R-DAS User Manual
Contents
1. 5555 22 6 1 FIRMWARE testes tev E 22 6 1 1 22 6 1 2 6 1 3 6 1 4 6 1 5 6 1 6 6 1 7 6 1 8 6 2 6 2 1 ARN 22 6 2 2 inaia 6 2 3 V2 2 6 2 4 22 6 2 5 23 6 2 6 A 23 OUTPUT BOARD 2 24 7 1 aves 7 2 R DAS IGNITER BOARD SPECIFICATIONS 7 3 OPERATION La ata eee 2 15 AND TEMPERATURE EXPANSION BOARD OPTION 8 1 ELA eee Cada Phat ak 8 2 SPECIFICATION 8 3 OPERATION GPS EXPANSION BOARD OPTION ccssssssssssssssssssssssssssssssssssesessssesessssssssessss2. 2 3 3 CONTI TE 12 2 3 4 LEED 5 12 2 4 IGNITER 12 3 1 CONFIGURING RDAS wis 13 3 1 1 casts dala 13 3 1 2 aati Lega 13 3 1 3 Sampling Settings 3 2 DOWNLOADING DATA ceccescesseseesecsecsecseeseeseeseseeececseesssessesscascascasesaesaesaesaeeaeeates 3 3 EXPORT science 3 4 UPGRADE R DAS FIRMWARE neronen naaa 3 5 3 6 lt 5 3 7 WINDOWS USER INTERFACE NEEE SASE SESTO ESEA 15 3 8 PALM USER INTERFACE a EE EEEE T NE A 15 CONNECTOR sesiis 16 4 1 J1 AND 12 IGNITER CURRENT SELECTORS CLASSIC ONLY 4 2
3. 11 Download the data as usual File Download 12 Also download GPS data File Download GPS Click index and wait A list of the latest flights is given Note that the time is GPS time i e UTC time 13 Click the flight that belongs to the downloaded data and press download 14 Save rdf file this will now also contain the downloaded GPS data 15 Export GPS data to a txt file File Export GPS data and read the generated text file manually all SI units Alternatively the R DAS plotting program to be released soon can be used to plot the flight trajectory parallel to obtain a useable battery life A single 9V battery is not sufficient and has often problem delivering the total current of more than 250mA for R DAS and GPS Another option is to use a small NiCd battery pack of 9 12V Q Because the GPS unit consumes about 200mA it is recommended to use several 9V batteries in center pin is not shortened against the outer shield It is possible to use a passive antenna by opening a NOTE The SMA antenna input of the GPS units also powers the antenna with 5V Make sure that the q solder jumper on top of the unit Please contact AED if you plan to use your own antenna 30
4. 40 185 C 9 Sensitivity 22 5 12 5 mV C mV F Resolution 0 217 0 391 C F Uncalibrated accuracy full range 2 0 2 9 oC F Connected to ADC2 EEPROM Type Memor Power supply Voltage Current 9 Physical Dimensions 48 x 48 1 89 x 1 89 Weight 18 0 6 Temperature range 0 to 70 8 3 Operation The ADXL250 expansion board is connected to the R DAS by means of a 14 wire ribbon cable If only one expansion board is attached a simple cable with two crimps connectors is sufficient These cables are available from AED If more expansion boards are used in a single flight additional crimp connectors have to be press mounted to the wire cable crimp connectors are available from AED or your local electronics shop Make sure that all connectors on the ribbon cable are connected the same way This is easily verified by looking at the small triangles at the connector and make sure they are all on the same side of the ribbon cable 27 The user can select range of acceleration measurement by setting 2 jumpers The range is printed next to the jumper rows Each axis can have a different jumper setting The positive directions of the measurement axis are indicated by the arrows on the printed circuit board The temperature sensor range is fixed and cannot be altered by the user On the bottom of the PCB there are two small solder jumpers for PC pull up From factory these are closed If you have several boards conn
5. 1 Capacitor 2200 uF 2 External power supply Test current lt 1 Power supply Voltage 9 to 10 6 Current 70 90 Physical Dimensions 125x48 4 92 1 89 90x36 3 54x1 42 inch Weight without 9V amp battery holder 65 2 3 3211 1 gram oz Weight with 9V battery holder 78 2 8 n a gram oz Weight with 9V battery and holder 114 4 0 gram 07 14 5 Electrical layout Figure 1 1 shows a block diagram of R DAS The computational heart of the unit consists of the microprocessor UP together with its memory R DAS has a volatile memory for data storage RAM and a nonvolatile FLASH EEPROM for permanent data storage The system further consists of a acceleration transducer a pressure sensor igniter stages and a serial port Power is supplied from the power supply The digital and analog power supplies are completely separated R DAS classic only A buzzer informs the user of the status see section 2 3 2 power supply Analog Digital 1O Figure 1 1 Block diagram of R DAS The FLASH memory is organized in 64kB sectors which be erased independently In the first sector the bootloader code BIOS of R DAS is stored This program starts the main application stored in the second sector It also allows upgrade of the main program by uploading the main program binary code to R DAS The other remaining six sectors are used for data storage This data memory is not erased until R D
6. For more details see section 5 2 4 3 Breakwire Except for G switch arming R DAS can also be triggered with a breakwire which is attached to connector J4 This feature also allows the user to test the R DAS system on the ground and for other data acquisition purposes The breakwire can be configured make or break contact for triggering via the user interface 4 4 J5 Expansion port The expansion port J5 accepts analog and digital signals from user supplied measurement systems e g roll sensor temperature sensor etc 15 also supplies the additional circuit with power from the R DAS power supply The table below d each of the individual pins of 15 Pin 1 is marked by a small triangle on the side of the slit of the connector Table 4 1 Pin layout of R DAS expansion port Pin Description Specifications 1 2 Vs Power supply Power supply for external experiments app R DAS power supply voltage 0 6V due to protection diode on R DAS 3 103 Digital input 3 Normal TTL specifications 4 102 Digital input 2 Normal TTL specifications 5 101 Digital input 1 Normal TTL specifications internal pull up 10kQ 6 100 Digital input 0 Normal TTL specifications internal pull up 10kQ 7 ADCO Analog input 0 Analog inputs 8 ADC1 Analog input 1 Nominal input 0 5 9 ADC2 Analog input 2 Maximum input 0 2 5 2 V 10 ADC3 Analog input 3 Input impedance 10 50 KQ 11 ADC4 Analog input 4 Input capa
7. e IC bus The I O connector features a serial 1 This allows simple extension of the R DAS with e g expansion boards like LCD screens remote data acquisition boards or GPS What extensions will be available in the future will be determined by customer demands 1 2 Main differences between R DAS classic and R DAS compact _ R DAS classic R DAS compact 125 x 48 mm 4 92 x 1 89 inch 90 x 36 mm 3 54 x 1 42 inch On off switch yes yes 1 3 R DAS Specifications The specifications of R DAS as summarized in Table 1 1 Table 1 1 R DAS Specifications po Compact Processor Type Philips 80C552 Clock frequenc 11 0952 MHz 2 kB Flash EEPROM 512 kB Acceleration transducer Type Analog Devices ADXL 150 JQC Range 50 to 50 Resolution 0 1 Pressure transducer Type Motorola MPXS4100A Range 20 to 105 Resolution Analog inputs Nr of channels Input span Input impedance Input capacitance Conversion time us Max sampling rate per channel samples sec Digital inputs Nr of inputs Input specifications Triggering G switch gt 2 5 g for 0 25 sec Breakwire make or break contact Igniter output stage Nr of output stages 2 drogue and main Current Classic user selectable 1 Current source 1A 2 Current limited by circuit resistance Compact limited by supply max app 2 5A Igniter supply Classic user selectable 1 Capacitor 2200uF 2 R DAS power supply 3 External power supply Compact
