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ESABASE2 Debris Software User Manual

1. E El El E El Explosion Fragments Figure 2 8 Debris input editor main tab Model Selection MASTER 2005 The MASTER 2005 options are similar to the MASTER 2001 options see previous subsubsec tion The following differences have to be noted e Collision and explosion fragments cover both historic and future populations not only historic populations as in MASTER 2001 o This also explains why the Fragments historic option has vanished in com parison to MASTER 2001 Like MASTER 2001 MASTER 2005 covers altitudes from 186 km to 37000 km The future is from 2005 05 01 and in the future objects lt 1 mm are not considered The population snapshots of the May 1 of the mission start year are used for the analysis Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 22 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 2 1 1 3 Debris model MASTER 2009 MASTER 2009 23 is ESA s meteoroid and space debris reference model and the successor of MASTER 2005 see previous subsubsection When you click on the Edit button a dialog with MASTER 2009 input parameters will open as show in the following figure Debris Model MASTER 2009 Options Debris density for constant density gcro 3 P S Launch and mission rel objects Nak droplets SAM slag partic
2. mm MISC RNENSE 0 56 52 El Et member of the ckc group ESABASE2 Debris Software User Manual Contract No Title ESA Technical Officer Prime Contractor Authors Date Reference Revision Status Confidentiality etamax space GmbH Frankfurter Str 3 d D 38122 Braunschweig Germany Tel 49 0 531 866688 30 Fax 49 0 531 866688 99 email esabase2 etamax de http www etamax de 16852 02 NL JA PC Version of DEBRIS Impact Analysis Tool G Drolshagen J S rensen etamax space GmbH K Ruhl K D Bunte A Gaede A Miller 2013 11 07 RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris doc 1 5 2 Final etamax space GmbH El Table of Contents member of the ckc group Document InforMatiON cmcccnccncnncnncnncnnnncnncnn ron none nan rnarnannaas 4 l Release NOte viicscccccccnccenccunccucccusucunueusueusacusaueesueususesusesusesusesusesugususesagesugengs 4 IL REVISION FISTOTY axdcaacoccctsnaccsaaceonncandrevensdesanenetnses sine saeeceteeancavadoeeeiatonneseans 4 TE Distribution ia 4 IV List Of REFEFENCES ccccccscccccescecccusceccuuscecceuaneaceuaeuscecauevscucueususuuesnescuusnesaauags 5 A E 0 11s E E 7 VI List of ADDreviatiONs ccccccsccccccccescecccuccecucuscecucuscucueuscusuuuenusceusgescuusnesuauags 8 VIE LAGE OE PUSS aan 9 DERE POC UCC OM wincworeunaswanewansieveususuenauuneuavauunuvenvinuiuccutiusedsucundvivuntvuneseuuveserenee 11 2 DEDMS SOIVO Sian 12
3. Choose between line bar and scatter chart e Series lt num gt o Linecolour Linewidth Color and width of the line of this data series o Stroke Type of the line of this data series e Range Set the X and Y range that the chart covers 2 4 2 2 2D Charts Image Export Pressing the Export Image button opens a file dialog asking for a location to save to PNG and JPG format are possible The size of the image is the same as it is currently shown re size the application window to get other image sizes Date 2013 11 07 ESABASE2 Debris Revision 152 Software User Manual State Final Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc Page 60 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 4 2 3 2D Charts Show Report The chart can be embedded into a print ready report press the Show Report button to invoke it After a dialog asking for a comment line has been confirmed a report as shown in the following figure will appear in a popup window 2 Esabase2 Debris Report Print Preview Report Export View Help a IRA ESABASE 2 Debris MASTER 2005 flux vs velocity orbital point 01 User Text by Kai Ruhl Table Graph Attributes Attribute Name Velocity km s Flux 1ime 24r scaling LINE AR LINE AR Minimum 0 0 0 0 Maximum 4 7375 766398105621 3375 Figure Chart 20 MASTER 2005 flux vs velocity orbital point 01 Figure 2 42 Debris
4. Input Parameters Wisualisation Angle deg Min 0 0 Max 69 0 Nb of steps 110 Angle deg 4 0 Particle density g cm 3 Min 5 Max 11 5 Mb of steps E Velocity kms 0 0 velocity km s Min 20 0 Max 30 0 Mb of steps 110 velocity km s 10 oo 5 Fun D ebris Ground Test Nor G eometric Analysis Figure 2 24 Debris input editor Ground Test tab The ground test option enables you to run the damage equations on their own outside of the ESABASE2 Debris analysis its purpose is to test and preview the results of the damage equations The following sections are available e Ground Test Choose damage type ballistic limit or crater size and shielding type Wall_1 to Wall_15 To define the wall configuration see section 2 2 1 4 e Shielding Parameters Choose shield thickness and density and spacing in case of double walls e Input Parameters Impact angle density velocity and diameter can be specified ei ther as single values or as arrays of values Each variable has three parameters the minimum value the maximum value and the number of steps For single shots only the minimum parameter is used For tabled data when the variable is used as x axis or y curve parameter all three parameters are used e Visualisation Choose the axis on the result graph Unlike the normal Debris analyses the ground test can be performed directly within the De bris input editor for this purpose press the Ru
5. The default is from 0 to 20 km s Please note that the NASA90 model is restricted to orbital altitudes below 1000km Date 2013 11 07 ESABASE2 Debris Revision 152 Software User Manual State Final Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc Page 24 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 2 1 1 5 Debris model ORDEM 2000 ORDEM2000 15 is a debris model developed by NASA it is the successor of NASA96 which in turn followed NASA9O The model describes the orbital debris environment in the low earth orbit region between 200 km and 2000 km altitude The only user editable input parameter is the assumed debris material density default 2 8 g cm as shown in the figure below Debris Model ORDEMZOO0 Options Debris density For constant density gfcn3 2 8 ok Figure 2 11 Debris input editor main tab model selection ORDEM 2000 ORDEM 2000 is appropriate for engineering solutions requiring knowledge and estimates of the orbital debris environment debris spatial density flux etc The model includes a large set of observational data both in situ and ground based covering the object size range from 10 um to 10 m The analytical technique uses a maximum likelihood estimator to convert observations into debris population probability distribution functions these functions then form the basis of the debris populations A finite ele
6. When user cam is called with x 126 1 it is to be used as a ballistic limit equation if xrrac 2 it is to be used as a crater hole equation Thus one subroutine can cover both types of equation It is possible to add further subroutines in the file user dam which are called by the main user subroutine user bam Thus the advanced user can build his own library of damage equations In case of persisting issues please contact the ESABASE2 development team using the email address provided on the website 3 To apply the subroutine to the entire model choose User Subroutine as damage equation in the Debris input editor as described above subsection 2 2 1 4 To apply it only to parts of the S C geometry go to the geometry editor modify a shape via wizard and on the De bris page choose User Subroutine as shield type see also section 2 1 ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 39 74 El member of the ckc group 2 2 2 Debris Ground Test Tab At the bottom of the Debris input editor the second tab leads to the Ground Test page which is depicted in the figure below AE debris ES A Ground Test Shielding Parameters penne EEE eee eee RE Fr i A z 3 7 uo Thickness 1 0 l cm Density 27 giem
7. 000000834826 1 399999976158142 0 24123288691043854 a 30 000000834826 1 399999976158142 0 19909483194351196 0 100 30 000000834826 1 399999976158142 0 173741415143013 E 30 000000834826 1 399999976158142 0 1563212275505066 0 075 30 000000834826 1 399999976158142 0 1433926373720169 0 050 0 025 0 000 0 5 10 15 20 25 30 35 40 Velocity km s 1 1 5 2 25 3 3 5 Density g cm 3 30 000000834826 39 99999883637168 39 99999883637168 39 999995883637168 39 99999883637168 39 99999883637168 39 99999883637165 49 999996837917 49 999996837917 49 999996837917 49 ao0006827017 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 399999976158142 1 2000000715214 0 13329951465129852 0 292770342962265 0 24163644015789032 0 21086564660072327 0 1897231936454773 0 1740320771932602 0 16173229451179504 0 3861951231956482 0 31873536109924316 0 27814653515815735 an PENPER1APTIFE 229 Figure 2 25 Debris input editor Ground Test tab Run Graph and table show the same results ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 41 74 El member of the ckc group 2 2 3 Debris Non Geometric
8. 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 29 74 El member of the ckc group 2 2 1 1 10Jenniskens Stream Model The above meteoroid models are describing the background meteoroid flux the Jenniskens stream model adds annual meteoroid streams e g the Perseids The streams model can be used with or without another meteoroid model only for the analyses on Earth orbits When pressing the Edit button the dialog for the Jenniskens Stream Model input parame ters appears as shown in the figure below Streams Opkions File For Streams Astreams jen str Lower CUE OFF mass 0 0 ay Figure 2 16 Debris input editor main tab Model Selection Streams The streams and possible interstellar sources are defined in an external input file with a default jen str being provided by ESABASE2 File locations are always relative to the ESABASE2 installation path Meteoroid particles with less mass than the lower cut off mass are not considered in the analysis The Jenniskens stream model is based on observation data gathered over a 10 year period and can be applied to flux and damage analysis It also includes directional information on the streams Please note that for long mission durations the directional effect is smeared out and does not give any additional information than the Grun sporadic option The stream option is best suited for t
9. 42 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El e Orientation and area Specifies the plate size and its orientation or randomly tumbling property e Result Log Execution log of the analysis run former listing file member of the ckc group 2 2 3 1 Non Geometrical Analysis The following screenshot shows the Non Geometrical Analysis section for single left and multi wall right selection Non geometrical Analysis Non geometrical Analysis Shielding Tope Ml Shielding Type WA Thickness 01 cm Density 2 7 gcm Thickness 1st plate 10 1 em Density 1st plate 2 7 g cm 3 Thickness nd plate 01 i lcm Density nd plate 2 7 g cm 3 Space betwee 0 0 cm Figure 2 27 Debris input editor Non Geometric Analysis tab Single and Multi wall The input values correspond to the ones used in the geometry editor in the Debris page of the shape wizards see 2 1 2 2 3 2 Plate Orientation and Area The figure below shows the Plate Orientation and Area section within the Non Geometric Analysis tab Orientation and Area Orientation and Area Randomly Tumbling _ Randomly Tumbling Azimuth Angle 0 0 deg zenit Angle 0 0 deg Plate rea 1 0 m2 Plate rea 1 0 m2 Figure 2 28 Debris input editor Non Geometric Analysis tab Orientation and Area ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_Use
10. 48 apply Number of Orbital Points 16 0 apply Figure 3 3 Transfer orbit parameters The Figure 3 1 indicates that correction manoeuvres can be performed during the transfer Such case can also be modelled by defining different mission files with according orbits and durations before and after the manoeuvre 3 1 1 3 Target Orbit The target orbit is the desired trajectory around the Moon Polar tracks with low altitudes are often aimed lunar orbits Parameters for such orbit can be e Central body centre of motion Moon e Sami major axis 1838 km e Eccentricity 0 0 e Inclination 90 deg Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc Page 68 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group e Other angles 0 0 deg The starting epoch of this phase of the lunar mission is the end epoch of the previous phase January the 6 2013 at 0 00 As already mentioned this is only an example so let arbitrary say that the mission duration is one month thus the end date is February the 6 2013 at 0 00 The mission file can be created as described in 1 section 3 1 The filename 7argetOrbit will be used in the text to identify the orbit The Figure 3 4 show the mission editor with the pa rameters applied as introduced before Central body Orbit Type Semi major Axis Peri
11. 93 O 1059E 02 0 639 E 03 0 1555E 02 O 7914E 03 0 1553E 02 0 4476E 00 0 2 1 35 asa 0 88134E 01 0 7237 E 03 0 18508E 02 0 1031E 02 0 2475E 02 0 22721E 00 0 3 0 04 72 34 0 30889E 01 0 1574E 05 0 53864E 00 0 3071E 04 0 6142E 04 0 2645E 04 O0 4 1 53 26 50 0 5634E 01 0 5044E 03 0 2042E 02 0 1165E 02 O 2795E 02 0 2 656E 00 0 5 0 11 53 59 0 92444E 01 0 4645E 05 0 1466E 01 0 8360EFE 04 0 1003E 03 0 2778E 03 0 6 0 11 Bs dl 0 2214E 01 0 45290E 05 O 1469E 01 0 5494E 04 0 101929E 035 0 3152E 03 0 Iv i T o Motes Listings 30 Results 20 Results Figure 2 43 Debris result editor 2D results listings In the result log you can see the different LIS files just select the appropriate LIS entry in the combo box For Debris Meteoroid Deb Met you can jump to orbital point bookmarks using the second combo box The following LIS files are available e Crater vs Crater size e Deb Met Debris Meteoroid e Failures vs Ballistic Limit e Kinematic e Orbit Detailed information about the contents of the listing files can be found in the original ESABASE user manual 4 Date 2013 11 07 ESABASE2 Debris Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 62 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El Please note The listing files are foremost saved as data nodes in the debris result file Addi tionally they are written in ASCII format to
