1. Critical Design Review Team SkyHawk Fort Lewis College Christopher Hardrick, Peter Samuelson, Travis Lange June 24, 2010 1

2. Mission Overview  Primary Objectives  Collect atmospheric radiation levels  This collection will help us learn about the quantity of radiation in varying layers of atmosphere  Perform visible and ultraviolet spectrum analysis of the atmosphere  From the collection of UV data we plan to analyze the amount of ozone present above eastern Colorado 2

3. Theory Behind Objectives Radiation The atmosphere does a great job at scattering radioactive particles that enter from the sun, celestial bodies and space in general. With the increase in altitude, there is less atmosphere to scatter this radiation and is why we expect to see a more dense concentration in radioactive particles. Ozone Ozone in the atmosphere are particulates that absorb harmful UV rays from the sun, most strongly absorbing UV-B and UV-C. In the wavelength spectrum this equates to 100 to 320 nanometers. 3

4. Mission Requirements 4 RequirementMethodStatus The battery must supply a minimum of 10 Watts for 3 hours. Design, Analysis, Test Camera software must be capable of operating two cameras. Design, Test The ITX must be accessed remotely.Design, Test Sensors must be exposed to atmosphere.Design ITX must be able to run Windows XP.Analysis, Test The USB DAQ must be able to process and deliver data from the sensors to the ITX for storage. Design, Analysis, Test Memory usage must not exceed 16 GB.Test, Analysis

5. Mission Requirements 5 RequirementMethodStatus The spacecraft must not exceed a weight of 1.5 kg.Design, Test Structurally integrated center tube for flight string.Design, Test The spacecraft’s center of gravity (CG) shall be within 0.25” of the geometric central axis of the ICU. Design, Analysis All parts of the payload must remain attached to the flight string during flight. Design The spacecraft’s CG shall not lie more than 12” above the satellite interface plane (SIP). Design, Analysis The payload must survive environmental stresses at 100,000 feet. Design, Analysis The payload must survive an accelerative load up to 15 g’s. Design, Test

6. Operation Prior to Launch (On Site) Assure full battery charge and connect in payload Activate power switch Close Payload Remote access ITX Begin script file Script file activates camera software Initiates both cameras Initiates terminal for Geiger Counter data acquisition Activates USB DAQ DAQ begins to take in data from sensors and sends data to file saved to flash drive Attach to flight string 6

7. Operation Post Launch (On Site) Open payload hatch Turn power switch to off Post Launch (Off Site) Prepare battery for storage Analyze data from USB flash memory Get ready for LA!! 7

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9. 9 Pressure Sensor Battery XYZ Accelerometer Geiger Counter DAQ Ports for Photodiodes and Thermisters USB hub PSU Wi-Fi Port For Flash Memory Cameras ITX

10. Structural Overview Structure 3K 2x2 Twill Weave Black Carbon Fabric Bubble aluminum sheeted insulation Flight String 160 PSI plastic tubing Inner Diameter: 8 mm Successfully used in previous launches 10

11. Structural Drawings 11

12. Structural Drawings 12

13. Structural Drawings 13

14. Subsystems Overview Power System has a cut off voltage of 11.5 V Battery supplies all power to PSU PSU supplies correct power to ITX, 13.5 V to pressure sensor and 5 V to accelerometer (all else is 5 V USB supplied) Data Acquisition (DAQ) USB DAQ collects voltages from 8 channels of sensors DAQ streams data to ITX to save on flash memory Channel 0: Pressure Sensor Channel 1: Accelerometer X Channel 2: Accelerometer Y Channel 3: Accelerometer Z Channel 4: Photodiode (VIS) Channel 5: Photodiode (UV) Channel 6: External Temperature Channel 7: Internal Temperature 14

15. Subsystems Overview Thermal Insulation maintains temperature above -10 degrees C with heat generation from ITX radiative cooling fins Battery must remain above 10 degrees C to supply power Video Capture Software maintains two cameras Video capture is alternated between two cameras Frame rate memory usage cannot exceed 10 GB of flash memory capacity Memory 16 GB Flash drive memory 15