8. 13 IGNITION POWER SELECT CLASSIC ONLY csssssssscsscsscsscsseesecsecsecsscsacseeseeseesseeeseasssssacseecessescssseaeeascaecsecaecsaeseeseesasenees 4 3 J4 BREAKWIRE 4 4 15 EXPANSION PORT 4 5 JO RESET CLASSIC ONLY 4 6 JLT 6 sesso 4 7 Bea ooo SISSIES E 4 8 J12 POWER CONNECTOR COMPACT ONLY c sssssssssscsscsscsscssessecsecsecssssscsseseessessesssensenssnssnecasensessessesaeceecsecsasaassasensensenees 4 9 J13 SAFE ARRM CONNECTOR COMPACT ONLY ccccsssscssssssscsesscsecsesscaescesscaessessseesesaescesesacseesesecsesaeseesesacasesesscseacaeeeseaes 8 19 5 1 MECHANICAL OUTLINE RDAS 19 5 2 OUTPUT STAGES CLASSIC ONLY harese R Ee ES EEEE AREE ES EEEE E S e s 19 5 3 ROSAIN DM N i e EENE AE T AEE EEE E EA E A eh EEEE 21 5 3 1 Calibration of the acceleration 21 5 3 2 Testing of the G switch 5 3 3 Wiring harness 5 3 4 E KER
9. allows the user to switch on the R DAS for a system check e g to see if the igniters have been attached correctly If the unit is switched off before a lock was obtained no entrance will be will be generated in the table A summary to setup R DAS for use with GPS and test the unit 1 Attach the GPS antenna to the GPS board golden SMA connector 2 Connect the GPS board to R DAS via the 14 pin expansion connector 3 Make sure you have the latest version of the R DAS user interface V2 3 or later 4 Upgrade R DAS with the firmware V2 5 or later 5 Configure R DAS Make sure to switch on GPS support Configure Configure R DAS switch GPS on in the GPS tab dialog 6 Press capacity to check to see if everything is connected properly It should report something like the following text The GPS unit has enough free flash memory to hold at least 454 minutes of logging data 7 After power up the GPS unit will initialize for five seconds the red LED is on 8 Now the satellites are being tracked When a valid fix has been obtained the LED will be switched on and two times three tones are beeped by the R DAS During a real flight this indicates that the GPS has obtained a valid fix and that the rocket can be launched 9 Now trigger R DAS to perform a dummy start Either by break wire or acceleration holding up side down for a while and then up again 10 Walk around a bit during the flight to get different GPS coordinates
10. consumption can be reduced classic only There is a small solder jumper on the back of the R DAS marked loud buzzer By opening this jumper the volume is decreased The factory setting is a loud buzzer 2 33 Continuity LED s Near the two igniter terminals are two red LED s These LED s are on when there is no continuity between the terminal outputs 2 3 4 Status LED Near the processor there is a green LED This LED informs about the status of R DAS For the moment the LED has the same function as the buzzer 2 4 Igniter connection Always test your igniters for compatibility with R DAS before use for a real flight NOTE To reduce power consumption of the R DAS shorten the igniter outputs by simple wires when not in use Each continuity LED uses approximately 7 mA This also prevents unwanted warnings for igniter discontinuity three buzzes from Table 2 1 If you are using high power output J1 J2 shorted or direct power selected by J3 see Chapter 4 then use a 1kOhm resistor in stead of a short to prevent loss of supply power during igniter output 12 3 Userinterface The main functions of R DAS user interface are 1 Configure R DAS 2 Download flight data including GPS data with optional GPS unit 3 Save view and export the flight data 4 Upgrade the R DAS program firmware The main window of the user interface is shown in Fig 3 1 Except for the conventional pull down menu items file ope
11. history This section summarizes the different versions of the R DAS firmware and the R DAS interface program The following convention is followed Version numbers are denoted as Vx yz A change of x indicates a major change of functionality Program changes of minor importance small functional changes and bug fixes are recognized by a change of z 61 Firmware Software for R DAS V1 0 hardware This unit had a limited distribution in the Netherlands Software for new R DAS design This specific version was for the prototype of new hardware 6 1 1 V1 x 6 1 2 V2 0 6 1 3 V2 1 x 6 1 4 V2 2 6 1 5 V2 3 6 1 6 V2 4 6 1 7 V3 0 6 1 8 V3 1 V2 1 First public release of R DAS firmware Fully functional and stable version v2 11 Removed bug when using both timed and smart recovery V2 1 firmware only used barometric information for main parachute deployment Support for igniter expansion board New download procedure especially for handhelds with CRC error checking Improved hardware checking Buzzes added for serious errors beeps for general status information Additional information in digital outputs bit 3 is set when timed recovery was used for smart recovery bit 3 is cleared Bug fix when testing R DAS on the ground drogue output stage remained open when main parachute was ejected immediately after drogue parachute Cleanup of source code Altitude is reported by beeping Igniter discontinuity problem is reported by buz
12. is not designed for use in life support appliances devices or systems where malfunction of this product can reasonable be expected to result in personal injury AED s customers using or selling these products for use in such applications do so at their own risk and agree to fully indemnify AED for any damages resulting from such improper use or sale Product warranty AED warrants that the R DAS unit is free of defects and that it will operate at a satisfactory level of performance for a period of one year from the original date of purchase If the unit fails to operate as specified notify AED within the warranty period Modifications to the unit void all warranty Glossary ADC Analog to Digital Conversion Process of converting analog sensor data to digital integer data which can be processed and stored BOOTLOADER Program that is executed when R DAS is switched on The bootloader automatically starts boots the main R DAS application if there is no intervention within four seconds after power up Other tasks it performs are memory check and upgrading of R DAS firmware the bootloader itself cannot be upgraded without special software BREAKWIRE Connection which is broken during lift off This can be an actual wire attached to the launch pad or rail but can also be a switch R DAS also allows inverting breakwire configuration In this case triggering takes place when a contact is made instead of broken CEP The radius of a
13. of the additional igniter outputs was sometimes selected Added GPS functionality configure download and export data clear GPS memory Now R DAS Data File contains both R DAS and GPS if applicable data User interface compresses data during save to minimize data file size New default values for sensors Export image support GIF export Scroll mouse can be used to zoom in out in graphs Added telemetry functionality configure telemetry system Receive save and view data like normal R DAS files Export data now also supported on WinCE 23 igniter output board option This section of the manual describes the igniter output board for R DAS The igniter output board is an extension for R DAS The board adds two additional pyro outputs to the system Up to four of these boards can be added to a single R DAS system 71 Features Features of the igniter expansion board 2 additional output stages per board maximum of four igniter boards can be added to a single R DAS unit resulting in a total of 10 output stages including R DAS outputs e Configurable power supply from capacitor discharge or separate battery e Configurable current A using current regulator perfect for Davey Fire or maximum current e High power FET output stages with very low internal ON resistance lt 0 03 Ohm for high current igniters e Continuity check with LED s Output stage status LED s e Timing can be configured from