12. A damage equation determines the size of the crater or hole depending on no penetration penetration on the first wall shield More information can be found in the ESABASE2 Debris technical description 2 and in the IADC Protection Manual 21 Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 14 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 1 2 Meshing Page Although the meshing page shown below is the same for all solvers the effects of the set tings may vary E Shape Wizard Meshing Box Size Meshing Position amp Attitude Kinematic Pointing Debris Comova Material Subdivison of the shape s boundary surface into node areas na 1 nb 1 nc 1 Number of elements on a axis b axis c axis Ray Tracing Ray tracing weighting Factor Active Side default v default both Colour positive negative none Figure 2 3 Geometry editor Meshing page Subdivisions of surfaces i e Surface nodes are not supported by Debris We recommend using the Number of elements on settings for finer meshing Regarding active sides Debris results always comprise both sides of an element the solver sums them up For volumes this is uncritical because only one side is ever affected For surfacic shapes e g plate we recomme
13. Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 32 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 2 1 2 Size Boundaries The figure below shows the Size Boundaries section of the main tab in the Debris input edi tor In this section you specify limits on the type of Debris or Meteoroids to be used in the analysis Size Boundaries Lower particle diameter 0 0010 cm Upper particle diameter 100 0 crn Min crater diameter 4 0010 crn Min eject Fragments 0 0010 crn Figure 2 19 Debris input editor main tab Size Boundaries At the top the minimum and maximum particle size limits can be input as mass g or di ameter cm The conversion between mass and diameter assumes spherical particles At the bottom the minimum crater diameter and ejecta fragment size are defined in cm Below these size limits crater or ejecta fragment are not further considered in the analysis ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 33 74 El member of the ckc group 2 2 1 3 Ray Tracing Ray tracing is the primary technique in ESABASE2 to determine whether Debris or Meteor oids hit the spacecraft geometry at a
14. ESABASE2 Debris Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 18 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 2 1 1 1 Debris model MASTER 2001 MASTER 2001 11 is the 2001 version of ESA s meteoroid and space debris reference model it is the forerunner of MASTER 2005 see next subsubsection When you click on the Edit button a dialog with MASTER 2001 input parameters will open as shown in the fol lowing figure Debris Model MASTER 2001 Options Debris density For constant density gfcm3 2 6 Launch and mission rel objects Fragments historic population only Mak droplets SRM slag particles SRM Al203 dust historic population only Paint Flakes historic population only Ejecta historic population only Collision Fragments Future population only Explosion Fragments future population only a Figure 2 6 Debris input editor main tab Model Selection MASTER 2001 Apart from the assumed debris density default 2 8 g cm as material mix average the MASTER 2001 model is based on numerical modelling of various population sources which can be included or excluded from an analysis e Launch and mission related objects payloads and satellites upper stages support structures These are mostly larger trackable objects o Note that the Westford needles experiment is
15. ESABASE2 is written in Fortran 77 ANSI C and Java 6 The GUI is built on top of the Eclipse rich client platform with 3D visualisation and STEP import realised by Open CASCADE Report and graphs are based on the JFreeReport JFreeChart libraries This user manual is the Debris handbook It complements the Framework user manual 1 which explains the common functionality of all solvers e g Debris Sunlight Atmos phere Ionosphere or COMOVA ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 11 74 El member of the ckc group 2 Debris Solver After we have specified mission and spacecraft geometry 1 the next step is to perform space environment analyses with these One of the available solvers ESABASE2 Debris per forms debris and meteoroid analyses within the framework Five space debris models NASA90 16 ORDEM2000 15 MASTER 2001 11 MASTER 2005 19 and MASTER 2009 23 as well as four meteoroid models Gr n 14 Divine Staubach 13 18 and MEM 20 respective LunarMEM 25 are currently available for flux and damage analysis For detailed information on the technical background of the space debris and micro meteoroid simulation please refer to the ESABASE2 Debris technical description 2 This debris solver chapter is structur
16. Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 53 74 El member of the ckc group 2 4 1 2 Orbital Point When the debris result editor opens it shows the analysis results for the entire mission You can also view the results for each orbital point or for the orbital arc Open the context menu and navigate to Orbital Point as shown in the following figure E Landsat _debris result 2009 07 06 16 41 06 E3 2 00 HG amp G Total Impact Flux 1 m2 year Orbital Point 4 Colour i Coordinate Systems P Orbital Arc Orbital Point 1 Orbital Point 2 Orbital Point 3 Orbital Point 4 Notes Listings 30 Results 20 Results Figure 2 37 Debris result editor 3D Results Orbital Point context menu Choose one of the following e Mission The entire mission duration e Orbital Arc One orbital arc only e One of the orbital points Results at a dedicated orbital point When you select an orbital point then Earth Sun and velocity direction are shown as de picted above Note that the correct pointing e g solar panel aligned towards the Sun can only be shown at the orbital points not for the whole mission or orbital arc Page 54 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 4 1 3 Coordinate Systems To visualise the coordinate system you used in the geometry editor change the coordinate system by opening the context menu
17. Krag R Walker P Wegener and C Wiedemann Upgrade of the ESA MASTER Space Debris and Meteoroid Environment Model Final Report ESA ESOC Contract 14710 00 D HK Sep 2002 10 Bunte K D ESABASE Debris Release 3 Technical Description ESA ESTEC Contract 15206 01 NL ND Upgrade of ESABASE Debris etamax space Sep 2002 11 Bunte K D ESABASE Debris Release 3 Software User Manual R0O33_r020 ESA ESTEC Contract 15206 01 NL ND etamax space Sep 2002 12 Cour Palais B G Meteoroid Environment Model 1969 NASA SP 8013 NASA JSC Houston TX 1969 13 Divine N Five Populations of Interplanetary Meteoroids Journal of Geophysical Re search Vol 98 No E9 pp 17029 17048 September 25 1993 14 Grun E H A Zook H Fechtig R H Giese Collisional Balance of the Meteoritic Complex Icarus 62 pp 244 277 1985 15 Liou J C M J Matney P D Anz Meador D Kessler M Jansen J R Theall The New NASA Orbital Debris Engineering Model ORDEM2000 NASA TP 2002 210780 NASA May 2002 ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 5 74 El 16 17 18 19 20 21 22 23 24 25 Date Revision State Page 6 74 member of the ckc group Kessler D J R C Reynolds P D Anz M
18. Moon part of the orbit shall be used Additionally to the missing equivalent for the lunar trajectories the Divine Staubach model application is limited to 1000 km above the geosynchronous orbit If the Grun model is applied for the analysis of a lunar mission it is recommended to use the Taylor HRMP velocity distribution It provides the most reasonable results compared with other models The Figure 3 6 shows the activation of the Taylor HRMP velocity distribution for the Grun model via the Edit button The available NASA90 velocity distribution is designed for the vicinity of the Earth The consideration of the focusing effect of the celestial body for constant velocity disregards the gravity constant of the body This leads to overestimation of the flux for lunar orbits Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 72 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group Model Selection Meteoroid Model Analysis Type meteoroid analysis e Gruen Options Debris Model Meteoroid Model Gruen Meteoroid density For constant density g cr3 1 0 C streams Meteoroid density model Constant Dalphaffeta Separation Meteoroid velocity model Taylor HAMP e Mie haenen Constant meteoroid impact velocity const velocity only kms 17 0 i Minimum meteor
19. S C geometry and depending on the number of orbital points an analysis might take a long time i e several hours Progress Information Running MASTER 005 Figure 2 32 Geometric Debris analysis Progress bar After the run a debris result file will be created in your workspace and it will be automati cally opened If you are interested in its contents skip to section 2 4 otherwise the follow ing subsection will explain the non geometric debris analysis Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 48 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 3 2 Non geometric Debris Analysis The non geometric analysis uses a simple plate instead of a full spacecraft geometry it is therefore considerably faster As in the geometric debris analysis locate the Run button and this time choose Run non geometric Debris Analysis The following figure shows the Run wizard for the non geometric debris analysis 2 Non Geometric Debris Analysis Non Geometric Debris Analysis Please choose the input File For the analysis Project debris_testing Debris test uritc 5 061M20054 05 Mission test uritc_ 5 061155 Report options Complete listing of all Figure 2 33 Non geometric Debris analysis Run wizard Compared to the geometric Debris analysis this wiz
20. a A A a a E SS nn a a A a Input Output Variable declaration INTEGER KFLAG REAL VPART DPART ALFA RHOP TB RHOB TS RHOS SPACE X_OUT REAL D USREQ 14 USER_DAM internal variables REAL VNORM Normal impact velocity FMAX Ballistic limit normalised to Dp Lambda XDUM Dummy variable c Specification of d_usreq 1 14 D_USREO 1 1 000 D USREQ 2 0 33d0 D USREQ 3 2 0d0 D USREQ 4 0 667d0 D USREQ 5 1 0d0 D USREQ 6 0 33d0 D USREQ 7 2 040 D_USREQ 8 0 667d0 D USREQ 9 1 0d0 D USREQO 10 0 3300 D USREQ 11 2 0d0 D USREQ 12 0 667d0 D USREQ 13 1 0d0 D_USREQ 14 0 33d0 VNORM VPART COS ALFA IF KFLAG EQ 2 THEN C Crater size equation XDUM DPART 1 056 RHOP 0 519 VNORM 0 66667 X OUT D_USREQ 11 D_USREQ 12 XDUM ELSE C Ballistic limit equation FMAX D USREQ 13 D_USREQ 14 RHOP 0 519 VNORM 0 66667 X OUT TB FMAX 0 947 END IF RETURN END E a ee eof Figure 2 23 Example user subroutine ESABASE2 Debris Software User Manual Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El After the variables specification a block containing 14 parameters can be defined for the user damage equation member of the ckc group The user sub routine must be named user damn The flag xriac indicates how the subroutine is called
21. for individual points of in terests can be extracted from the results If only a part of a transfer orbit is considered and analysed using MASTER 2009 the desired results shall be extracted from the orbital points included in the arc Summarising the properties of the debris models it can be concluded that MASTER 2009 is the preferable choice due to its actuality and the range of validity for the abstracted lunar mission If the transfer orbit is represented by only one mission file as in 7ransferOrbit then also MASTER 2005 can be used which show a better performance If the transfer trajectory is represented by multiple mission files then MASTER 2009 shall be used and the results of individual orbital points included in the considered arc shall be combined to achieve the de sired result for the arc 3 2 1 2 Meteoroid Models The ESABASE2 Debris application allows the use of four alternative meteoroid models Grun Divine Staubach MEM and LunarMEM But the four can be reduced to three because LunarMEM is a MEM version tailored to the vicinity of the Moon For the analysis of orbits around the Earth the models Grun Divine Staubach and MEM are available For the analysis of lunar trajectories Gr n and LunarMEM are available To achieve coherent results for the whole track the models used for Earth and Moon vicinities shall be also coherent Therefore either Grun model for both Earth and Moon part of the orbit or MEM for Earth and LunarMEM for
22. limit instead of crater size of the back wall It uses the same principle and definition of the thresholds ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 63 74 member of the ckc group 2 4 4 Notes The figure below shows the Notes tab within the Debris result editor E Landsat _debris result 2009 07 06 16 41 06 E Here you can enter notes for this result file Figure 2 45 Debris result editor 2D Results notes It consists of a simple text area where you can write your notes concerning the debris re sults Your text will be saved and is available to whomever you may send the file Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 64 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 3 Lunar Mission Debris Analysis The intention of this chapter is to provide a small overview how a debris analysis for lunar mission can be performed An Capture Orbit at 1000km Capture Orbita mn at 1000krn moon A dl A Elliptical ZN i Transfer F B Y Orbit Final Lunar i oOrbit100km a E Lunar Orbit E initial 200km Elliptical Mid Course Parking l Correc
23. specific orbital point Below you can see a screenshot of the Ray Tracing section in the main tab Ray Tracing Primary rays 100 Secondary rays O Secondary ray jump 1 Figure 2 20 Debris input editor main tab Ray Tracing The Primary rays parameter governs the number of primary rays to be fired per element For ESABASE geometric models at least 250 rays per element are recommended for non geometric analyses 1000 rays In the middle the Secondary rays parameter specifies the number of secondary rays to be fired from each impact point Due to the high computational effort caused by this option it is recommended to choose fairly low values lt 100 Another option to reduce computation time is to specify a Secondary ray jump which causes the program to skip the respective number of secondary rays Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 34 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 2 1 4 Damage Model Up to 15 different damage models can be defined for damage assessment Each model is defined by two types of damage equations which are used during the analysis e The ballistic limit equations or failure equation which deliver the limit impactor di ameter above which a structural failure of the analysed surface occurs This limi