16. Subsystems Design Drivers Thermal Power Memory 16

17. Parts List PartCompanyStatus BatteryThunder Power RCJust Arrived 280 nm Optical FilterEdmunds OpticsJust Arrived USB DAQMeasurement ComputingJust Arrived Pressure SensorICSensorsAcquired XYZ AccelerometerAnalog DevicesAcquired Pico ITXEPIAAcquired Web CamMicrosoftAcquired PSUEPIAAcquired USB Wi-FiNfinitiAcquired Geiger CounterSparkfunAcquired Carbon FiberInfinity CompositesAcquired Compact Flash (OS)TranscendAcquired Flash DriveUnknownAcquired 17

18. Parts List PartCompanyStatus UV PhotodiodeOrdered VIS PhotodiodeOrdered 18

19. Special Requirements / Requests Would prefer to be at the top of the payload flight string in order to capture balloon burst How non-aerodynamic does a payload need to be to designate the top position? 19

20. Management 20

21. Management 21

22. Management Current concentration on finishing all ITX interfacing and structure molding Moving concentration towards sensors 22

23. Management - Mass ItemPredicted MassActual Mass Battery325 ITX (Board Only)137 PSU74 Flash (OS)40 Flash (storage)8 Wi-Fi4 USB Connections89 Geiger Counter51 Pressure Sensor (Entire Circuit)17 Accelerometer (Entire Circuit)11 Two Cameras35 UV Filter2 UV Photodiode15 VIS Photodiode15 USB DAQ45 Thermisters1 Switches & Wires25 Predicted Total Total55839894 Structureg/sq.in.sq. in.Predicted MassActual Mass Carbon Fiber1.1250.5275.55 Flight String Tube10 Insulation0.19250.547.71428571 Total333.2642857 Grand Total Mass 1227.26 Grams 23

24. Management - Budget PartCost Battery$90 USB DAQ$150 Geiger Counter$165 Carbon Fiber Supplies$95 USB Hub x2$20 UV Filter$120 Molding Foam$30 Misc.$100 Photodiodes$50 24 Current Total$820

25. Test Plans Planned Testing Endurance Test Battery testing Run entire payload for a minimum of 2.5 hours Drop Test Already tested Carbon layers Payload will be dropped from 21 foot balcony on to concrete patio Whip test 30 foot drop while attached to actual flight string sample Cold Test Run entire payload for a minimum of 2.5 hours at -20 C environment Then at -40 C environment Then at -80 C environment Vacuum Test Run payload, excluding structure, while in vacuum 25

26. Test Plans Testing procedures All our tests have been written out, for example: Tests are written for each individual component in the payload as well as the five main tests present on the previous slide Testing is scheduled for July 8 th through the 16 th, result analysis and repair is scheduled for July 17 th through the 28 th 26 Test Subject Step ID NumberProcedureExpected ResultsActual Results Pass/Fail/Par tialComments ITX Boards1Get the ITX Boards and all the componentsFind all of themFound all of themPassComponets: Power, USB, and VGA cables, compact flash and reader, and a monitor 2Hook the USB cables to oneof the ITX BoardsHook up fineHooked upPass 3Put the compact flash reader on a ITX BoardHook up fineHooked upPass 4ATurn on one ITX BoardTurns onDoesn't workFailTurns on sometimes but then shuts down 4BTurn on the other ITX BoardTurns onTurned onPassShort the fifth and sixth pin Cameras1Get the camerasFind all of themFound all of themPass 2Make sure the wires are still connectedConnected Pass 3Plug the cameras into the USB ports 4Find cameras on the ITX BoardFind all of themFound all of themPassNeeded to get drivers from Microsoft website

27. Conclusions Our Concerns At the present moment we are unsure if the ITX and USB hub can power all of the usb devices If not we are prepared to power each USB device externally We have little experience writing script files Typical Web Cams do not span a spectrum that dips deep in to UV Our back up plan if the web cam cannot “see” through the 280 nm filter is to use a standard UVenus filter to capture the upper bounds of UV and use the narrow band filter over the UV Photodiode to better pin point the spectrum band we are interested in. So far operations are moving smoothly and roughly on schedule. 27

28. Questions or Suggestions? 28