14. within the R DAS windows user interface e Automatic detection of igniter boards by R DAS Small board size only 48 x 48 mm 1 89 x 1 89 inch The igniter expansion board is attached to the R DAS via the expansion port A simple flatcable connects the units The maximum flatcable length is 1 meter This makes it possible to place the igniter expansion board where it is needed Possible use of the igniter expansion board Multi stage rockets Air starts Smoke generators Pyrotechnic air brakes Back up charges Etc 24 72 R DAS igniter board specifications The specifications of R DAS igniter expansion as summarized in Table 7 1 Table 7 1 R DAS igniter expansion board specifications 2 Current User selectable 1 Current source 1A 2 Current limited by circuit resistance Igniter supply User selectable 4 Capacitor 2200UF 5 External power suppl Power supply Voltage 9 to 15 from R DAS Current 15 Physical Dimensions 48 x 48 1 89 x 1 89 inch Weight 23 0 8 gram 2 Temperature range 0 to 70 C 7 3 Operation To reduce R DAS circuit board size the unit has components on both sides of the board The figure below shows the layout on the topside of the igniter circuit board The igniter board can be mounted using the four holes at the corners of the unit The distance between the holes at the corners is the same as that of R DAS Because all components and PCB wiring is at least 1 mm of the edges it i
15. AS detected a liftoff by either the G switch or the breakwire This makes it possible to extract the data after the R DAS has been switched off or when power has been down due to a depleted battery Sectors 2 6 384 Kbytes 512 Kbytes Sector 1 64 Kbytes Sector0 64 Kbytes Fig 1 2 Memory map of the FLASH memory 2 R DAS Operation This chapter describes the normal operating procedure of R DAS including unit mounting and program flow 21 R DAS mounting To reduce R DAS circuit board size the unit has components on both sides of the board The figure below shows the layout on the topside of the R DAS circuit board The processor flash memory on off switch and serial port connector are easily identified The R DAS can be mounted using the four holes at the corners of the unit Note the mounting direction for flight as indicated in this figure Attach R DAS to the panel by 4 bolts R DAS classic or 2 bolts using the supplied standoffs R DAS compact The best way to mount R DAS is to use standoffs This attaches R DAS securely and prevents vibrations of the PCB Because all components and PCB wiring is at least mm of the edges it is also possible to mount the circuit board in small slots Mounting hole 2x Serial port Flash memory _ Processor Main parachute Drogue parachute Drogue parachute Main parachute Mounting hole 4x Figure 2 1 R DAS with some of the most important components Le
16. R DAS User Manual Rocket Data Acquisition System R DAS hardware V2 x V3 x Firmware V3 1 User Manual V1 5 16 June 2001 AED Electronics Bertelindislaan 3 5581 CS Waalre The Netherlands E mail aed iae nl Phone fax 31 40 2213972 For the latest version of this manual look at http www iae nl users aed rdas download htm 1999 2001 by AED Waalre The Netherlands Product disclaimer and limit of liability The R DAS unit is intended for use in model high power rockets only Do not use this device for any other purpose than specified in this manual Please read this manual carefully and make sure to understand all aspects related to the safe operation of the device Never fly rockets overhead of people building or other properties Always use remotely controlled SAFE ARM devices to inhibit pyrotechnic devices attached to R DAS Because the use and application of the R DAS unit is beyond our control the purchaser or user agrees to hold harmless AED from any and all claims demands actions debts liabilities judgements costs and attorney fees arising out of claimed on account of or in any manner predicated upon loss or damage to property of or injuries to or the death of any and all persons arising out of the use of this equipment Due to the nature of electronic devices the application and environments for those devices the possibility of failure can never be totally ruled out Life support applications This product
17. ailable when the digital I O was selected for measurement as the flight phase information is stored as part of the digital I O byte Furthermore there is the selection of the acceleration and altitude data The other 5 buttons select the user analog input channels 0 to 5 V The measured data can also be exported as an ASCII file There are two different possibilities Either export the raw data use File gt Export raw data or export data that has been converted using the calibration values use File gt Export interpreted data The files can be used for further processing in e g a spreadsheet program The header of the file contains a summary of the measurement configuration The raw data is written as measured ADC values Each ADC value corresponds to 5V 1024 steps 4 883 mV Use the calibration values for conversion to real world data Apart from ASCII exporting it is also possible to export the graph as shown in the window as a bitmap bmp file or gif file Use the File Export Image option The data is written as measured ADC values Each ADC value corresponds to 5V 1024 steps 4 888 mV Use the calibration values for conversion to real world data 3 4 Upgrade R DAS firmware The R DAS software is continuously being updated when new expansion hardware becomes available and to improve the algorithms This makes it necessary to be able to upgrade the main program firmware The R DAS user interface allows eas
18. and the connection pins of the battery holder It is also strongly recommended to secure the battery into its holder with a tie rap The best way to do is is to run a tie rap around the battery under the holder h Classic only Because of the harsh environment in the rocket during the powered flight it is 2 2 R DAS Program flow 2 21 Bootloader When R DAS is switched on the bootloader application software is started After two seconds the bootloader automatically starts the main application the actual R DAS program During booting there is a continuous beep from the buzzer to indicate the booting process The bootloader also tests the RAM memory In case of a memory failure the bootloader responds with a low frequency beep from the buzzer The bootloader is also used to upgrade the R DAS main program firmware 2 2 2 Power up checks After the main program is started the program first checks several transducer signals and breakwire connection The accelerometer signal has to be within expected limits and a self test is carried out If the accelerometer signal is not within the allowed range at power up the g switch function is disabled This prevents accidental triggering of the unit in case of a malfunctioning accelerometer The user is warned by the buzzer a continuous signal of 6 short buzzes see buzzer section Also the pressure signal is checked and compared with the allowed interval In case the pressure is not within the expec