24. usersubroutine a11 Dynamic Linked Library located in the re lease dlls directory of the installation as shown in the figure below Ordner x Name S ESABASE2_2 0 0_2009 07 02 S DFORMD DLL components A E2 DatalibFacade dll configuration 2 E2 EsabaseAtomox dil 5 logs S Ez EsabaseDebris dl H plugins 2 E2_Usersubroutime dll D release dlls 3 odious dll fy Solver 5 logdexx dl workspace 2 meso dl Figure 2 22 Finding the User subroutine DLL ESABASE2 2 0 0 uses the Compaq Visual Fortran 6 compiler It is highly advisable to use the same compiler Also while it is possible to use other languages e g C to produce the subroutine DLL compiler issues frequently occur Please note When writing your own user subroutine in Fortran take care to initialise all variables otherwise results can be erratic As a starting point look at the Fortran file user_dam f in the Debris plugin directory plugins eu esa estec esabase2005 debris 2 0 0 user subroutine A simple example file is shown in Figure 2 23 ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 37 74 etaycigik Date Revision State Page 38 74 member of the ckc group 2013 11 07 1 5 2 Final c lt kdb etama C GMAC COCQUQA QOO TQT OQOQA QOQ OGO
25. y marie x Wall o wars Srgewar y marine y Wall 11 Watt smge wat y mPa v Wall 13 WALI smge Wat y Thek Pie V Wall 14 wal ia Sre wai y Trek Fle y Wall 15 WALS rewal x mero 3 Debris Ground Test Non Geometric Analysis lt lt lt Secondary rays lo Secondary ray jump ET Damage Equation Crater Size Thick Plate v Crater Size Thick Plate w Crater Size Thick Plate v Thick Plate v Thick Plate v Thick Plate v Figure 2 4 Debris input editor main tab At the bottom of the editor you can see the Debris Ground Test and Non Geometric Analysis tabs This subsection is concerned with the main Debris tab In the following the four sections of the main tab will be explained ESABASE2 Debris Software User Manual Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Date 2013 11 07 Revision 1 5 2 State Final Page 17 74 El member of the ckc group 2 2 1 1 Model selection Your first decision is which debris and meteoroid models you want to use The following fig ure shows the model selection block within the Debris main tab Model Selection Analysis Type debris and meteoroid analysis e Debris Model MASTER 2005 Meteoroid Model Divine Staubach e F Streams Alpha Beta Separation Apex Enhancement Figure 2 5 Debris input edi
26. yr Pz DJ E tt Dl U0 25 50 78 100 125 1580 175 200 225 250 275 300 325 35 0 375 400 Velocity km s Notes Listings 3D Results 20 Results Figure 2 40 Debris result editor 2D Results In the combo box on the top left you can select the chart you want to see Which charts are available depends on the debris meteoroid model used for the analysis as shown in the fol lowing table Debris meteor Flux distributions oid model NASA9O F f d valid for all orbital points MASTER 2001 F f d F f azimuth F f elevation F f velocity for each orbital point MASTER 2005 F f d F f azimuth F f elevation F f velocity for each orbital point MASTER 2009 F f d F f azimuth F f elevation F f velocity for each orbital point ORDEM2000 F f d F f azimuth for each orbital point ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 57 74 El member of the ckc group Debris meteor Flux distributions oid model Gr n sd f m valid for all orbital points Divine Staubach F f d F f azimuth F f elevation for each orbital point MEM F f m F f azimuth F f elevation F f velocity for each orbital point LunarMEM F f m F f azimuth F f elevation F f velocity for
27. 20 Consequently his toric missions e g LDEF and future missions can be analysed using realistic population snapshots The population snapshots of the May 1 of the mission start year are used for the analysis For the future evolution of the space debris environment the following assumptions have been applied e continuation of space activity launches explosions solid rocket motor firings at the same rate as in the recent past e no new Satellite constellations deployed e no implementation of debris mitigation measures This corresponds to the MASTER 2001 future reference scenario ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 21 74 El 2 2 1 1 2 Debris model MASTER 2005 MASTER 2005 19 is ESA s meteoroid and space debris reference model and the successor of MASTER 2001 see previous subsubsection When you click on the Edit button a dialog with MASTER 2005 input parameters will open as show in the following figure member of the ckc group Debris Model MASTER 2005 Options Debris density For constant density gfcn 3 2 8 Launch and mission rel objects Mak droplets SRM slag particles SRM 41203 dust historic population only Paint Flakes historic population only Ejecta historic population only Collision Fragments k e
28. 50 format thus a decimal value DDDDD d gt d UTC implies the use of the CCSDS ASCII time code A i e YYYY MM DDThh mm ss d gt d for the definition of the epochs member of the ckc group The body of the file provides the state vectors of the trajectory It must be placed behind the head and has to start with the key BEGIN If the key END is not found a warning is directed to the console view which states that the trajectory file could be incomplete but the analysis is continued The listed state vectors have to be preceded by the according epoch in the predefined for mat MJD or UTC and follow the format X Y Z X_dot Y_dot Z_dot The state vector has to be in the predefined coordinate frame to get reasonable results Each state vector with according epoch is interpreted as an orbital point to be analysed The maximum number of orbital points for the trajectory file is currently limited to 100 The trajectory file can be modified with the ESABASE2 editor or every other text editor out side the application To define a text file to be trajectory file and to be identified as such by ESABASE2 it must have the file type trajectory 3 2 Debris Input Limitation for Lunar Mission The use of the Debris solver ant the generation of a debris file is described in the chapter 2 The intention of this section is to introduce the limitations associated with the analysis of lunar mission or the use of a trajectory file 3 2 1 Sp
29. 7 03147852 6992 148315 109921629629 226226 195277236839 280398 370256302762 319467 564641026722 347003 923373151664 3646833 864160855301 373947 690921552770 374834 343681340663 5714 255328231473 29170 226320218550 18725 302590315150 6027 124364110680 7060 320356665809 19916 583080674551 32226 446256702318 43771 471716275177 54355 372132761142 0 164960105913E 12 22994 538303340792 32003 944520032528 37620 677676406325 41203 360972652750 43295 770665876990 44175 831010104965 43999 897190661796 42855 701921501168 4 624454537551 1 759254471321 1 165682717708 0 836727320480 0 601124790635 0 410462982675 0 244018276115 0 090479017080 0 057725707549 8 794028563774 0 138532715746 0 221179444568 0 2383068397627 0 238235389148 0 230658389569 0 2185325860558 0 202768322262 0 183352046203 1 656573672415 0 215028620544 0 127063680752 0 08172968358999 0 050731326032 0 02 6541351840 0 006080424525 0 012245515964 0 029440347424 END Figure 3 5 Trajectory file example The trajectory file is composed of two parts not considering the comments the head and the body The head of the file provides information about the mission The keywords for the kind of information are Origin Target Coordinates and Epoch They are required to indicate which information is given The colon is required as a marker for the start of the input No predefined order for the p
30. 705E 01 20616E 04 41490E 08 OD000E 00 OO000E 00 10 O 017 w29610E 01 0053E 01 31162E 01 1612E 04 435512E 08 O0000E 00 O0000E 00 1i 0 723 266855 E 02 13917E 02 17356E 00 11466E 03 z22471E 07 00000E 00 O0000E 00 le O ves wa ageE 0e 14160E 02 16190E 00 1l e25E O35 24117E 07 O0O000E 00 O0000E 00 Figure 2 44 Example of Crater vs Crater size LIS file The first column IELMT lists the elements of the model thus the results of the Crater vs Crater size LIS file are on the element level The corresponding results on the object level are presented on the bottom of the Deb Met LIS file Both LIS files provide the mission level of hits The second column lists the areas of the corresponding elements in m2 The columns 3 to 9 provide results number of hits for seven different crater size thresh olds This means the listed hit causes a crater that is equal or larger than the threshold cra ter size The first minimum threshold is the Min crater diameter defined by the user see 2 2 1 2 Based on this value the other six thresholds are defined by raising the crater size threshold by one order of magnitude This can be seen very well in the first line of the table in Figure 2 44 which lists the values of the thresholds as head of the columns In the same way the LIS file Failures vs Ballistic Limit can be interpreted In this case the number of failures instead of number of craters is tabulated again the ballistic
31. Analysis Tab The non geometric analysis uses simplified spacecraft geometry A pointed or randomly tumbling plate This mode is used to check an analysis environment consisting of the orbit specification the environment models and the damage assessment parameters Using this mode is recommended for large spacecraft models with many elements in order to iron out input errors without running a time consuming full analysis The ray tracing scheme is the same for both geometric and non geometric analyses The following figure shows the Non Geometric Analysis tab in the Debris input editor Wf debris 3 Tom Non geometrical Analysis Orientation and Area Shielding Type Wall 2 v Randomly Tumbling Thickness ist plate 0 1 cm Density ist plate 2 73 g cm 3 Azimuth Angle deg Thickness 2nd plate 0 1 cm Density 2nd plate 2 73 g cm 3 Zenith Angle deg Space between 10 0 cm Plate Area 1 0 m 2 Result Log Debris Ground Test Non Geometric Analysis Figure 2 26 Debris input editor Non Geometric Analysis tab In the tab three sections are visible e Non geometrical Analysis Specifies shielding type Wall_1 to Wall_15 as well as shield thickness and density and spacing in case of double walls To define the wall configuration see section 2 2 1 4 Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page
32. GO OOA ONA QAaAA amp amp amp A A A A A a lt 2007 09 14 gt SUBROUTINE USER DAM KFLAG VPART DPART ALFA RHOP TB RHOB TS RHOS SPACE X OUT D_USREQ C A E E E E E PE E E E E E E E E S E E A E E E E E E E S E E S E S OE ee Parameters of the calling sequence Input KFLAG Calling Flag of the Routine 1 Routine called as ballistic limit equation 2 Routine called as crater hole size equation VPART Scalar impact velocity km s DPART Particle diameter for call as crater hole size equation ALFA Impact angle deg RHOP Particle density g cm3 TB Back up or Main Wall thickness cm RHOB Back up or Main Wall density g cm3 TS Shield cumulated thickness cm RHOS Shield average density g cm3 SPACE Cumulated spacing shield to Back up wall cm Output X OUT Routine output Ballistic limit call Particle limit diameter Crater hole size call Crater hole diameter Input Output D USREQ Parameters up to 14 of the user failure and damage laws Purpose Specification of any user defined failure ballistic limit and damage crater size equation This is a simple example routine C A A A a a T a a es A a a a a a a a y e a a y a a a a a a ds a a a CALLS any user defined subroutine to be included in the UserSubroutine dll E A a a ___ A a A mz A a ff a a S CALLED BY DACRAHO SH BALDIV RPRT_IMPA C ma A A A A A A a A a ya a COMMONS none C AA a a
33. Zid Denis GeO Meu arab 12 2 1 1 Debris PAGS A e n rr IA 13 Ns a A O o ge A 15 2 2 DOS IDU lancia daras 16 2 2 1 Debris E o A AA 16 2 2 2 Debris Ground Test Tab ccccccccccscccccccccccccececuceccucecueeesucecuneesauenuneesanenaneeganes 40 2 2 3 Debris Non Geometric Analysis Tab oococcoconoccononocionenoninnoneninnononcnnoneninnaneninos 42 2 DEDAS ANS Sometidos ici iairaia italian 44 2 3 1 Geometric Debris ANalySiS cococcoconocconenocionenonionononinnononennononennononennonenennanenenss 45 2 3 2 Non geometric Debris ANAIS Sousa dd idad 49 2 4 Debris Results cccccccccscceccceccecccecacenacecacenucenacenunenanenunenanenunenanenanenanenanes 51 241 3D ROSUIS ocx zcacecacecscsecedesstaaceeacieicaceciescecaciaacieicsaiesenvieieieanieiazeiaiarezescieseienseiie 51 DAD ZU ROS ONS eE EEEE EEEE EEEE EEEE EEEE EEEE TEE 57 A A o EEEN 62 LA NOS e osa 64 3 Lunar Mission Debris ANalySIS c scscscscseseseeneneseeeeseneneneneseeneneneneneeennens 65 Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 2 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig member of the ckc group Bel O gr MISSION A AO 65 3 1 1 Abstraction of the Lunar MiSSiON occococccccocconnonnonocnocoonnanonnnnonnnnnnaronrrranrannnnnns 66 za MAC 69 3 2 Debris Input Limitation for Lunar MISSION ccecceceeeeeeeeeeeseee
34. ace GmbH Frankfurter Str 3 d 38122 Braunschweig 2013 11 07 1 5 2 Final Page 9 74 Revision El member of the ckc group Figure 2 29 Figure 2 30 Figure 2 31 Figure 2 32 Figure 2 33 Figure 2 34 Figure 2 35 Figure 2 36 Figure 2 37 Figure 2 38 Figure 2 39 Figure 2 40 Figure 2 41 Figure 2 42 Figure 2 43 Figure 2 44 Figure 2 45 Figure 3 1 Figure 3 2 Figure 3 3 Figure 3 4 Figure 3 5 Figure 3 6 Figure 3 7 2013 11 07 1 5 2 Final Page 10 74 Geometric Debris analysis RUN button ccccococonononcncanaconononencanananononenencanoso 45 Geometric Debris analysis RUN wizard ccccococonononcncananonononencnnananononenennanoso 46 Geometric Debris analysis Run dialog export page occccoconoccononociononeninnanos 47 Geometric Debris analysis Progress Dar coccccoconocionenonionononionononianoneninnanos 48 Non geometric Debris analysis RUN wizard ococococococconacononononencananonononenen 49 Non geometric Debris analysis results coccccocococonononcanacanonononencanaronononenen 50 Debris result editor 3D Results 0ooocococococococononoconananananananananararanarararanananns 51 Debris result editor 3D Results colour context MeNU occccccccccncnnonanananananass 52 Debris result editor 3D Results Orbital Point context MENU cccceseevevaees 54 Debris result editor 3D Results Coordinate Systems context menu 55 Debris result editor 3D Results El
35. al Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 74 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig
