1. Louisiana State University (LSU) NSF PACER Program Physics & Aerospace Catalyst Experiences A. M. Espinal Mena, V.Gónzalez Nadal, J. Díaz Valerio Faculty Advisor: Dr. H. Vo Aerospace Balloon Imaging Testing with Accelerometer (ABITA) Experiments The Interamerican Geospace Research Experiments (TIGRE) Team Preliminary Design Review (PDR) 6/30/2008

2. Outline  Goals, Objectives & Requirements  Payload Design  Payload Development Plan  Payload Construction Plan  Project Management  Master Schedule  Risk Management and Contingency

3. Mission To determine balloon dynamics. Reference: BEXUS 5 Experiment (Altitude Sensing and Determination System)

4. Balloon Flight ACES-08

5. Scientific Objectives  Obtain images of the surrounding environment  Create a model of the balloon movements  Determine rotational & translational movement

6. Technical Objectives  Develop a payload less or equal to 500 g  Have a maximum cost of $ 500  Collect data for about 4 hours balloon flight

7. Science Background Reference: Lyndon State College, Department of Meteorology

8. Scientific Requirements  Record the flight time of payload  Observe the surrounding environment of the balloon  Record outside temperature  Obtain the vector acceleration of the balloon payload  Know the rate of tilt change and its relationship with the acceleration

9. Technical Requirements  Require to have a real time clock on board  Include video camera capable of recording 4 hours  Include a three axis accelerometer to record vibration/shock  Compare data at high rates  Record tilt of payload

10. System Design

11. Electrical Design

13. ADXL330 Three Axis Accelerometer

14. 32480 Digital Video Camera

15. Digital Video Camera

16. 1N4001 Diode Temperature Sensor

17. Control Electronics

18. Power Supply

19. Power Budget ComponentCurrent (mA) BalloonSat~56 3 Buffers~3 (1 each) Three axis accelerometer (ADXL330) ~0.32 Temperature Sensor (Diode)~1 Voltage to Frequency Converter ~ 5 (1.67 each) Total Current~64.32

20. Power Budget  Estimated Requirement : 257.28 mA-hour  The 9V battery will supply: 750 mA-hou r at -20 C  Note: The camera has its on power supply & also its own memory

21. Mechanical Design

22. General Design The “Giammanco” Model? Foam core construction. Component placement and its importance. Mechanical design and construction.

23. External Structure Front, Cross Section and Bottom View of Model Multi-View Enclosure Model

24. Internal Structure Multi-View Internal Model Front, Cross Section and Hidden Lines View of Model

25. New Design Advantages: Components are placed in modular spaces. Physically smaller than original design. Structurally stronger. Ease of access to components.

26. Redesigned Enclosure The above picture depicts the payloads enclosure, insert and lid. Multi-View of External Design

27. Redesigned Enclosure Multi-View of Assembled Model Picture above depicts assembled enclosure, open and sectioned views.

28. So why a new design?

29. New Design Disadvantages: Still in the drawing board. Design might be heavier than original. Complexity of construction.

30. Assembly and Disassembly

31. Weight budget Component:Weight: BalloonSat Board67g Video Camera42.3g Accelerometer~19g Temperature Sensor~2g Conditioning Circuitry~30g Camera Power Supply48.6g Electronics Power Supply46.6g Payload Enclosure~150g Cables and Connectors~40g Total:~447.5g

32. Payload Development Phases are required to build our payload: Electronics design. Software design and testing. Mechanical design and construction. Assembly, testing and modification to the payload.

33. Payload Fabrication The order of fabrication is as follows: Ordering of components needed. Component prototyping and functionality assurance. Mounting components onto PCBs. Construction of payload enclosure. Testing and certifying that all components work together.

34. Software Design

35. Software Requirements Control Instruments - Time Stamp - Temperature Sensor - Accelerometer - Digital Camera Calibrate Data Analyze Data Interpret Data

36. Data Format and Storage EEPROM will have to store 13 bytes per minute for 4 hours from the 4 * 60 minutes = 240 minutes 13 bytes * 240 minutes = 3, 120 bytes for the whole flight

37. Data Format and Storage ByteDescription 1Time Stamp: hour 2Time Stamp: minute 3Time Stamp: second 4Temperature 5Accelerometer: X axis Max 6Accelerometer: X axis Min 7Accelerometer: X axis Average 8Accelerometer: Y axis Max 9Accelerometer: Y axis Min 10Accelerometer: Y axis Average 11Accelerometer: Z axis Max 12Accelerometer: Z axis Min 13Accelerometer: Z axis Average

38. Software: Pre- Flight

39. Software: During Flight Main loop: After every minute

40. Software: During Flight The accelerometer Loop: If one minute has not passed

41. Software: Post- Flight

42. Data Analysis Plan Level 0: Raw Data - Data downloaded to BASIC STAMP and saved using Term 232 Level 1: Calibrated Data - Convert digital values into physical quantity Level 2: Analysis -Data interpreted using Graphing Analysis -Frame grabber to analyze video image -Accelerometer’s frequency using Spectrogram

43. Work Breakdown Schedule

44. Risk Management & Contingency

45. Management Plan Team TIGRE member roles: -Ana M. Espinal Mena: Electronics design. -Jonathan Diaz Valerio: Mechanical design & fabrication. - Victoria Gonzalez Nadal: Software Design and implementation. Team TIGRE webpage: www.pjarea.com/wiki