19. celeration The transfer function for the temperature is T C 0 217 x ADC2 61 1 or F 0 391 x ADC2 78 0 For the accelerometer a similar procedure is followed using the theoretical sensitivity values from Table 8 1 e g for a 25 g range g 5 1024 67 9 x 0 001 x ADC1 offset The offset is determined from the average value of ADC1 before the liftoff Because the sensitivity of the accelerometer has a large spread the user may want to calibrate the transducer This can be done by selecting the range in which the board will be operated and then holding the board in several directions e g x axis up and down The difference between these two positions is 2g s If the average value with the board up is in ADC counts and the average value with the board down is AVG2 then the resolution is determined from resolution 2 AVG1 AVG2 Values AVGI and 2 can be determined by connecting the board to R DAS and run a dummy flight during which the board is first hold up and then down This data is then exported to a spreadsheet for accurate determination of and AVG2 28 9 GPS expansion board option This Chapter describes the optional Global Position System expansion board shortly GPS board 91 Features Features of the GPS board data logging of 2 velocity number of satellites flight phase UTC time e logging capacity about 25 hours e multiple flight storage up
20. circle centered at the GPS antenna s true position containing 50 of the fixes DOWNLOADING The process of retrieving measured data from the R DAS to the PC EEPROM Electrically Erasable Programmable Read Only Memory FIRMWARE Application software embedded in R DAS This is the program running on the microprocessor of R DAS The firmware can be upgraded with the R DAS windows interface New versions of the firmware are available on AED s web site GPS Global Positioning System A space based radio positioning system which provides accurate position velocity and time data G SWITCH Triggering of R DAS by means of an acceleration signal above a specified threshold 2 5 g for R DAS HEX FILE Binary file according to the Intel HEX format R DAS firmware upgrades are available as HEX files from AED s web site MONITOR MODE Special R DAS mode The monitor mode is entered when R DAS receives commands via the serial port This mode is indicated by a single beep every three seconds In the monitor mode R DAS cannot be triggered In this way the data is secure during the downloading process and R DAS cannot be accidentally triggered Never launch a rocket when R DAS is in monitor mode as no triggering will take place To leave the monitor mode switch R DAS off and on or use reset SMART RECOVERY Term used for automatic deployment of parachutes An integrating accelerometer is used to detect apogee and the main parachute is release
21. citance max 15 pF 12 ADCS Analog input 5 13 14 GND Analog digital ground Note Open drain outputs can be directly connected to inputs 0 and IO1 because of the internal pull up of these input ports 4 5 J6 Reset classic only Shortening the two pins of J6 resets R DAS 4 6 J9and J11 Igniter terminals The igniter wires of the drogue and main parachute igniters are attached to J9 and J11 respectively Close to the terminals are continuity LED s which are switched on if there is a continuity problem large igniter resistance 47 J10 Serial port The serial port J10 is used to connect the R DAS to a PC to configure R DAS download the data or upgrade the R DAS application software Only use the supplied cable to connect R DAS to a PC 4 8 J12 Power connector compact only Power input connector for R DAS compact Connect power to switch unit on 17 4 9 J13 Safe arrm connector compact only The safe arm connector of the J13 allows to switch off the power supply to the igniters The following diagram shows the operation of the safe arm connector igniter output stage power supply J12 Figure 4 2 Safe Arm connector J13 The power supply fills the firing capacitor C through diode D and resistor R For normal operation J13 is closed see red line in Fig 4 2 this is the small jumper that is factory installed If an external safe arm device is desirable the jumper can be replaced by e g an exter
22. d at the specified altitude TRIGGERING Detection of liftoff by R DAS either by G switch or breakwire UPLOADING Sending of a new R DAS executable firmware to the R DAS circuit board from the PC R DAS Mailing List Join the R DAS mailing list to be informed about the latest developments new software release and participate in discussions with other R DAS users For subscription and the mailing list archive visit http rdas listbot com Table of Contents 1 INTRODUCTION csssscssssssssssssssssscssssssssssssssssssesnsessssesesesessssssesssnsssessssssessessnssessssssssnsesossesesessenssesesssssscsesesessssssessnsesoseess 6 1 1 HEATURES tessa cial case eee Io aa et ee ee eee 1 2 MAIN DIFFERENCES BETWEEN R DAS CLASSIC AND R DAS COMPACT 1 3 RDAS SPECIFICATIONS ia ernro ranee ana rara eiae E 1 4 RDAS FEEGTRIGAL LAY OUTS a a A St R DAS 2 111 9 2 1 RDAS MOUN TN Ge vas oth cou wah cs E a E E E e E E E 9 252 RDAS PROGRAM BE OW 10 2 2 1 Bootloader 2 2 2 Power up checks 2 2 3 Pre flight phase 2 2 4 Flight phase 2 3 USER COMMUNICATION I O 2 34 Serial Interface RS 232 232
23. d breakwire triggers the R DAS when contact is made It is possible to select both G switch or breakwire triggering Note that at least one type of triggering is required 3 1 2 Recovery settings The recovery settings determine the method to determine the drogue and main parachute igniter activation The timed recovery setting fires the igniters at the desired time after lift off The maximum time of the timers is 255 seconds the resolution is second Smart recovery uses an integrating accelerometer algorithm to determine apogee and activate the drogue parachute output The main parachute is deployed at a user selectable height above the initial launch altitude It is possible to select both methods e g to use the timing as back up for smart recovery 13 NOTE The interface software automatically rounds deployment altitude to resolution of R DAS This might be observed by change of the last digit of the entered value 3 1 3 Sampling settings The channels to be sampled are selected by the sampling settings Pressure and acceleration are always sampled and stored The channels ADC 0 to ADC 5 refer to the analog channels on the expansion port The digital input stores the value of the 4 digital inputs on the expansion port This information is stored as a single byte The remaining 4 bits of this byte are used to store the flight status i e before liftoff flight phase drogue parachute phase and main parachute phase This g
24. ected to R DAS these jumpers can be opened to reduce power consumption and increase the maximum expansion cable length The mounting of the board can be in all kind of directions If the R DAS accelerometer has to be complemented with the two other axes the board is mounted perpendicular to the R DAS board Of course it is also possible mount the ADXL250 board with one of the axis in the same direction as the R DAS accelerometer to improve the resolution of the measurements Note that for determination of apogee R DAS only uses its own onboard accelerometer The user can select any of the channels that need to be measured during flight from within the R DAS user interface program The x axis of acceleration is connected to ADCO the y axis to ADC1 the temperature measurement output to ADC2 For example if only the temperature needs to be registered during flight only check the ADC2 box Because the ADCO ADC1 and ADC2 signals are connected make sure that no signals from your own experiments are connected to any of these signals After flight the data can be viewed with the user interface program However no scaling is applied to the signal only volts are shown For further processing the R DAS plot program or e g a spreadsheet program can be used The R DAS plot program converts all the data automatically assuming zero g before lift off When a spreadsheet is used the measured ADC values need to be converted into temperature and ac