36. al orbit HEO the transfer orbit with a perigee at the parking orbit and the apogee at the orbit of the Moon e A low lunar orbit LLO which is the target orbit of the mission Each of the orbits represents one of the phases of a lunar mission The three phases de scribe roughly the lunar mission the first phase includes the mission time in the vicinity of the Earth here it is represented by a LEO The second phase is the transfer from Earth to Moon represented by a HEO The third phase of the mission is the motion of the S C in the vicinity of the Moon in this case a LLO The individual orbits generated in the following give only an outlook of possible tracks and are not combined to reflect a real mission To abstract a real mission the used mission ep ochs and durations have to fit a meaningful timeline i e the mission epochs have to form a continuous time interval second track starts at the end of the first track etc Furthermore the start epoch and orbit parameters of the transfer orbit have to be defined in a way that the Moon interferes with the transfer orbit and the S C is at the according sector of the orbit at the particular moment This implies also the usage of the correct orbital parameters e g inclination true anomaly at start etc Nevertheless to get an impression of the result magnitudes to be expected and to get the feeling of the usage three independent orbits can be used This is also the case for the fol lowi
37. alysis The Slim Results checkbox is a performance switch With it LIS files as in the original ESABASE and 2D graphs will be created as usual and with full information content as speci fied in the Report Options box but the only 3D geometry result will be for the entire mis sion no orbital points or arcs will be available For large models or many orbital points this may be the only option to run ESABASE2 Debris within the available RAM of the executing computer Generating an output filename is highly recommended The default filename contains the solver type here debris and the current date and time Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference RO77 232rep_01_05_ 02 Software_User_Manual_Solver_Debris doc Page 46 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group At the bottom the Report options combo box allows you to specify the content of the Deb Met listing formerly LISD LISM LISDM output files within the Debris result file You can choose between the following options e Output of a summary of objects results on orbital arc and mission level and on ob ject and spacecraft level no object element summary no orbital point related results and no element related results e Output of header and summary all the same but including object element summary and element related results e Comp
38. and navigating to Coordinate Systems as shown in the following figure EE Landsat _debris result 2009 07 06 16 41 06 2 Ziyear Colour Orbital Point Coordinate Systems no coordinates global coordinate System centered default Notes Listings 3D Results 2D Results Figure 2 38 Debris result editor 3D Results Coordinate Systems context menu You can choose among the following coordinate system settings No coordinates Note that pointing vectors will also be deactivated Global coordinate system centred Shows the xyz axis for the entire system Global coordinate system in the corner Same as before but in the corner of the sys tem not centred Global and local coordinate systems Shows xyz axis for each object Detailed but probably slightly irritating for complex S C geometries etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 55 74 El member of the ckc group 2 4 1 4 Element Chart Different 2D graphs of the debris results can be shown for the entire spacecraft geometry using the 2D Charts tab as described in the next section 2 4 2 However it is also possi ble to show graphs of only one element Shift Leftclick an element of the S C geometry then open the context menu and select Element Chart The following figure shows the resulting small popup window 2 Chart for element_1 A 2 Chart for element_1 Result Set i Result Set UAE t te ag tne 8 E EA Export I
39. ard is considerably simpler The space craft geometry input file is omitted and all options have been removed only the report op tions remain No output file needs to be specified since the result listings are displayed in the Result Log section of the Debris input editor s Non Geometric Analysis tab The content of the listings is stored within the debris input file ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 49 74 Et The screenshot below shows the debris input editor supplied with results from a non geometrical debris analysis member of the ckc group Result Log LISTINGDEBMET STATA i a TTT TATA ESABASE Tebris rel 2 0 ESTEC etamax space 2008 09 16 Current run Debris only non geometrical analysis Date O06 JUL 2009 Tine 23 04 41 STATE ATE TATE TTA TTT A Debris Ground Test Non Geometric Analysis Figure 2 34 Non geometric Debris analysis results In the Result Log section the combo box toggles between the output files while the text area below shows the content of the selected file Here the Debris Meteoroid listing LISTINGDEBMET is shown Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Sol
40. bris result 2009 07 06 16 41 06 5 Posa yla ee 2 year Orbital Point 4 Element Chart colo Orbital Point i Object Number Coordinate Systems Surface Number Element Number KS Factor Average Impact Velocity km s Average Impact Angle deg Crater Flux So year Total Impact Flux 1 frie year Total Impact Fluence 1 m2 Total Failure Flux 1 m2 year Total Failure Fluence imz Motes Listings 3D Results 20 Results Figure 2 36 Debris result editor 3D Results colour context menu Cata Ein Drfrarnarmas DATT Oran A1 NE ND Cafes Inne Manili Cahar Malva lar T ATO J i gt Ly OATQLraANnra DIV lt Jran ia f LAID rTAQ ICA VI ni gt SMNVAa mMnri lt Yi old le Midi mMeicCrcrilLe WU J ZOZI f OI LW dI Ser Manuali gt Ol VTI VEVDIIS GQOC Page 52 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El The first 4 items listed below are not part of the Debris results instead they are used to gain an overview of the spacecraft geometry and particular its objects surfaces and ele ments member of the ckc group e Colour Displays exactly the same object colour which was used in the geometry edi tor e Object Number Each object is identified by an object number In this overlay this object number is mapped to colours o Leftclick on an object in the 3D view to select it and then look at the colour scale to the right The appropriate colour will be marked and th
41. e ckc group 1 Introduction ESABASE2 is a software application and framework for space environment analyses which play a vital role in spacecraft mission planning Currently 2012 it encompasses De bris meteoroid 1 Atmosphere ionosphere 7 Contamination outgassing 5 6 and Sunlight 8 analyses with this it complements other aspects of mission planning like ther mal or power generator design The application grew from ESABASE2 Debris an application for space debris and micro meteoroid impact and damage analysis which in turn is based on the original ESABASE Debris software 4 developed by different companies under ESA contract ESABASE2 adds a modern graphical user interface enabling the user to interactively establish and manipulate three dimensional spacecraft models and to display the selected orbit Analysis results can be displayed by means of the colour coded surfaces of the 3D spacecraft model and by means of various diagrams The development of ESABASE2 was undertaken by etamax space GmbH under the European Space Agency contract No 16852 02 NL JA The first goal was to port ESABASE Debris and its framework user interface to the PC platform Microsoft Windows and to create a modern user interface From the start the software architecture has been expressively designed to accommodate further applications the solvers outlined in the first paragraph were added and more mod ules like e g Radiation are to follow
42. e object num ber will be shown e Surface Number Breaking down the objects each surface is shown in a different col Our o Ctrl leftclick on a surface in the 3D view to select it The respective surface number is marked in the colour scale to the right e Element Number Further breaking down the surfaces each element is shown in a different colour o Shift leftclick on an element in the 3D view The selected element number and color will be marked in the color scale The following 8 items show the respective quantity listed below as colours on the elements of the geometry model To see the exact value on an element Shift leftclick the element the colour scale on the right will then show the quantity value e KS Factor e Average Impact Velocity km s e Average Impact Angle deg e Crater Flux year e Total Impact Flux 1 m2 year e Total Impact Fluence 1 m 2 e Total Failure Flux 1 m 2 year e Total Failure Fluence 1 m 2 If the secondary ejecta option was activated in the Debris input editor it is now additionally possible to display the direct impact failure flux fluence and the ejecta impact failure flux fluence Please note that results always sum up both sides of all elements A distinction between positive and negative side of an element is not possible ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State
43. each orbital point Table 2 1 Available 2D charts in dependency of the Debris Meteoroid model The 2D Result tab offers additional functionality to work with the charts represented by buttons to the right of the chart combo box e Options Allows you to customise the chart appearance e Image Export Save the current chart to a PNG or JPG file e Show Report Opens a print ready report for a given chart 2 4 2 1 2D Charts Options The Options button opens a context menu for a given chart as shown in the following fig ure It contains axis configurations as well as settings for the data lines Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc Page 58 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group ES Landsat _debris result 2009 07 06 16 41 06 53 m Graph 1M105_vel_opOl e Label text Y PO Grid Title Label Font MASTE ena gt teata City Orbital point 01 Background Label Font style T w Box Maximum Foreground Minimum gt E w Auto scaling Mumber Format E Graph Type Number scaling E Series O an 4 Export a Range x y Lu 2 1 al A DO 25 50 72 100 125 150 175 200 225 250 275 300 325 350 375 400 Velocity km s Notes Listings 3D Results 2D Results Figure 2 41 Debris result editor 2D Res
44. eador Orbital Debris Environment for Space craft Designed to Operate in Low Earth Orbit NASA TM 100471 NASA 1989 Kessler D J J Zhang M J Matney P Eichler R C Reynolds A Computer based Orbital Debris Environment Model for Spacecraft Design and Observations in Low Earth Orbit NASA TM 104825 NASA 1996 Staubach P Numerische Modellierung von Mikrometeoriden und ihre Bedeutung fur interplanetare Raumsonden und geozentrische Satelliten Theses at the University of Heidelberg April 1996 S Stabroth P Wegener H Klinkrad MASTER 2005 Software User Manual MO5 MAS SUM 2006 McNamara H et al METEOROID ENGINEERING MODEL MEM A meteoroid model for the inner solar system PROTECTION MANUAL Version 5 0 Inter Agency Space Debris Coordination Com mittee IADC 04 03 Revision October 2012 SWENET ESA s Space Weather European Network since 2004 http www esa spaceweather net swenet Flegel S Gelhaus J Mockel M Wiedemann C Kempf D Krag H MASTER 2009 Software User Manual MO9 MAS SUM June 2011 Flegel S Gelhaus J Mockel M Wiedemann C Kempf D Krag H Maintenance of the ESA MASTER Model Final Report of ESA contract 21705 08 D HK MO9 MAS FR June 2011 NASA MSFC personal communication 2013 11 07 ESABASE2 Debris 1 5 2 Software User Manual Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig
45. ecifics for Abstracted Lunar Mission In the case of an abstracted lunar mission the individual mission steps represented by the mission files are analysed independently Thus theoretically for the analysis of orbits in the vicinity of the Earth all model possibilities except LunarMEM are available But if the results of the individual mission steps are to be combined manual post processing they have to be coherent This means coherent models should be used throughout the analysis of the mission The use of the debris and meteoroid models can be seen as independently For each mission file a debris file can be defined due to the individual analysis More practi cable is the definition of one debris file for the analysis of orbits around the Earth and one debris file for the analysis of orbits around the Moon The debris file around the Earth should define the debris if desired and meteoroid model to be used e g MASTER 2009 and MEM The debris file around Moon should define the meteoroid model to be used e g LunarMEM 3 2 1 1 Debris Models Debris models are available only for the vicinity of the Earth and thus can be only applied to orbits around the Earth In the case that the debris environment should be considered only for the low Earth orbits than all debris models can be used If the effects of the debris shall be considered for trajec tories with semi major axes about LEO gt 2000 km also than only the MASTER models are app
46. ed as follows e Debris Geometry Explains debris specific additions to a S C geometry see section 2 1 e Debris Input Describes the input parameters for Debris and meteoroid analyses see section 2 2 e Debris Analysis How to perform an analysis see section 2 3 e Debris Results How to interpret the analysis results see section 2 4 2 1 Debris Geometry The geometry editor defines a spacecraft s geometry for all solvers available within the ESABASE2 framework 1 including Debris Solver specific geometry parameters are defined using special pages in the shape wizard For Debris the following special pages and options are available e Debris Page Settings only applicable to the Debris solver concerning material thick ness and shielding see section 2 1 1 e Meshing Page Positive negative sides and meshing recommendations for Debris see section 2 1 2 Date 2013 11 07 ESABASE2 Debris Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 12 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 1 1 Debris Page A dedicated Debris page is shown for each shape allowing you to define the shielding con figuration of any shape both primary and secondary shielding Classic surface material properties as defined by the Material page are not interpreted by the Debris solver Please note t
