continuity When the black powder is finally loaded all other team members will be at safe distance and all safety precautions will be met 3 5 Propulsion 3 5 1 Final Rocket Motor Selection The selection of the motor was dominated by three principle factors impulse diameter and apogee The length and impulse of the motor were first looked at As long as the total impulse was kept under the required 5120 N s or a maximum of an L class motor any motor could be used The second constraint of motor diameter was
215. within the 2500 foot drift mark The new diameter parachute for the main body will become 50 in The new descent speed will thus cause the total kinetic energy to become 67 6 ft lbs within the 75 ft lb margin while the new wind drift will become 2430 ft as modeled in Open Rocket 56 3 7 Vehicle Verification 3 7 1 Wind Tunnel Testing In an effort to model the static and dynamic stability of the rocket during flight a scale model of the rocket was constructed and tested on a sting balance in the open loop open return Eiffel wind tunnel located at the United States Naval Academy This scale model consisted of multiple different materials The functional test plan can be found in Appendix C 3 7 1 1 Nose Cone The nose cone was 3D printed in order to create 10 15 pressure ports along the leading edge of the rocket It was determined that additive printing was the only plausible way to create tunnels inside the nose cone to determine pressure The idea was the pressure port at the leading edge PP1 will be tunneled to a point at the bottom of the nose cone that will be inside the PVC section This tunnel would allow the pressure to be measured at PP1 using a standard pressure measurement tool inside the body of the PVC pipe However the material the nose cone was printed with was porous and could not hold pressure through the tunnels 3 7 1 2 Body Section The body section of the test model was made of Polyvinyl chloride PVC The body was
216. xists Wash spili residue with warm soapy water If necessary STORAGE TEMPERATURE 40 F 4 C 90 F 32 dc caet MEM Keep HANDLING PRECAUTIONS s Use with adequate ventilation Do not breath vapors or mists from heated material Avoid exposure to concentrated vapors Avoid skin contact Wash thoroughly after handling When mixed wih epoxy resin fnis product causes an exothermic reaction which In large masses can produce enough Neat to damage or Ignite surrounding materials and emit fumes and vapors that vary widely In compostion and toxicity EYE PROTECTION GUIDELINES Chemical splash proof goggles or tace shield SKIN PROTECTION s Wear liqu d proof chemical resistant gloves nitrtle buty rubber neoprene uty rubber or natural rubber and full body covering clothing RESPIRATORYIVENTILATION GUIDELINES Use with adequate general and local exhaust ventilation to meet exposure limits In poorly ventilated areas use a NIOSH MSHA approved respirator with an organic vapor cartridge Note West System Inc has conducted an air sampling study using this product or similarly formulated products The results indicate that the components sampled for phenol formaldehyde and amines were elther so low that they were not detected at all or they were well below OSHA s permissible exposure levels ADDITIONAL PROTECTIVE MEASURES
217. y oriented chain system The Scorbot will be placed on the ground adjacent to the payload bay area All components will then be connected to their respective power source and powered on All subsystems will be tested to ensure that they are functioning correctly Following this the rocket sled will be detached from the tower and the rocket will be fed into the launch rail on the rocket sled The rocket sled will then be reattached to the tower and the payload bay will be opened The sample will then be placed on the ground beneath the Scorbot gripper Ensure Scorbot is powered on Enable the homing function from the command laptop Set waypoints Test waypoints without payload to ensure full range of motion and gripper capabilities Spray gate latches on the tower with lubricant Make sure tower motor has power Make sure igniter insertion device has power Make sure all RF units have power Make sure exposed portion of igniter wire is not bent or broken SOOO SON ee ONS 5 1 6 Igniter Installation Once the rest of the AGSE is assembled the igniter insertion device will be in place since it is attached to the base of the rocket sled It will be verified that the igniter insertion device is properly aligned with the center of the rocket motor bore The igniter insertion device with its linear actuator will be tested in place on the AGSE for proper operation Once proper operation 84 is ensured the igniter insertion device will be

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