25. ector both were intended to be attached to a PC A null modem cable can be obtained from most computer suppliers It is also easy to solder your null modem Using two male DB 9 plugs connect the following pins Plug 1 Plug 2 DCD to not connected RxD pin 2 to pin 3 needed TxD pin 3 to pin 2 needed DTR pin4 to pin 6 optional GND pin5 to pin 5 needed DSR to pin 4 optional RTS 7 to pin8 optional CTS pin8 to pin7 optional RI pin9 to not connected 3 8 Palm user interface Rob Nee wrote a Palm user interface for the R DAS that can be downloaded from http www robnee com rdas For use of the R DAS with this interface also a null modem is needed See paragraph 3 7 for more detail 15 4 Connector description In this chapter each of the connectors of R DAS will be discussed The figure below shows the external connections of R DAS J10 serial port J4 breakwire J11 main parachute J2 main current J9 drogue parachute J9 drogue parachute J11 main parachute J12 power connector J1 drogue current Figure 4 1 Connector description of R DAS 41 J1 and J2 Igniter current selectors classic only The jumpers J1 and J2 determine the current through the igniters of the parachute pyro systems When open no jumper a regulated current of 1A flows through the igniters A regulated current prevents burn through of the igniter bridgewire without ignition of the surrounding pyrotechnic mixture When using ign
26. es the output stage A low TR1 signal activates the igniter output by opening FET Transistor and resistors R2 and R17 both 1 5Q act as current source and limit the igniter current to By shortening J1 the current source is bypassed and the igniter current is determined by the inline resistance The VOK signal is for safety reasons It is activated once the processor is running During power down it disables the output stage within 10 before the processor goes down app 10ms Also shown in Fig 5 2 is the power supply circuitry for the igniter stages If J3 is unconnected the igniter outputs are supplied from capacitor C4 When pins and 2 are shortened using a jumper the R DAS power supply is directly connected to the output stage of R DAS When an external ignition source is supplied between pins 2 and 3 the external battery directly powers the output stage without drainage from the R DAS power supply NOTE When using C4 for igniter power supply make sure that there is at least 5 seconds between activation of the two igniter outputs so there is enough time for recharging of C4 19 PMLL4148L D D2 1 PRLL4001 rie c4 IGNITER 2200UF Figure 5 2 Igniter output stage The output current to the igniters is determined by the setting of J1 and J2 igniter current selectors and J3 Ignition power select Using the current source ensures reliable
27. ft R DAS compact right R DAS classic Altitude is determined from static pressure measurements It is therefore necessary that the pressure transducer is able to measure the ambient pressure To make sure that R DAS measures the ambient pressure at least one vent hole should be made in the rocket casing The size of the venting area is determined by the payload volume Typically several holes of a few millimeters are enough These holes can be used as access to the on off switch of R DAS R DAS classic The most convenient way to switch R DAS on and off is to use a small screw driver through one of the vent holes For the R DAS classic the user has to supply its own on off switch or other alternative like twisting wires The user has the option to supply the R DAS by different power supplies Most simple option is to supply the R DAS by 9V battery placed in the battery holder on the backside of the R DAS R DAS classic only For small diameter rockets battery holder might be too large and battery be placed anywhere within the rocket with wires leading to R DAS The power supply is not limited to 9V batteries only Any power supply between 9 and 15 capable of delivering the required current suffices extremely important that there is a good mechanical contact between the 9V battery and the R DAS PCB For rockets with large acceleration loads it is advised to use backup wires soldered between the battery
28. ignition of the electric match preventing melting of the fine igniter wire without ignition of the surrounding pyrotechnic composition J1 and J2 open If C4 is selected as power source J3 open the ignition current descreases as soon as the charged voltage of C4 becomes too small app after 10 msec Using the R DAS battery or an external power supply holds the current constant as long as the outputs are activated 1 second Shortening J1 and or J2 bypasses the current source and the current is then limited by the total resistance of igniter and igniter output stage I A Maximum current external power Current source external power Current source power from C4 t msec 10 Figure 5 3 Igniter output current for several configurations The settings of R DAS and the output stages can be tested by attaching LED s to the igniter outputs A resistor of 470Q in series with the LED limits the currents through the LED s The LED s have to be connected with the right polarity When holding the R DAS in the flight directions the upper connections of J9 and J11 are positive 20 5 3 Hints and tips 5 3 1 Calibration of the acceleration transducer With a simple procedure it is possible to calibrate the acceleration transducer AMNPRWNE Configure R DAS to measure with a high sampling rate e g 200 Hz and inverting breakwire Use a jumper or other conducting material to trigger R DAS by shortening the brea
29. informs the user about the status Two LED s show the continuity of the attached igniters A third LED is used for status monitoring 2 3 1 Serial Interface RS 232 This connector attaches the R DAS to a PC with the supplied cable The RS 232 port is used for configuring R DAS downloading the measured flight data and upgrading the R DAS firmware 11 2 32 Close to processor loud piezo buzzer is placed This buzzer informs about status of the R DAS by varying the acoustic signal The table below describes the different cases Table 2 1 Summary of different acoustic signals BEEPS high frequency longbeep bootloader running at start up eoccccccccccce fast beeps continuous uploading firmware o o short beep every second R DAS standby ready for launch short beep every three seconds R DAS in monitor mode during download and configuration two short beeps R DAS detected lift off data acquisition busy BUZZES low frequency drogue igniter discontinuity error main igniter discontinuity error ooo three buzzes breakwire error breakwire triggering disabled four buzzes external hardware error hardware creer pressure transducer out of range at power up offset six buzzes accelerometer out of range at power up offset and or self check g switch disabled As of V2 2 of R DAS s n 004xx the volume and power
30. iters that require more than to set of shorten and J2 by placing jumpers The current flow is then determined by the resistance of the igniter and ignition circuit only For more details see section 5 2 4 2 3 Ignition power select classic only With terminal J3 the power source for the igniters is selected When J3 is not connected to an external power source or shortened by jumpers the ignition current is supplied from the large capacitor just above J3 This capacitor holds enough charge for a 1A current flow for at least 10ms This is more than enough for Davey Fire type igniters When using the capacitor the R DAS power supply eg 9V battery feels no peak loads as the capacitor is charged with a charging time of about 5 seconds When the igniter leads are shortened after firing the current is limited by the charging current of the capacitor Shortening pins and 2 of J3 by a jumper directly connects the power supply of R DAS to the igniter output stages This allows prolonged igniter current supply However if the power supply of R DAS cannot supply enough current there is the possibility that the computer circuit of R DAS resets When large ignition currents are needed it is suggested to use the third option of J3 i e an external power supply for the igniters This external power supply can be connected to pins 2 positive and 3 ground 16 maximum voltage of this external power supply is 15 Volt like R DAS