47. eeeeeeeeeeeeeeees 71 3 2 1 Specifics for Abstracted Lunar MISSION coccccoconocconenonconenoninnononinrononcnnoaneninnanos 71 3 2 2 Specifics for Trajectory File scainiiacisa aida 73 3 3 Perform an Analysis occcconccconccconcnconcncononconrnrononnonrnrononrnnr anar rnarn anar nanarnaana 73 ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05_02_Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 3 74 Et member of the ckc group Document Information I Release Note Name Function Date Signature Established by Ruhl K D Bunte A Technical Project 2013 11 07 Gaede A Miller Manager Released by P Hake Project Manager 2013 11 08 ll Revision History Version Date Initials Changed Reason for Revision os 20090925 KB A Review formalar 1 2 2010 08 23 KB Section 2 2 1 5 Description of the use of the User Subroutine ex all tended document layout update 2012 12 04 Section 2 2 Modified BLE and Shielding handling 1 5 2013 04 19 AM Sections 2 2 1 1 Extended for Lunar missions consideration 2 4 2 3 2013 07 09 Sections Clarification of the used date for MASTER popula 2 1 1 1 tion snapshots 2013 11 07 Section 2 4 3 1 Introduction of Crater vs Crater size listing inter pretation IN Distribution List Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 So
48. ement Chart ccccccesssessevaveeeeeeeuuavavavas 56 Debris result editor 2D Results cccccccceeseeeseseeeeeueueueeeeeeeeeaeeeaeaeanaeaeananas 57 Debris result editor 2D Results OPtiONS occocococcononocconenoncanenoncanenonnanonon 59 Debris result editor 2D Results reporting cococcccoconocconenocconenoncanononcanonons 61 Debris result editor 2D results liStINGS o cococococococconanononononcncananononononon 62 Example of Crater vs Crater size LIS file c ccecceseceeceeeeeeeeseneeseaeaeeeeenenes 63 Debris result editor 2D Results notes oococococococononocananananananananarananananans 64 Scheme of the lunar mission of Chandrayaan 1 source North East India e e o EEE E E 65 Parking Orbit Parameters oocococococconacononononencananonononenencaronononenenrararononenenens 67 Transfer Orbit parameters ococcococononononcanananononenencananononenenca raro nonenencarananonos 68 Target orbit Parameter commit a 69 Trajectory file example oococcocoroccocoroccocaronconaronrocaroarncaroarncnroarnenrnarnenroann 70 Taylor HRMP activation with the Edit button for Gr n coccccococonononcnnananononos 73 Choosing a trajectory file oocococcononiocionononionenonionononnarononinnononinroneninnanos 74 ESABASE2 Debris Software User Manual Reference RO77 232rep_01_05_ 02 Software_User_Manual_Solver_Debris doc etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of th
49. ep_01_05_ 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 35 74 El Failure and damage equations of the ESABASE2 Debris analysis tool are defined in a para metric form with editable parameters constants and exponents The parameters can be edited via the Edit buttons shown in Figure 2 21 member of the ckc group Up to seven entities can be defined for failure equation e the single wall ballistic limit equation e the multiple wall ballistic limit equation and e the user subroutine parameters for damage equation e the crater size equation e the parametric clear hole equation e the advanced hole equation and e the user subroutine parameters The user subroutine option is only for expert users with Fortran and or C experience see section 2 2 1 5 For a detailed description of the user input of the damage equations please refer to 10 Date 2013 11 07 ESABASE2 Debris Revision 152 Software User Manual State Final Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc Page 36 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 2 1 5 User Subroutine For expert users of the original ESABASE the possibility to use your own damage equation subroutine is provided This option requires the availability of a FORTRAN or C C compiler and linker You need to rebuild the 2
50. et member of the ckc group V Glossary Ballistic limit The minimum particle diameter which is able to penetrate a given wall configuration Eclipse Eclipse is an open source community whose projects are focused on providing an extensible development platform and application frameworks for building software For de tailed information refer to http www eclipse org ESABASE Unix based analysis software for various space applications For details refer to the ESABASE User Manual 4 ESABASE Debris ESABASE framework and the debris and meteoroid flux and damage analysis application ESABASE2 New ESABASE version running on PC based Windows plat forms to be distinguished from the old Unix based ESABASE Geometric al analysis Flux and damage analysis of a full three dimensional geo metric model Object pointing keyword tracking of a GEO satellite Ground test Evaluation of the results of a selected damage or failure equation LunarMEM MEM version which is tailored to orbits around the Moon MASTER 2001 ESA s Meteoroid and Space Debris Terrestrial Environment Reference Model For details refer to the MASTER Upgrade Final Report 5 ESABASE2 Debris uses the MASTER 2001 Standard application MASTER 2005 ESA s successor to MASTER 2001 now defined as standard application for space debris risk analyses MASTER 2009 Successor of ESA s reference model MASTER 2005 For de tails refer to 24 Meteoroid Eng
51. ets with aphelia less than 7 AU The model also considers the con tributions from long period comets to the sporadic meteor complex and includes the effects of the gravitational shielding and focussing of the planets Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 28 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 2 1 1 9 Meteoroid model LunarMEM LunarMEM is a MEM 20 version which is tailored to the vicinity of the Moon Upon pressing Edit a dialog with the LunarMEM input parameters opens as shown in the figure below Meteoroid Model Lunar MEM Options Constant meteoroid density glem 3 1 0 Figure 2 15 Debris input editor main tab Model Selection LunarMEM Since LunarMEM is a tailored version of MEM most model characteristics are coherent as for the use of a constant meteoroid density of 1 g cm We propose to always use 1 g cm also for LunarMEM Please note that the default 2 5 g cm is fitting only for the other meteoroid models all models use the same parameter within the data model this is the reason that the default in the GUI cannot be 1 g cm For further information about LunarMEM please refer to 2 or the MEM reference 20 ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05
52. ftware User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 4 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group IV List of References 1 K Ruhl K D Bunte ESABASE2 Framework software user manual RO77 230rep ESA ESTEC Contract 16852 02 NL JA PC Version of DEBRIS Impact Analysis Tool etamax space 2009 2 A Gade K D Bunte ESABASE2 Debris Technical Description ESA ESTEC Contract 16852 02 NL JA PC Version of DEBRIS Impact Analysis Tool etamax space July 2009 3 ESABASE2 homepage http www esabase2 net 4 ESABASE User Manual ESABASE GEN UM 070 Issue 1 Mathematics Software Di vision ESTEC March 1994 5 Giunta 1 Lemcke C Roussel J F COMOVA 1 1 Technical Description ESTEC Contract No 12867 98 NL PA HTS AG and ONERA March 2002 6 Giunta I Lemcke C Roussel J F COMOVA 1 1 10 Software User Manual ESTEC Contract No 12867 98 NL PA HTS AG and ONERA October 2006 7 Borde J Sabbathier G de Development of an Improved Atomic Oxygen Analysis Tool Software User Manual S413 NT 19 94 Issue 2 ESTEC Contract 9558 91 NL JG Matra Marconi Space Toulouse France May 1994 8 ESABASE Sunlight Application Manual ESABASE SUN UM 072 Issue 2 Rel 2 1 ESTEC Mathematics amp Software Division Noordwijk The Netherlands September 1994 9 Bendisch J K D Bunte S Hauptmann H
53. gee Altitude 100 000 Eccentricity Apogee Altitude 100 000 Inclination RAAM Argument of perigee True Anomaly Solar time Geographic longitude Mission Time Number of Orbits 1 0 Start Date 2013 1 6 0 0 0 EndDate 2013 2 6 0 0 0 Time Interval or Number of Orbital Points Time Interval between Orbital Points 441 93 apply Mumber of Orbital Points 16 0 apply Figure 3 4 Target orbit parameters The Figure 3 1 depicts that in fact the targeted orbit is not reached immediately After the capture of the spacecraft by the Moon the trajectory is corrected and reached via multiple thrusters impulses Thus also the last phase of the mission can be modelled in more detail by defining various mission files which describes the orbits between the firings 3 1 2 Trajectory File The trajectory file allows the user in contrary to the abstraction of a lunar mission to define the whole track of the lunar mission in one file using the maximum of 100 orbital points state vectors If more orbital points than the maximum are contained in the file only the first 100 points can be used In this case a warning is shown in the console view The Figure 3 5 provides an example of a trajectory file which represents the half of a highly elliptical orbit around Earth by 9 orbital points The apogee is at the Moon distance and the last two points are in the in the sphere of influence of the Moon thus they are interpreted as orb
54. hat the Debris page is only available if ESABASE2 Debris is part of your installa tion it is also possible to have only ESABASE2 Atmosphere for example depending on your license To see the Debris page open a geometry file select a shape then rightclick it and choose Modify gt Debris A wizard page as shown in the figure below will be opened E Shape Wizard Debris Box Size Meshing Position amp Attitude Kinematic Pointing Debris Comovya Material Shield type only for geometrical analysis none Material density 1st plate 2 713 g cm 3 Thickness 1st plate 0 1 cm The parameters of the second plate are only considered if the selected predefined wall is setup up as Multi Wall or User Subroutine Spacing 5 0 crm Material density 2nd plate 2 713 g cm 3 Thickness 2nd plate 0 2 crn Figure 2 1 Geometry editor Debris page On this page you can define shielding and material parameters that go beyond the Material page of the shape wizard The simplest option is to check the Inherit parent values checkbox which takes over all Debris related values from the parent shape This is possible for all shapes except the central body Below the shield type can be chosen One of the 15 predefined damage and failure equation combination can be selected here Wall_1 to Wall_15 for setup see 2 2 1 4 The lower three parameters spacing Material density 2 plate and Thickness 2 plate are only used if the
55. he investigation of missions below 10 days where high stream activities are ex pected Date 2013 11 07 ESABASE2 Debris Revision 152 Software User Manual State Final Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc Page 30 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group 2 2 1 1 11Alpha Beta Separation As an improvement to the Grun meteoroid model the Alpha Beta Separation divides the me teoroids in alpha particles following the Gr n sporadic omni directional flux model and smaller beta particles stemming from the sun When you press Edit the Alpha Beta Separation options shown in the screenshot below appear in a dialog Alpha Beta Opkions WO cross over velocity 20 0 Gamma exponent 0 18 ay Figure 2 17 Debris input editor main tab Model Selection Alpha Beta Separation The velocity distribution of the beta particles can be modified by specifying two parameters for more details see 10 e VO cross over velocity default 20 0 km s e Gamma exponent default 0 18 The Alpha Beta Separation obtains improved directional information by attempting to split off the beta meteoroids which are driven away from the Sun into hyperbolic orbits by radiation pressure from the alpha meteoroids It is applicable only to Earth orbits An apex enhancement of the alpha meteoroids and interstellar streams see next subsubsec tion
56. he names of the listing files are composed from the string NonGeom the analy sis date and time and the type of listing result set 2 3 Debris Analysis With both debris information within the spacecraft geometry and global debris input parame ters specified the time has come to perform a debris analysis There are two types of analy sis runs e Geometric Analysis This is what you would normally expect A mission and a space craft geometry are sent to orbit propagation and debris analysis see section 2 3 1 Date 2013 11 07 ESABASE2 Debris Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 44 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et e Non geometric Analysis Subtracts the S C geometry from the analysis instead taking a simple plate see section 2 3 2 member of the ckc group 2 3 1 Geometric Debris Analysis In the toolbar at the top of the application window locate the Run button depicted in the following figure Press the small down arrow at the right of the button and a context menu will appear 2 ESABASE2 File Edit Window Help gt O i Reset perspective CO gt pe a a ES Run geometric Debris Analysis Run non geometric Debris Analysis Figure 2 29 Geometric Debris analysis Run button Whenever you click directly on the Run button instead of the down arr
57. ime Geographic longitude Mission Time Number of Orbits 1 0 Start Date 2013 1 1 0 0 0 EndDate 2013 1 1 4 38h 6 Time Interval or Number of Orbital Points Time Interval between Orbital Points 347 63 apply Number of Orbital Points 16 0 apply Figure 3 2 Parking orbit parameters Figure 3 1 shows that in a realistic scenario the first phase of a lunar mission is more com plex than just one orbit The mission phase is often composed of multiple orbits with differ ent eccentricities and inclinations Reasons for such an approach are the minimisation of the required propellant and also of the failure risk This approach can be modelled by definition of new mission files with according orbits and mission times after each firing of the thrust ers The first phase of the lunar mission would be than described by multiple mission files instead of one the results of which have to be combined in the manual post process 3 1 1 2 Transfer Orbit The transfer orbit is abstracted by a highly elliptic orbit around the Earth with the perigee at the LEO orbit and the apogee at ca the distance to the Moon Possible parameters for a representative HEO are e Central body centre of motion Earth e Sami major axis 206585 km e Eccentricity 0 9671892 e Inclination 28 5 deg e Other angles 0 0 deg This trajectory has nearly the same perigee as the one of the LEO ESABASE2 Debris Date Software User Manual Revis