31. ives information about the igniter output stage activation time which is otherwise unknown in case of smart recovery TIP After retrieval of a stored data file rd the configuration settings show the settings used for that flight 3 2 Downloading data After the rocket flight the accumulated data is retrieved from the R DAS by downloading The download procedure is started by the download button or from the File Download pull down menu During the downloading procedure the number of seconds of retrieved flight data is shown on the screen The stop download button interrupts the downloading process The data is sent by the R DAS in 1 second blocks with a checksum If there is a checksum or connection error the interface software request the data again retry The number of retries is shown on the screen if there has been at least one retry The download procedure is stopped when there are more than 25 retries If this is the case check the cable connection 3 3 View and export data After downloading the data it can be viewed do not forget to save your important flights Each of the measured channels can be switched on or off by the view selectors above the graph of data The first view selector selects whether the flight phases are shown In this case each flight phase pre flight ascent pilot parachute and drogue parachute phase is marked by a vertical red line NOTE Flight phase information is only av
32. kwire pins Hold R DAS upright for a few seconds Hold R DAS upside down for a few seconds Download the data of this experiment Export the data as an ASCII file and determine the average value of the acceleration signal in both positions and use e g a spreadsheet program to determine the averages The difference between both positions is 2g The voltage of each ADC value is 5 1024 4 883mV so the sensor sensitivity is found from the following 5 4 883 ADC 2 mvV g up down accurate digital voltmeter and enter this value as the calibration value It is also possible to measure the output voltage of the sensors directly in both positions using an 5 3 2 Testing of the G switch The G switch can easily be tested by holding the R DAS upside down and then suddenly rotating it This is felt as a difference of 2g by the acceleration sensor and triggers R DAS liftoff an acceleration of 1g is sensed because of the gravity acting on the sample weight A total The acceleration transducer measures the force on a sample weight inside the sensor Before acceleration of 2 5 g means a difference of 1 5g compared to the calibration power up value As the acceleration calibration is continuously updated during the pre flight phase the unit must be rotated suddenly 5 3 3 Wiring harness It is advised to make a wiring harness in your rocket This wiring harness should contain safe arm co
33. n save print etc there are also specific menu s and buttons The download button starts the collection of measurement data from the R DAS The cursor selectors allow to change between zoom and drag mode In drag mode the graph can be dragged within the program window by holding the left mouse button In the zoom mode a rectangular window can be drawn by pressing the left mouse button After releasing this area is zoomed in Pressing control while selecting an area zooms out The view selectors above the graph determine which signal is plotted Left of the graph are buttons which manipulate the graph View selectors Cursor selectors Download 218 Zoom buttons Figure 3 1 R DAS User interface 31 Configuring R DAS R DAS can be configured by selecting Configure RDAS from the Configure menu Select the COM port to which R DAS is connected The current settings can be retrieved from R DAS by the Get Config button The R DAS is programmed with the selected settings by the Store Config button 3 1 1 Trigger settings The trigger settings determine the trigger i e start of acquisition of R DAS Selecting G switch triggers R DAS when an acceleration of 2 5 g is sensed for more than 0 25 seconds It is also possible to trigger R DAS by making or breaking a contact This is called breakwire triggering Normal breakwire triggering triggers the R DAS when a contact is broken Inverte
34. nal switch that is connected to jumper block J13 Note that power is only supplied to the igniters when J13 is closed The dotted blue line indicates another way of operation An external wire can be connected from the power supply connector block J12 to J13 in case the capacity of the firing capacitor C is not enough to fire the ematch Also other alternatives are possible E g by connecting a second power source to the lower pin of 113 and to the ground of J12 it is possible to connect a second power supply Figure 4 3 shows the wiring in case of an external safe arm switch and separate power supply remote safe arm supply switch 9V supply igniter supply Figure 4 3 Wiring of safe arm connector J13 for an external safe arm switch left or external igniter power supply right In both cases remove the factory installed jumper Of course it is also possible to combine a remote safe arm switch with an external power supply 18 5 Technical information 5 1 Mechanical outline of R DAS The figure below shows the mechanical outline of R DAS including component space Left R DAS without 9V battery holder right R DAS with 9V battery holder component space is hatched Figure 5 1 Mechanical outline of R DAS classic sizes in millimeters 5 2 Igniter output stages classic only The figure below shows one of the igniter output stages of R DAS The TR1 signal comes from the microprocessor of R DAS and activat
35. niter output drogue is activated when a zero acceleration integral is reached If timed recovery is configured the drogue output is activated when the desired time is reached In case of both smart recovery and timed recovery both conditions are checked fore and if one of them is met the drogue output is activated The main parachute output is activated when the configured time is reached in case of timed recovery or when measurements show that the altitude is below the configured altitude for main parachute deployment for more than 0 25 sec in case of smart recovery Again when both smart recovery and timed recovery are activated the system monitors for any of the two events When the memory is full the R DAS unit stops data acquisition After the main parachute is deployed the maximum obtained altitude is calculated and reported by beeping The altitude is reported in feet There are up to five digits in the number First a buzz is generated followed by the altitude Because a zero cannot be beeped it is reported as a long beep For example 1023 feet is reported as buzz beep beeeeeep beep beep beep beep beep pause buzz etc 23 User communication I O There are several ways in which the R DAS unit communicates with the outside world For configuring R DAS downloading the measured flight data and upgrading the R DAS firmware R DAS is equipped with a standard RS 232 serial port A buzzer
36. nnectors for the igniter outputs Especially when using pyrotechnic recovery devices such as pyrotechnic bolts a good safe arm plug is essential for safe operation of the rocket igniter outputs always bear in mind that pyrotechnic devices can be set off when R DAS is xa Although R DAS s electronic circuits have been designed to prevent accidental activation of the switched on and operating Safe operation of R DAS is only possible in combination with safe arm devices which inhibit the pyrotechnic devices e g by shortening the ignition wires or proper use of J13 5 3 4 Testing igniter outputs The following procedure allows testing of the functionality of the igniter output 1 2 3 FR e Connect ematches to R DAS igniter outputs 19 and 1 or use small bulbs Switch on R DAS Configure R DAS for timed recovery only no smart recovery Set recovery times to e g 5 and 10 seconds Switch off R DAS Hold R DAS unit upside down Switch on R DAS Wait till the bootloader is finished and the normal application is running single beep every second Suddenly rotate R DAS in the flight direction UP arrow pointing upwards to trigger the g switch In case of a good lift off two continuous beeps are heard otherwise restart from 4 After 5 and 10 seconds the outputs fire the ematches Re configure R DAS according to your wishes e g smart recovery only 21 6 Software
37. overy integrating accelerometer barometric main parachute and or timed recovery barometric altitude for main chute release extra data acquisition channels sampling rate etc e Huge amount of data storage e g when ambient pressure and acceleration are sampled 200 times per second the measurement time is more than 8 minutes At lower sampling rates the sampling time is proportionally longer e Pre flight data the large RAM memory of R DAS is continuously updated with the last 2 seconds of pre flight data After lift off the unit starts storing the data in EEPROM starting with the last 2 seconds before lift off In this way also pre flight data is available e g for offset calibration or drift verification Extra analog inputs 6 analog input channels are available through 14 pin boxed header for your own experiments This connector also provides your experimental board with electric power 4 digital inputs read and store the status from a digital indicator e Program code can easy be upgraded by the user simply download future versions of the program code from the web and upgrade your R DAS system with the latest firmware in seconds e Multiple rocket flights Separate EEPROM s with boot code are available This makes it possible to fly several rockets with the same R DAS without the need to download the data immediately after each flight Of course each EEPROM may contain a different configuration R DAS classic only
38. ownloaded and saved to the hard disk there is no real need to save old flights in the memory except e g for flights that were done the same day The user has to configure R DAS for GPS via the user interface Logging will always take place but there will not be a power up test to see if the GPS board is present nor will the transmitter if present send the 29 position Each time when logging session entrance is made an internal EEPROM table on GPS board There are 32 entrances in this table When the table if full there is a wrap around From the table the PC user interface software knows exactly where to start reading in the FLASH memory of the GPS unit to obtain a certain flight When the FLASH memory is cleared also the EEPROM table is cleared To make life easy the table is presented by the user interface along with the time and date of the particular flight This allows easy selection of old flights When the R DAS with GPS unit attached is switched on the red LED of the GPS unit will be on for five seconds Then the GPS will unit will try to obtain a position fix As soon as a position fix has been obtained the LED is switched on again The R DAS will beep out a 3 tone tune to indicate that a position fix was obtained At this time the logging starts and an entrance is made in the EEPROM table Usually it takes about one minute to obtain a position fix from a cold start During that period no logging takes place This
39. s also possible to mount the circuit board in small slots External power Future expansion port Output 2 R DAS expansion port Current 2 Pull up jumpers Output 1 Current 1 Address jumpers Figure 7 1 R DAS igniter board with the most important components The whole output stage is very similar to that of R DAS It is therefore advised also to consult the Chapters 4 and 5 of this manual The output connector terminals are easily recognized Next to these terminals are two jumpers By shortening these jumpers the current source of 1A is bypassed and the maximum current is controlled by the total circuit resistance gt 5 A in a 1Q load Each output has its own continuity check If there is no continuity between the terminal outputs the red LED is on Two green LED s show the current output status one for each output This simplifies testing of a programmed configuration In the normal operation the expansion board uses the large capacitor as a power source It is also possible to supply the board with an external power supply This external supply can be attached to the two 1 3 mm PCB pins shown in Fig 7 1 25 If this is first expansion board attached to R DAS shorten pull up jumpers with a small amount of solder Only in one of the expansion boards e g the first attached to R DAS these two jumpers should be closed The other two jumpers set the address of the output board Each board attached to R DAS should ha
40. ssssnsnsevsssesssssnnsesessssesesnsesssesssesnsenseseres 29 9 1 PEATURESS 9 2 SPECIFICATION tes eee ee 9 3 OIEI rD N LO N ETAETA EE BEEE EES EET EE EAEE E EAE E E E AE 1 Introduction The rocket data acquisition system R DAS is used for measuring and storing analog and digital data gathered during rocket flight Furthermore it can be used to set off your drogue and main parachute charges There are two different versions of the R DAS The R DAS classic hardware version V2 x and the R DAS compact hardware version V3 x The R DAS system is built on a small double sided printed circuit board classic 125 x 48 mm 4 92 x 1 89 inch compact 90 x 36 mn 3 54 x 1 42 inch This is small enough to fit in almost any high power or amateur rocket The R DAS compact was designed to fit ina 38 mm rocket This chapter summarizes the features and specifications of R DAS New users should at least read the Chapters 1 2 and 3 of this manual More details for advanced use are found in Chapters 4 and 5 A history of the changes of the R DAS main program and user interface software is found in Chapter 6 Expansion options for R DAS are discussed in Chapter 7 and following 11 Features The R DAS has the following features Easy to configure Configure the R DAS system with easy to use free downloadable Windows software G switch and or breaking launch detection smart rec
41. ta storage then catches up with the measurements 10 2 24 Flight phase The flight phase is entered triggering of R DAS when liftoff is detected Triggering of R DAS can be accomplished by the breakwire or by a g switch A valid g switch trigger occurs when the accelerometer measures an acceleration of more than 2 5 g for 0 25s If one of the measurements shows a lower value than 2 5 g the 0 25 second timer is reset again This prevents accidental triggering in case of a shock Holding the unit upside down and then rotate it suddenly allows testing of the g switch triggering If the R DAS is slowly rotated there is no valid liftoff detection because of the continuous calibration of the accelerometer Note be careful when handling a rocket with R DAS switched on Suddenly rotating it or tripping the breakwire will start R DAS followed by activation of the parachute outputs After liftoff detection the R DAS starts erasing the FLASH memory This is not done before the liftoff detection so the user can download old data until a new liftoff is detected During the first three seconds of the flight phase there is a dead time and none of the igniter outputs can be activated The flight phase can be distinguished from other phases by the double buzzer beeps During the flight the accelerometer signal is integrated A zero acceleration integral defines the apogee of the flight trajectory If smart recovery is configured the first parachute ig