58. included as subpopulation and cannot be turned off with this flag e Fragments collision and explosion before reference epoch 2001 05 01 These are known fragment populations e Nak droplet releases coolant droplets released from Russian RORSAT satellites e SRM solid rocket motor firing waste products o Slag produced in the final firing phase mostly gt 1 mm ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 19 74 El member of the ckc group o Aluminium oxide Al 03 dust e Paint flakes are generated by surface degradation effects mostly sunlight and ther mal cycling e Ejecta are small fragments of the S C created by the impact of debris or meteoroids e Collision but not explosion fragments after reference epoch covers assumed colli sion rate of satellites with other bodies in the future e Explosion but not collision after reference epoch covers assumed explosion rate of satellites in the future In the context of the MASTER 2001 model reference epoch or historic means dates until 2001 05 01 The future are dates from 2001 05 01 note that from there objects lt 1 mm are not considered this also means that paint flakes ejecta and dust are not available be cause they are always lt 1 mm As an example of the effec
59. ineering Model for details refer to 20 NASA9O Simple analytical space debris engineering model established by NASA 16 NASA96 ORDEM96 NASA s space debris engineering model Successor of NASA90 and predecessor of ORDEM2000 For details refer to the ORDEM96 documentation 17 non geometric al analysis Flux and damage analysis of a plate which can be specified as a randomly tumbling plate or an oriented plate ORDEM2000 NASA s latest space debris engineering model For details refer to the ORDEM2000 documentation 15 STEP Acronym which stands for the Standard for the Exchange of Product model data ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_ 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 7 74 el member of the ckc group VI List of Abbreviations OCAF Open CASCADE Application Framework contains the ESABASE2 data model ORDEM Orbital Debris Engineering Model RTP Randomly Tumbling Plate UTC Coordinated Universal Time Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 8 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group VII List of Figures Figure 2 1 Geometry editor Debris PAY occococociocon
60. ion Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig 2013 11 07 1 5 2 Final Page 67 74 El The start time for the transfer orbit is the mission end epoch of the LEO mission file e January the 1 2013 at 4 38 and 6 seconds A HEO with the introduced parameters has a period of ca 10 82 days Thus the half of the period only the way to Moon would be for a Hohmann transfer ca 5 41 days Let s say the transfer duration is more than 5 days but shorter than the duration of a Hohmann transfer The end epoch for the second phase of the lunar mission the transfer is thus arbitrary adjusted to January the 6 2013 at 0 00 member of the ckc group The mission file can be created as described in 1 section 3 1 The filename 7ransferOrbit will be used in the text to identify the orbit The Figure 3 3 show the mission editor with the parameters applied as introduced before sd 8 Orbit Central body Earth A Orbit Type GEN M Semi major Axis 206585 0 Perigee Altitude 400 079 Eccentricity 0 9671892 Apogee Altitude 400013 641 Inclination 28 5 RAAN 0 0 Argument of perigee 0 0 True Anomaly 0 0 Solar time Geographic longitude Mission Time Number of Orbits 1 0 Start Date 2013 1 1 4 63856 End Date 2013 1 6 0 0 0 Time Interval or Number of Orbital Points Time Interval between Orbital Points 58403
61. ital points of lunar orbits ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 69 74 El member of the ckc group ERRATA Example trajectory file Head defines the coordinate system and the epoch format Possible origin bodies Earth Moon Origin is optional if it is missing Earth is assumed to be the origin body Possible target bodies Earth Possible coordinate system ECI Earth Centered Inertial EME2000 LCI Lunar Centered Inertial Moon_J2000 Mean pole 2 Possible epoch format MJD Modified Julian Day 1950 UTC CCSDS ASCII time code A YYYY MM DDThh rm s d gt d E Moon Body provides the state vectors with appropriate epoch currently currently Each state vector represents an orbital point Format epoch X Y Z X dot Y dot dot CERRAR ARRE a a a a a a a a a a a a a a a a a a a a a a a a a a a a a a a a a Origin Earth Target Moon Coordinates ECI Epoch MJD IAU node of J2000 0 xj System a a a a a a a a a a a a a a a a e a a a a a a a a a a a a a a a a a a a a e a a a a a a a a a BEGIN 19798 48806713 19799 12152037 19799 75497361 19800 38842685 19801 02188009 19801 65533333 19802 28878657 19802 92223981 19803 55569306 516
62. km s e The NASASO velocity distribution In most cases this delivers the best results and is thus the recommended option for the industrial user The NASA90 velocity distribu tion is not applicable to lunar orbits due to the intended design for Earth orbits e The Taylor HRMP velocity distribution This model is the most complex option It is also applicable and recommended for the lunar orbits The last two lines handle the meteoroid velocity range namely the minimum and maximum meteoroid velocity to be considered The default is 11 km s and 72 km s Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 26 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 2 1 1 7 Meteoroid model Divine Staubach Divine Staubach 13 18 is a meteoroid model which is also part of the MASTER 2005 model When you press the Edit button a dialog shows the the Divine Staubach input pa rameters depicted in the screenshot below Meteoroid Model Divine Staubach Options Constant meteoroid density gfcn3 2 5 Figure 2 13 Debris input editor main tab Model Selection Divine Staubach The only parameter is the material density of meteoroids It is assumed to be constant Divine Staubach is based on the size and orbital element distributions of five meteoroid sub populations and thu
63. les SAM 41203 dust Paint flakes Ejecta Collision fragments Explosion fragments MLI historic populations only r aa Figure 2 9 Debris input editor main tab Model Selection MASTER 2009 The MASTER 2009 options are similar to the MASTER 2005 options see previous subsubsec tion The following differences to MASTER 2005 have to be noted e Objects down to 1 um are considered for both the historic and the future populations MASTER 2005 do not consider objects lt 1 mm for future populations e Both historic and future populations for solid rocket motor dust are available gt absence of the hint historic populations only e Both historic and future populations for paint flakes are available gt absence of the hint historic populations only e Both historic and future populations for ejecta are available gt absence of the hint historic populations only e The new source multi layer insulation MLI is introduced Historic populations until the reference date are provided for this source The reference date of MASTER 2009 is the 2009 05 01 Dates after the reference date are considered as future MASTER 2009 covers altitudes from 186 km to ca 37000 km The population snapshots of the May 1 of the mission start year are used for the analysis ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris d
64. lete listing of objects orbital point orbital arc and mission related results on ob ject and spacecraft level no object element summary and no element related re sults e Complete listing of all the same but including object element summary and element related results Optionally you can press the Next button to go to the second page of the Debris analysis wizard which is depicted in the figure below Geometric Debris Analysis Export to ZIP file Please select if you wank bo export the results Export to ZIP file will save all Files First Export geometry File Export mission File Export debris File Export result File Target directory For export Comment khat will be included in the Filename cubesat Figure 2 31 Geometric Debris analysis Run dialog export page ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 47 74 El member of the ckc group The debris result file will be saved into your workspace This page allows you to additionally export the input and result files to a ZIP file suitable for transmission via email or other means Press the Finish button to launch the Debris analysis A progress bar will appear and keep you updated about the current state of the application Depending on the number of elements in the
65. licable This practically excludes NASA90 target altitude lt 1000 km and ORDEM2000 ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 71 74 El member of the ckc group target altitude lt 2000 km models because using them will lead to neglecting of the debris environment in the vicinity of the Earth for the transfer orbits Three versions of the MASTER model are available MASTER 2001 is the oldest version and based on outdated data but it is fast and thus can be handy sometimes MASTER 2005 is the successor of MASTER 2001 and based on real data up to 2005 It is applicable to the vicinity of the Earth up to 1000 km above the geosynchronous orbit The limitation of MASTER 2005 is the provision of mission averaged results only Due to the averaged re sults it should be ensured that the examined mission part is in the range of validity of MASTER 2005 otherwise not existing debris fluxes will be provided Furthermore the debris analysis results are not tailored to the considered arc of the track The best choice is the successor of MASTER 2005 the MASTER 2009 model It is based on the most up to date data real data up to 2009 of all five debris models Furthermore it provides data for the each orbital point besides the averaged mission data Thus data
66. mage KS Factor Pi iar Aa Total Impact Fluence 1 m 2 vs orbital points for element_1 0 0009 Total Failure Flux 1 m2 year Total Failure Fluence m 2 E 0 0008 0 0007 2 0 0006 3 0 0005 L 0 0004 0 0003 0 0002 0 0001 O 0 0000 0 0 05 10 15 20 25 Orbital Points Figure 2 39 Debris result editor 3D Results Element Chart From the Result Set combo box select a variable the appropriate graph for the given ele ment will be displayed as shown on the right These are the same values that are colour coded in the element in the 3D view You also have the possibility to adjust the appearance of the graph via the Options button or a context menu opening on rightclicking and to export the image as PNG or JPG via the Export Image button s sections 2 4 2 1and 2 4 2 2 for details Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 56 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 4 2 2D Results Complementing the 3D Results tab described above charts can show different flux distri butions in the 2D Results tab An example is shown in the following figure ES Landsat _debris result 2009 07 06 16 41 06 E3 E y MASTER 2005 flux vs velocity orbital point 01 Graph Win AA Flux 1 m 2
67. may introduce further directional information We do not recommend using other values than the default values for this model unless you have in depth knowledge in astrophysics ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 31 74 El member of the ckc group 2 2 1 1 12Apex Enhancement As a modification to the Gr n model the Apex Enhancement describes the meteoroid flux enhancement caused by the earth s motion on its orbit around the sun similar to the en hanced flux a spacecraft experiences in velocity direction It is applicable only to Earth or bits If you press Edit a dialog shows the Apex Enhancement input parameters shown in the figure below Apex Enhancement Opkions RF antapex to apex Flux ratio 2 0 Dy velocity ratio 0 36 Figure 2 18 Debris input editor main tab Model Selection Apex Enhancement Two parameters can be used to describe the ratio of flux and velocities between apex front and antapex back directions see 10 for more details e Rf antapex to apex flux ratio default 2 0 e Dy velocity ratio default 0 36 As with Alpha Beta Separation we do not recommend using other values than the default values for this model unless you have in depth knowledge in astrophysics Date 2013 11 07 ESABASE2
68. ment model processes the debris populations to form the debris environment ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 25 74 Et member of the ckc group 2 2 1 1 6 Meteoroid model Gr n Grun 14 is an omni directional interplanetary flux model for sporadic meteoroid environ ment It can be applied for Earth and lunar orbits When you press the Edit button a dia log with the Grun input parameters shown in the figure below appears Meteoroid Model Gruen Options Meteoroid density For constant density gfcm 3 5 Meteoroid density model Constant Meteoroid velocity model Constant Constant meteoroid impact velocity const velocity only km s 17 0 Minimum meteoroid impact velocity Nasa90 and HAMP only kms 11 0 Maximum meteoroid impact velocity Nasa90 and HRMP only kms 72 0 a naa Figure 2 12 Debris input editor main tab Model Selection Gr n On top you see the meteoroid density option Below choose between this constant meteor oid density and alternatively the NASA90 density distribution model the latter choice will ignore your meteoroid density specification above The next two lines are concerned with the meteoroid velocity distribution option e Constant meteoroid velocity for this option the default value is 17
69. n button Afterwards the Graph and Ta ble buttons at the bottom right are enabled leading to the popup windows illustrated in the screenshot below Date 2013 11 07 ESABASE2 Debris Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 40 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig etate i member of the ckc group E Laoi xi io Ground Test NASA ISS BLE 1 399999976158142 1 399999976158142 Density g cm 3 Threshold Thickness cm a 0 15865212678909302 0 1384488344192505 0 300 1 399999976158142 0 12456725537776947 j 1 399999976158142 0 11426488310098648 0 275 0 0 1 399999976158142 0 106222003698349 9 99999970909292 1 399999976158142 0 19693270325660706 0 250 9 99999970909292 1 399999976158142 0 16253291070461273 9 99999970909292 1 399999976158142 0 14183542132377625 0 295 9 99999970909292 1 399999976158142 0 12761428952217102 2 9 99999970909292 1 399999976158142 0 11705990135669708 5 0 200 9 99999970909292 1 399999976158142 0 10882028937339783 2 19 99999941818584 1 399999976158142 0 21206402778625488 E 0175 19 99999941818584 1 399999976158142 0 17502112686634064 a 19 99999941818584 1 399999976158142 0 15273334085941315 La 19 99999941818584 1 399999976158142 0 13741952180862427 0 150 19 99999941818584 1 399999976158142 0 12605419754981995 2 19 99999941818584 1 399999976158142 0 11718149483203888 5 0 125 30