42. ted range the user is warned by the buzzer 5 short buzzes After sensor testing the system checks the breakwire If breakwire triggering was selected the R DAS unit checks if a breakwire is present If no breakwire is present the breakwire triggering is disabled This prevents accidental triggering of the unit by e g a loose breakwire The user is warned by the buzzer 4 short buzzes In case of inverted breakwire the R DAS expects an open breakwire connection at power up If this is not the case the triggering is disabled as well and the user informed by the buzzer 2 2 3 Pre flight phase After the initial checks the R DAS unit comes in the pre flight phase During this phase the accelerometer and pressure transducer are continuously calibrated R DAS samples all configured measurement channels The measurement data is stored in a circular buffer see figure 2 2 In this way two seconds of pre flight data is always in the memory When the flight phase is entered the R DAS stops overwriting in the circular buffer and starts storing the data in the FLASH memory During the pre flight phase the R DAS buzzer beeps every second measurements circular buffer data storage t 2 t 0 t flash erased t 0 25 launch detection Figure 2 2 Circular memory buffer of R DAS Measurements are continuously taking place at the set sample frequency Data storage begins when the flash has been erased and starts at t 2 seconds The da
43. to 32 own FLASH memory loss of R DAS memory capacity e audible signal for GPS lock for ease of use in the field prepared for telemetry unit when available high gain active antenna e to use via familiar R DAS windows interface 9 2 Specification The specifications of the GPS board are summarized in table 9 1 Table 9 1 R DAS GPS expansion board specifications GPS unit Manufacturer Type GPS MS1E Max update rate 1 Accuracy CEP 5 Acquisition cold start typical 60 Operational limits Altitude lt 60000ft and velocity lt 1000knots Either limit may be exceeded but not both COCOM restrictions Antenna Manufacturer Macom Model no 135 active antenna Gain 30 Antenna power supply 5 Connector SMA Power supply Voltage 9 to 15 from R DAS Current 200 Physical Dimensions 48 x 48 1 89 x 1 89 mn inch Weight gee Pos gram oz Temperature range 0 to 70 C 9 3 Operation The GPS unit has its own internal nonvolatile FLASH memory In this memory the rocket s trajectory is stored together with some information about the quality of the solution to obtain the position and the velocity The FLASH memory is sufficiently large to contain several flights The user has to make sure that there is enough memory available for a new flight So it is recommended to regularly clear the FLASH memory of the GPS unit via the PC user interface software As logged flight paths can be d
44. ve a different address Table 7 2 shows the relation between the jumper settings and the output stage numbers as configured in the R DAS user interface software Table 7 2 R DAS igniter expansion board jumper settings closed closed Expansion board 1 Expansion board 4 26 8 2 accelerometer and temperature expansion board option This Chapter describes the optional 2 axis accelerometer and temperature expansion board shortly ADXL250 board 81 Features Features of the ADXL250 board e 2 1 acceleration measurement e Selectable range from 50 25 10 g and 5 g Each axis can have a different range Temperature measurement e EEPROM for future expansions 8 2 Specification The specifications of the ADXL250 board are determined by the two transducers that are used For the acceleration an Analog Devices ADXL250JQC accelerometer is used The temperature is registered by an Analog Devices AD22100AR temperature transducer The accelerometer is centered at the top of the printed circuit board The temperature transducer is mounted on the bottom of the board Table 8 1 R DAS accelerometer expansion board specifications Accelerometer Type ADXL250JQC Number of axis 2 Range 5 10 25 50 Sensitivity 380 211 67 9 38 0 Resolution respectively 0 01 0 02 0 05 0 1 Uncalibrated accuracy 20 Connected to ADCI1 Temperature transducer Type AD22100AR Range 40 85
45. y upgrading the firmware First download a recent version of the rdas hex file from AED s web page Then select Upload executable from the Configure menu and follow the instructions on the screen Within a few seconds the R DAS software is upgraded After upgrading an automatic reset of R DAS is carried out note the beep of the bootloader 14 3 5 Calibration The calibration values of the pressure sensor and accelerometer can be modified using Configure Calibration values dialog This window also defines the acceleration before liftoff usually 1 g from the earth s acceleration 3 6 Scale settings Following the Configure Scale settings allows to change the scale settings of the plot In this dialog the altitude before liftoff can also be set If the launch altitude is different from sea level this option can be used to determine the actual altitude obtained rather than the absolute value of the altitude which is measured with the pressure transducer 37 Windows CE user interface The R DAS user interface is also available for the Windows CE platform This version has the same features as the Windows interface although some of the dialogues have a different layout R DAS is connected to the CE device via its docking station or a separate serial cable available for most devices An additional null modem is needed to connect the CE cable to that of R DAS because both devices have a female conn
46. zes buzz drogue parachute igniter problem 2 buzzes main parachute igniter problem Improved calibration at power up Pre flight acceleration is now running average of measured values before liftoff Improved acceleration integral resolution Limitation before variable overflow maximum motor burn time is 500 seconds Added GPS functionality Added telemetry functionality 6 2 User interface 6 2 1 V2 1 First public release of R DAS user interface Specifically designed to work with R DAS V2 1 hardware and firmware 6 2 2 V2 2 Support for igniter expansion board added 22 6 2 3 2 2 1 6 2 4 V2 2 2 6 2 5 V3 0 6 2 6 V3 1 After configuration change or software upgrade the user interface now bypasses the bootloader for quicker boot process Clip function added to reduce data file size or select specific measurement channels New download protocol with improved error checking used for firmware V2 2 and up Export image thicker lines in high resolution images More grid lines in display Export data now possible as raw data or export of interpreted data Scale settings moved to the view menu On CE devices firs fast drawing of graph after this more accurate update of the graph Removed minimum altitude for main parachute deployment When low altitudes are selected the user is warned with a dialog window Removed bug when retrieving configuration and storing the configuration In this case one
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