70. n section 2 3 1 For the case of an abstracted lunar mission three analyses have to be performed Each with the same geometry but for the two analyses with ParkinOrbit and TransferOrbit mission files the debris file for orbits around the Earth has to be used The last analysis is combined of the geometry the 7argetOrbit and the debris files for the orbits around the Moon After the performance of all three analysis the results need to be combined in a manual post processing to get the results of the whole mission ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 73 74 Et To use a trajectory file it can be simply chosen in the drop down menu of the mission files as shown in Figure 3 7 member of the ckc group 2 Geometric Debris Analysis Geometric Debris Analysis Please choose the input Files For the analysis Project Mission TransterExamplelMJD Debris Earth nalysis only preprocessing to verify pointing and kinematic Faster Slim Results no 3D results will be created Generate output Filename Filename debris result 2013 04 23 16 11 47 Report options Complete listing of all Figure 3 7 Choosing a trajectory file Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Fin
71. nd choosing only one active side because the re sults can otherwise not be correctly assigned to an element side Please note In NASA90 the average instead of the sum of both sides is taken This is a known bug And with this the geometry file is ready and we can move to the Debris input editor ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 15 74 El member of the ckc group 2 2 Debris Input Complementing the Debris parameters bound to the geometry see previous section the global Debris Meteoroid input parameters are all specified in the Debris input editor This editor is divided into three tabs e Debris Main Tab Specifies the parameters for the geometrical analysis see section 2 2 1 e Ground Test Tab An efficient way to test damage equations see section 2 2 2 e Non Geometric Analysis Tab Allows a fast guess for the expected flux values on a specific orbit see section 2 2 3 2 2 1 Debris Main Tab The main tab of the Debris input editor contains four major blocks for specifying geometrical analysis input parameters e Model selection Allows you to choose among debris and meteoroid models and to edit dedicated model parameters see section 2 2 1 1 e Size boundaries Limits on the type of debris or meteoroids to be con
72. ng orbit descriptions 3 1 1 1 The Parking Orbit Before the start of the journey to Moon the spacecraft is placed in an orbit around the Earth A possibility is the low Earth orbit of the ISS The basic values of such an orbit can be e Central body centre of motion Earth e Semi major axis 6785 km e Eccentricity 0 001 e Inclination 51 6 deg e Other angles 0 0 deg The mission starts on January the 1 2013 at 0 00 The orbital period of the orbit is ca 92 7 minutes let s say that 3 orbits are completed before starting the transfer which means a mission duration of 278 1 minutes for the LEO Thus the end epoch is January the 1 2013 at 4 38 and 6 seconds The mission file can be created as described in 1 section 3 1 The filename ParkingOrbit will be used in the text to identify the orbit Figure 3 2 shows the mission editor with the parameters applied as introduced before Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 66 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Et member of the ckc group ParkingOrbit amp 3 Orbit Central body Earth v Orbit Type GEN v Semi major Axis 6785 0 Perigee Altitude 400 075 Eccentricity 0 0010 Apogee Altitude 413 645 Inclination 51 6 RAAN 0 0 Argument of perigee 0 0 True Anomaly 0 0 Solar t
73. oc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 23 74 El member of the ckc group 2 2 1 1 4 Debris model NASA90 NASA90 16 is an analytical debris model developed by NASA which provides a simple and very fast debris flux calculation but does not fully reflect the current knowledge of the Earth s debris environment in particular the existence of a large number of particles on ec centric orbits Upon clicking the Edit Edit button the NASA90 input parameters dialog is opened as shown in the screenshot below Debris Model 45490 Options Debris density For constant density gfcm3 2 6 Annual mass growth 0 05 Annual Fragment growth 0 02 The solar Flux 10 22 Win He 70 0 Minimum debris impact velocity km s 0 0 Maximum debris impact velocity km s A j i Cancel Figure 2 10 Debris input editor main tab Model Selection NASA90 As with all debris models the average density of the debris material can be specified The debris mass P and fragments number Q annual growth rates are specified as per centage where 1 100 growth It is recommended to use the default values Solar flux is used to specify the solar activity appropriate values for the mission duration can e g be retrieved using the publicly available SWENET database 22 At the bottom you see the debris velocity range namely the minimum and maximum debris impact velocity to be considered
74. occononeniononencanononcanononcanonenianeneninrs 13 Figure 2 2 Debris Shielding parameters ococcoconociononociononeniononencorononcarononcaroneninneneninss 14 Figure 2 3 Geometry editor Meshing page ccocococcoconocconononionononconononcanononcanononennaneninss 15 Figure 2 4 Debris input editor Main tab ccoconocioconociononenconononiononeninnononcnnoneninnanenenss 17 Figure 2 5 Debris input editor main tab Model Selection ococcoconocionenocionenonionononnnss 18 Figure 2 6 Debris input editor main tab Model Selection MASTER 2001 occccocococc 19 Figure 2 7 Cumulative flux vs particle diameter for an ISS like orbit MASTER 2001 20 Figure 2 8 Debris input editor main tab Model Selection MASTER 2005 0000 22 Figure 2 9 Debris input editor main tab Model Selection MASTER 2009 coccccococooco 23 Figure 2 10 Debris input editor main tab Model Selection NASAOO ococococcccononononononns 24 Figure 2 11 Debris input editor main tab model selection ORDEM 2000 nsss 25 Figure 2 12 Debris input editor main tab Model Selection Gr N cocococococccconanononononos 26 Figure 2 13 Debris input editor main tab Model Selection Divine Staubach 27 Figure 2 14 Debris input editor main tab Model Selection MEM ccecsesecseeeeneeeeneees 28 Figure 2 15 Debris input editor main tab Model Selection LunarMEM sceceeeeeeneees 29 Figure 2 16 Deb
75. oid impact velocity Masa90 and HRMP only kms 11 0 Ray Tracing Maximum meteoroid impact velocity Masa90 and HRMP only kms 72 0 Primary rays 100 Seco Figure 3 6 Taylor HRMP activation with the Edit button for Grun 3 2 2 Specifics for Trajectory File The trajectory file can be combined with a limited number of models The available models are selected according to the advantages and disadvantages described in 3 2 1 Due to the possibility to tailor the results to desired arcs and handling a higher variety of orbits the MASTER 2009 model is available for the debris analysis The models Grun MEM and LunarMEM can be combined with a trajectory file Thereby the choice of MEM or of LunarMEM means the same to the software It automatically switches from MEM to LunarMEM if the centre of motion is identified to be the Moon Since the debris and the mission files are independent a try for each pair of files can be given Non compatible files will result in an error message which should describe the prob lem 3 3 Perform an Analysis Three mission files were presented in section 3 1 abstracting the lunar mission and two de bris files were suggested Earth MASTER 2009 MEM and Moon LunarMEM in section 3 2 Also a geometry is required for a geometry analysis A sample geometry is generated in ESABASE2 Framework software user manual 1 in section 3 2 this can be used for the analysis How to perform an analysis is described i
76. ow to the right the last selected run type will be repeated Choose the first entry Run geometric Debris Analysis A wizard as illustrated by the follow ing screenshot will appear ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05_ 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 45 74 El member of the ckc group EA A Analysis Geometric Debris Analysis Please choose the input Files For the analysis Project debris testing Satellite test uritc 5 061135 Full Mission test uritc 5 061155 Debris test uritc 5 061M20054 015 Only preprocessing to verify pointing and kinematic Faster Slim Results no 3D results will be created Generate output Filename Filename debris result 2009 07 06 22 27 57 Report options Complete listing of all e Figure 2 30 Geometric Debris analysis Run wizard In the first line you specify a project from your workspace then the next three combo boxes will only show files from this project A spacecraft geometry a mission file and a de bris input file must be chosen Activating the Only Preprocessing checkbox will stop the analysis after pointing and kine matics have been calculated It is useful to check the correctness of the pointing and kine matics settings without running a complete and possibly time consuming debris or meteoroid an
77. r_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 43 74 El The plate orientation can be one of the following member of the ckc group e Randomly tumbling This is the random tumbling plate RTP mode It often corre sponds to the environment models themselves and is an effective way to get a quick first order assessment of the micro particle environment risk for a mission e Oriented For this mode azimuth and zenith angles of the plate normal can be de fined o The azimuth angle is the angle with respect to the velocity direction 0 deg corresponds to the ram direction positive towards right o The zenith angle is the angle to the space zenith direction 0 deg corre sponds to the space direction In both cases the area of the plate can be defined Normally the default 1 m is used but a specific area can be specified instead e g in case of a detector or other special surface 2 2 3 3 Result Log The results of a non geometrical analysis are displayed in the bottom part of the Debris input editor You can select between four different sets of results e hits vs crater size e debris and meteoroid flux and damage results e failures vs ballistic limit e orbit propagation results All results will be presented in textual form ASCII files The results listings are also available in the ListingFiles folder of the corresponding project directory T
78. result editor 2D Results reporting This report details the chart properties and below the chart itself followed by the data val ues represented in the chart on the second and following pages It is thus a complete data description of a value pair s relation suitable for distribution to your colleagues You may either print the report press the print button or choose Export gt Save as PDF for electronic distribution ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 61 74 El member of the ckc group 2 4 3 Listings The original ESABASE produced LIS files or listing files containing all debris results in one text file This ability is also available in ESABASE2 in order to stay compatible to many post processing tools The listings are shown on the Listings tab of the debris result editor as shown in the figure below Landsat _debris result 2009 07 06 16 41 06 E3 E Result Log Deb Met e con 18 ORBITAL POINT NUMBER 1 CLASSICAL ORBITAL ELEMENTO A 6775 20 km E O 0000046 Inclination 51 600 deq RAAT O 000 deg ArgotPer O 00 deq True Anomaly O 000 deq True Latitude o EL Es Fc Imp ingle Imp Vel Crat Area Imp Flux Imp Flue Mb Impacts Fail Flux F degrees km 3 yr fie Year forme mea Year 1 1 04 46
79. ris input editor main tab Model Selection Streams cscsecsceceeeeeenenes 30 Figure 2 17 Debris input editor main tab Model Selection Alpha Beta Separation 31 Figure 2 18 Debris input editor main tab Model Selection Apex Enhancement 32 Figure 2 19 Debris input editor main tab Size Boundaries cocococcccococononenencananononenenens 33 Figure 2 20 Debris input editor main tab Ray TracinQ coccccoconocconenocionenonnanononianonononos 34 Figure 2 21 Debris input editor main tab Damage Model ocococccconcciononocionenonionenonnnss 35 Figure 2 22 Finding the User Subroutine DLL ococccconocicnonocionenocionononinnononcanononianononinss 37 Figure 2 23 Example user SUDrOUTIN occcconoccononociononenionononinnononcorononcnnonencaronenennenenenss 38 Figure 2 24 Debris input editor Ground Test tab coccococconccconncconncnonnononnanoninnononnonnanons 40 Figure 2 25 Debris input editor Ground Test tab RUN ocococcoconocconononiononencanononiananoninss 41 Figure 2 26 Debris input editor Non Geometric Analysis tab oococcccononocconenonianenonnnso 42 Figure 2 27 Debris input editor Non Geometric Analysis tab Single and Multi wall 43 Figure 2 28 Debris input editor Non Geometric Analysis tab Orientation and Area 43 ESABASE2 Debris Date Software User Manual Revision Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State etamax sp
80. rovision of the information exist it can theoretically be placed eve rywhere in the head before BEGIN but it is recommended to group the inputs for better readability The input is handled not case sensitive Origin provides the information of the starting celestial body Possible inputs are Earth and Moon This input is optional if no origin is given Earth is used as default Target provides the information of the journey s destination Possible inputs are Earth and Moon It is mandatory For trajectories around one celestial body only Earth orbit or only lunar orbit the origin and the target must be equal Coordinates provides the information of the coordinate frame that is used for the given state vectors It is mandatory Possible inputs are ECI and LCI Thus the state vectors can be provided in Earth centred inertial ECI frame which is EME2000 or in lunar centred inertial LCI sometimes also called Moon J2000 LCI is a mean pole z axis IAU node x axis at the epoch of J2000 0 system Epoch provides information of the time format used for the state vector epochs It is mandatory Possible inputs are MJD and UTC MJD indicates that the epochs are given in ESABASE2 Debris Date 2013 11 07 Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 70 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El the modified Julian day 19
81. s provides directional information in the same way as the MASTER 2005 debris model Please note Since the Divine Staubach meteoroid model is implemented in the MASTER Standard application one MASTER 2005 run covers both debris and meteoroid flux determi nation if the corresponding switches are set ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 27 74 El member of the ckc group 2 2 1 1 8 Meteoroid model MEM MEM 20 is a meteoroid model developed by the University of Western Ontario Canada Upon pressing Edit a dialog with the MEM input parameters opens as shown in the figure below Meteorold Model MEM Options Constant meteoroid density gfcn3 2 5 Figure 2 14 Debris input editor main tab Model Selection MEM MEM has no options by itself using a constant meteoroid density of 1 g cm The option available here is used to convert mass to diameter for damage computation We propose to always use 1 g cm Please note that the default 2 5 g cm is fitting only for the other meteoroid models all models use the same parameter within the data model this is the reason that the default in the GUI cannot be 1 g cm MEM is a parametric model of the spatial distribution of sporadic meteoroids The primary source is short period com
82. selected wall is defined as multiwall In the screenshot above you see none chosen and thus all further parameters are dis abled ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 13 74 Et The figure below illustrates the parameters from the Wizard member of the ckc group whole or scattering whole or scattering particle Backup wall thickness Spacing thickness plate 1 plate 2 Figure 2 2 Debris shielding parameters A particle hits the first shield wall and the effect depends besides the impact velocity the impact angle and particle properties such as its diameter and material density on the mate rial density and thickness of the wall The particle is either stopped or penetrates the wall it can remain whole or be scattered into smaller pieces due to the impact If it penetrates it travels the spacing between the walls the same stop penetration scatter happens with the second wall Depending on the remaining energy the particle causes a a crater on or b a penetration of the device behind the wall In a single wall scenario the second wall does not exist and the likelihood of a crater or penetration is considerably increased A failure equation determines whether a particle penetrates the wall configuration
83. sidered in the analysis see section 2 2 1 2 e kay tracing Defines the accuracy of ray tracing results see section 2 2 1 3 e Damage Model Defines a set of failure and damage equation combinations for the Debris analysis see section 2 2 1 4 Within the damage model block the option user subroutine can be selected How to define your own damage equation in a Fortran library will be explained in section 2 2 1 5 Date 2013 11 07 ESABASE2 Debris Revision 159 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 16 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig etaycigiK member of the ckc group The figure below shows the ESABASE2 Debris main tab within the Debris input editor W debris 2 Model Selection Size Boundaries Lower particle diameter 0 0010 Analysis Type debris analysis v Debris Model MASTER 2005 na Upper particle diameter cm Meteorcid Model GAR Edit Min crater diameter 0 0010 cm A Min eject fragments 0 0010 cm Streams Edit Alpha Beta Separation Edit Apex Enhancement Edit Ray Tracing Primary rays Damage Model Cutoff angle Failure Equation Wall 1 Single Wall Thick Plate vw Woll 2 waz srgevar lv Thek Pie x Wall wars Srgeviar y Tari x wat a waa Sralewal y ThekPite x Wall wars Srgeviar y ThekPie x Wall 7 warz Srge via
84. t di ameter is used to compute the probability of a failure using the chosen flux models e The damage size equations which compute the crater diameter of semi infinite tar gets and the hole size of thin targets Again the flux models are then used to com pute the total cratered or perforated area of the surface The figure below shows the damage model setup in the main tab Damage Model Cutoff angle Failure Equation Damage Equation Wall 1 Wall i Shgewat y recae y Ea Wall2 Wall Sngewa v Trik Pee y Ea Wall 2 wars Shalewal v marino x El Wall a Was Srgowat v Thick y Ea Wall s wars Sie wal y Trik Pity Ea Wall o wars Sngewar x Trik ie y Ea Wall7 Wall 7 ngewa v Trek le y Ea Wall wars Shalewal v marino v El Wall 9 walls Sngewar v Trik Pae y Ea Wall 10 vao Sholewat v Thick Pate Ea Wall 11 wait Sine wat v Thx Pie El Wall 12 wall 12 Sige wal y Taek Pe Ea Wall 13 Wall 12 Sige wal y Taek Pw Bal Wall 14 wal i4 Sine wt v ripio El Wall 15 WALLIS Srolewal 7 Thick Pate Ea Figure 2 21 Debris input editor main tab Damage Model There are no conventions concerning the combination of failure and damage equation Single wall as well as multi wall can be combined with crater or hole size equations ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232r
85. t of the various factors the figure below shows the cumulative cross sectional debris flux from different sources on an ISS like orbit 1e 006 launch mission rel obj 10000 fragments m Nak droplets oe 100 SRM slag S SRM AI203 dust E paint flakes eect gt 0 01 ENE sum of all eS 0 0001 1e 006 1e 008 1e 010 1e 012 1e 006 1e 005 0 0001 0 001 0 01 0 1 1 10 100 impactor diameter m Figure 2 7 Cumulative flux vs particle diameter for an ISS like orbit MASTER 2001 MASTER 2001 provides realistic yearly population snapshots for the past and the future The flux calculation is based on the analytic evaluation of the distributions of the size and the orbital elements of the particle population MASTER 2001 Standard application The model considers the population asymmetry induced by the asymmetric distribution of the particle orbits argument of perigee Date 2013 11 07 ESABASE2 Debris Revision 1 5 2 Software User Manual State Final Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc Page 20 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group MASTER 2001 covers the entire altitude range from LEO to GEO 150 km to 37000 km Within the given altitude range there are no restrictions concerning the target orbit so that highly eccentric orbits such as GTO can be analysed The MASTER population snapshots are available from year 1980 to 20
86. the Listings subfolder of the current project folder in order to be more easily accessible to post processing tools member of the ckc group Due to some confusion in the past the interpretation of the Crater vs Crater size LIS file is described in the following section 2 4 3 1 Crater vs Crater size The Figure 2 44 shows an example of a Crater vs Crater size LIS file The name indicates that it tabulates the number of craters again a crater size The results are cumulative Result Log Crater ve Cratersize Ww HITS vs CRATER SIZE File K ESABASE2 temp ESA BASE2 6 0 0 workspace Example ListingFiles Plate Grun CRT D CRT D IELMT Elm rea 1000E O2 1000E O01 1000E 00 1000E 01 1000E 02 1000E 05 1000E 04 1 0 723 17946E 035 15043E 03 32011E 01 25539E 02 55527E 06 OO000E 00 OO000E 00 Es O ves 175 7P1E 05S 14609E 03 315453E 01 25253E D2 52 2IE 06 OO000E 00 OO000E 00 3 0 015 1768TE 01 12261E 01 197249E 01 14002E 04 28367E 08 OO000E 00 OO000E 00 4 0 015 17503E 01 12256E 01 19631E 01 13774E 04 27009E 083 OD0O00E 00 OO00U0E 00 5 0 017 27159E 00 65109E 01 9004E 03 10363E 06 76045E 11i 00 00E 00 O0000E 00 6 0 017 2 6408E 00 64745E 01 31146E 035 11697E 06 11506E 10 O0000E 00 O0000E 00 T 0 015 17665E 01 12050E 01 18494E 01 12509 04 5269 06 00000E 00 O0000E 00 z 0 015 17975E 01 12311E 01 19380E 01 13432E 04 270e9E 08 000 00E 00 OO000E 00 a 0 017 29001E 01 19323E 01 29
87. tion Orbit pe Lunar Transfer Trajectory T Progress of moon in its orbit Figure 3 1 Scheme of the lunar mission of Chandrayaan 1 source North East India News The Figure 3 1 displays an example of a trajectory of a lunar mission as was used for Chandrayaan 1 3 1 Lunar Mission Two different approaches can be used for an analysis of a lunar mission e Abstraction of the mission by splitting it into multiple orbits e Describing the mission with state vectors provided via a trajectory file In the first case the results of the individual orbits have to be post processed manually to obtain the results for the whole mission The second case provides complete mission results In this case a trajectory file is used describing the whole mission with up to 100 orbital points Both approaches for the mission definition are described in more detail in the following sec tions ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01 05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 65 74 El 3 1 1 Abstraction of the Lunar Mission member of the ckc group A lunar mission can be abstracted by the definition of multiple orbits The simplest case in cludes three orbits only the journey from Earth to Moon e A low Earth orbit LEO which is often called the parking orbit e A highly elliptic
88. tor main tab Model Selection As a starting point to the Debris analysis you have the choice between debris or meteoroid analyses or both see first combo box Analysis Type Depending on your choice the De bris Model or Meteoroid Model combo boxes will be enabled or disabled ESABASE2 Debris provides five Debris models MASTER 2001 MASTER 2005 MASTER 2009 ORDEM 2000 NASA90 and four meteoroid models Gr n Divine Staubach MEM Lunar MEM Most of the models accept detailed input parameters Press the Edit button to the right of the model combo boxes Additional parameters Streams Alpha Beta Separation and Apex Enhancement are shown below they are valid only for some models Details are given in the sections 2 2 1 1 10 2 2 1 1 11 and 2 2 1 1 12 For the analysis on lunar orbits only the two meteoroid models Gr n and LunarMEM are ap plicable no debris models will be accepted In combination with a trajectory file the debris model MASTER 2009 and the meteoroid models Gr n MEM and LunarMEM are applicable The use of other models for lunar orbits or with a trajectory files than listed here causes a stop of the analysis execution informing the user about the invalid configuration In the following the available models will be described together with their associated pa rameters This description is necessarily short a full description can be found in the ESABASE2 Debris Technical Description 2 Date 2013 11 07
89. ults options You can customize the following chart properties e x y axis o Label Text Changes the text of the axis label o Grid Displays horizontal vertical dashed lines o Label font Label font size Label font style Changes the appearance of the axis label o Maximum Minimum The value range that this chart shows o Number format The format of the number labels e g the number of decimal places can be specified o Number scaling Choose between linear or logarithmic scale o Graph title The title text above the chart o Title visible Show or hide the title text o Title Font Title Font Size Title Font Style The appearance of the title text e Legend o Legend Show or hide the legend o Legend Font Legend Font Size Legend Font Style The appearance of the legend e Background The background color of the chart e Box Shows or hides the box around the graph ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference R077 232rep_01_05_02_Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 59 74 member of the ckc group e Axis and label colour The colour of the axis lines and the labels e Major tick labels Shows or hides number labels at the major ticks e Minor tick marks Display small ticks between the major ticks e Ratio Set a fixed aspect ratio e Auto scaling Re scales the chart e Graph Type
90. ver_Debris doc Page 50 74 etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig El member of the ckc group 2 4 Debris Results A geometric Debris analysis produces a debris result file which is interpreted by the Debris result editor The editor contains the following functionalities e 3D Results Shows the spacecraft geometry overlaid with the impact flux or other output parameters see section 2 4 1 e 2D Results Graphs with different data about flux distributions at the orbital points as well as average flux distributions see section 2 4 2 e Listings In tradition of the original ESABASE this tab shows the LIS files produced by the Debris solver see section 2 4 3 e Notes A blank text area for your own notes see section 2 4 4 2 4 1 3D Results The following figure shows the 3D Results tab in a debris result editor EN File Edit Window Help t E Q Reset perspective O e E ESABASE2 Explorer O E Landsat _debris result 2009 07 06 16 41 06 5 ES t Pe P wm D 4 ra e B E tc_07_ landsat a O pz ia a g PA pt ty o Y E Landsat Total Impact Flux 1 m 2 year E Landsat _debris result 2009 07 Orbital Point 4 W Landsat _debris Y Landsat _ mission lt Tz Outline 3 lt E Properties Property ID Notes Listings 3D Results 2D Results Figure 2 35 Debris result editor 3D Results You can see a spacecraft geometry Landsat7 with total impact flu
91. x visualised by colour codes on the elements and decoded by the colour scale on the right At the top of the editor the same toolbar as in the geometry editor appears allowing you to zoom rotate and scroll around the spacecraft ESABASE2 Debris Date 2013 11 07 Software User Manual Revision 1 5 2 Reference RO77 232rep_01_05 02 Software_User_Manual_Solver_Debris doc State Final etamax space GmbH Frankfurter Str 3 d 38122 Braunschweig Page 51 74 El member of the ckc group Additionally you can rightclick into the 3D area to invoke the context menu which contains the following options e Colour Defines the result value to be laid over the S C geometry default is total im pact flux e Orbital Point Whether to show results for the entire mission single orbital points or an orbital arc e Coordinate Systems Whether to display coordinate systems alongside the S C ge ometry e Element Chart Shows the results for one single geometrical element select one with Shift Leftclick to enable 2 4 1 1 Colour Debris results come in multiple variables e g impact flux or failure flux and either per year or over the entire mission time Only one of these variables at a time can be laid over the geometry model To choose a result set to be displayed rightclick the 3D view to open the context menu then choose Colour gt lt Variable gt as shown in the following figure E Landsat _de

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