1. Colorado Space Grant Consortium Virginia Space Grant Consortium 1 RockOn... A Sounding Rocket Payload Workshop Colorado & Virginia Space Grant Consortium Mission Initiation Conference February 21, 2008 2:00 PM EST RockOn... A Sounding Rocket Payload Workshop Colorado & Virginia Space Grant Consortium Mission Initiation Conference February 21, 2008 2:00 PM EST

2. Colorado Space Grant Consortium Virginia Space Grant Consortium 2 Presentation Overview 1.Workshop Concept 2.Introduction and Background 3.Workshop Kit Concept 4. Concept of Operations 5.Stacked Kit Configuration 6.RocketSat Can Configuration 7.Can to Launch Vehicle Integration 8. Testing 9.Special Requests 10.Summary of Final Configuration

3. Colorado Space Grant Consortium Virginia Space Grant Consortium 3 1. Workshop Concept: - Faculty and students come to Wallops for a six day hands-on workshop - In teams of 3-4, they build a sounding rocket payload (RocketSat) from a kit - All payloads are identical - Payloads integrated into a standard container and integrated on 4 th day - Payloads are launched on a single rocket on the 6 th day - Workshop is held annually - Past participants come back to fly their own payloads in standard container for a set price (some may fly on future workshop rockets to help pay cost of workshop launch)

4. Colorado Space Grant Consortium Virginia Space Grant Consortium 4 1. Workshop Concept: - RockOn workshop is based on the successful Boulder BalloonSat workshop

5. Colorado Space Grant Consortium Virginia Space Grant Consortium 5 1. Workshop Concept: - This workshop has been held five times with great participation

6. Colorado Space Grant Consortium Virginia Space Grant Consortium 6 1. Workshop Concept: - We are expecting similar participation with the RockOn workshop - The website can be found at…http://spacegrant.colorado.edu/rockon/

7. Colorado Space Grant Consortium Virginia Space Grant Consortium 7 2. Introduction and Background: RocketSat and Workshop Goals: 1.) Allow students to design payloads that will go into space 2.) More challenging design problem 3.) Unique science opportunities 4.) More demanding hands-on experience 5.) Interdisciplinary team work 6.) Help create a new and standard access to space platform with Wallops

8. Colorado Space Grant Consortium Virginia Space Grant Consortium 8 2. Introduction and Background: - The workshop kit or RocketSat has been under development and testing since January 2006. - RocketSat has been develped by undergraduate students from the University of Colorado at Boulder - RocketSat has flown three times in different configurations - RocketSat I September 2006 - RocketSat IIApril 2007 - RocketSat IIIJune 2007

9. Colorado Space Grant Consortium Virginia Space Grant Consortium 9 RocketSat 1 Objectives: 1.) Easily reproducible payload design (COTS) 2.) Qualitative data description of flight environment with altitude 3.) Science Package: - Geiger Counter - Microwave Detector - Sensor Package - Temperature sensor - Accelerometers - Pressure sensor 2. Introduction and Background:

10. Colorado Space Grant Consortium Virginia Space Grant Consortium 10 RocketSat 2 Objectives: 1.) Easily reproducible payload design (COTS) 2.) Record detailed flight data: - Video Camera 3.) General environmental sensors: - Temperature - Pressure - Humidity 4.) Structural Loading Data: - Three-axis accelerometer recordings - Strain gauges - Faculty Sponsored GPS experiment 2. Introduction and Background:

11. Colorado Space Grant Consortium Virginia Space Grant Consortium 11 RocketSat 3 Objectives: 1.) Re-fly all hardware from RSI except microwave sensor and Geiger counter 2.) New Sensors: - Silicon pressure sensor - New Geiger counter - New microwave sensor 2. Introduction and Background:

12. Colorado Space Grant Consortium Virginia Space Grant Consortium 12 3. Workshop Kit: - No Rocket power needed - No Telemetry needed

13. Colorado Space Grant Consortium Virginia Space Grant Consortium 13 3. Workshop Kit: AVR Geiger Counter G-Switch 9 Volt Batteries Z axis Accels.

14. Colorado Space Grant Consortium Virginia Space Grant Consortium 14 3. Workshop Kit: - Plate material is similar to Lexan - CG of populated plate is + 0.0679 X -0.0195 Y - 0.0176 Z - Weight of populated plate is ~1.75 to 2.00 pounds - Notches for electrical

15. Colorado Space Grant Consortium Virginia Space Grant Consortium 15 Functional Block Diagram AVR Temp. Sensor Geiger Counter Pressure Sensor X and Y Acc. Z Accel. Data Retrieval Board (not flight) Flash Memory 9V In Parallel VREGS AVR Output G-Switch Wallops Activation Flash Input Flash Output Legend Power Data AVR Input 3. Workshop Kit:

16. Colorado Space Grant Consortium Virginia Space Grant Consortium 16 AVR Board – Revision 3: - ATMega 32L Microprocessor - 2 MB Flash Memory - 0-15 Psi Pressure Sensor - 3-Axis Acceleration - Temperature Sensor - In-System-Programming - Attached Geiger Counter - 9 Volt Bus - RBF pin on each kit - G-switch on each kit Data Retrieval (not flight) Z-Axis Acceleration Main Board G-Switch 3. Workshop Kit:

17. Colorado Space Grant Consortium Virginia Space Grant Consortium 17 Geiger Counter – Revision 3: - Addition of Audio Segment to compliment blinking LED - New Aerosol Urethane based conformal coating (1500V/mil dielectric spec) to prevent coronal discharge - Digital Output TTL pulse for AVR interface and recording - Epoxy application to Geiger tube to prevent depressurization blowout of mica window Geiger Board 3. Workshop Kit:

18. Colorado Space Grant Consortium Virginia Space Grant Consortium 18 T-15 minutes – Arming Relay Activated G-switch and AVR deactivated T-0 – Liftoff G-switch and AVR activated Z-axis accelerometers show a large vertical acceleration System begins collecting data T+1 second – Z-axis accelerations cause memory protection latches to engage X- and Y-axis accelerometers show constant values due to spin T+~3 minutes – Rocket reaches apogee Z-axis accelerometers read 0 g due to free fall conditions T+15 minutes – Rocket lands Sensors continue to collect data until flash memory is full Later – Retrieval Payloads retrieved AVR continues to operate in low power mode until battery power is exhausted If power returns, data is not overwritten due to memory protection system 4. Concept of Operations:

19. Colorado Space Grant Consortium Virginia Space Grant Consortium 19 Single Plate w/ Stand-Offs 2 nd Plate Clocked and Stacked On Top of 1 st 5. Stacked Configuration:

20. Colorado Space Grant Consortium Virginia Space Grant Consortium 20 Stand-Offs Added 3 rd Plate Clocked and Stacked On Top of 2 nd 5. Stacked Configuration:

21. Colorado Space Grant Consortium Virginia Space Grant Consortium 21 Stand-Offs Added 4 th Plate Clocked and Stacked On Top of 3 rd 5. Stacked Configuration:

22. Colorado Space Grant Consortium Virginia Space Grant Consortium 22 Stand-Offs Added 5 th Plate Clocked and Stacked On Top of 4 th 5. Stacked Configuration:

23. Colorado Space Grant Consortium Virginia Space Grant Consortium 23 Stand-Offs Added Stacked Configuration ~10 pounds 5. Stacked Configuration:

24. Colorado Space Grant Consortium Virginia Space Grant Consortium 24 5 Plate Stack Attached to Can Bottom Bulkhead 6. RocketSat Can Configuration:

25. Colorado Space Grant Consortium Virginia Space Grant Consortium 25 Split Barrel Section Added and attached to Bottom Bulkhead (8 Places) 6. RocketSat Can Configuration:

26. Colorado Space Grant Consortium Virginia Space Grant Consortium 26 5 Plate Stack Stand-offs attached to Top Lid. Barrel Section attached to Top Lid (8 Places) Assembled can with payload ~20 pounds 6. RocketSat Can Configuration:

27. Colorado Space Grant Consortium Virginia Space Grant Consortium 27 Bottom Bulkhead 6. RocketSat Can Configuration:

28. Colorado Space Grant Consortium Virginia Space Grant Consortium 28 Barrel Section 6. RocketSat Can Configuration:

29. Colorado Space Grant Consortium Virginia Space Grant Consortium 29 Top Lid 6. RocketSat Can Configuration: Colorado Space Grant Consortium Virginia Space Grant Consortium

30. Colorado Space Grant Consortium Virginia Space Grant Consortium 30 7. Can Integration to Launch Vehicle: Use of standard can will simplify integration 3 longerons and 5 Sub- SEM Rings Can #1 integrated and bolted to Sub- SEM Ring Colorado Space Grant Consortium Virginia Space Grant Consortium

31. Colorado Space Grant Consortium Virginia Space Grant Consortium 31 7. Can Integration to Launch Vehicle: Use of standard can will simplify integration Can #2 integrated and bolted to Sub- SEM Ring Electrical Connections to Latching Relays run down side of Cans and through inner diameter of Sub-SEM Ring Colorado Space Grant Consortium Virginia Space Grant Consortium

32. Colorado Space Grant Consortium Virginia Space Grant Consortium 32 7. Can Integration to Launch Vehicle: Use of standard can will simplify integration Can #3 integrated and bolted to Sub- SEM Ring Electrical Connections to Latching Relays run down side of Cans and through inner diameter of Sub-SEM Ring Colorado Space Grant Consortium Virginia Space Grant Consortium Can #3 has camera payload (See Section #9)

33. Colorado Space Grant Consortium Virginia Space Grant Consortium 33 7. Can Integration to Launch Vehicle: Use of standard can will simplify integration Can #4 integrated and bolted to Sub- SEM Ring Electrical Connections to Latching Relays run down side of Cans and through inner diameter of Sub-SEM Ring Colorado Space Grant Consortium Virginia Space Grant Consortium

34. Colorado Space Grant Consortium Virginia Space Grant Consortium 34 7. Can Integration to Launch Vehicle: Use of standard can will simplify integration Can #5 integrated and bolted to Sub- SEM Ring Electrical Connections to Latching Relays run down side of Cans and through inner diameter of Sub-SEM Ring Colorado Space Grant Consortium Virginia Space Grant Consortium Can #5 has different payload to test standard concept for next year’s workshop (See Section #9)

35. Colorado Space Grant Consortium Virginia Space Grant Consortium 35 7. Can Integration to Launch Vehicle: 4 th Longeron is added after all electrical connections have been made Colorado Space Grant Consortium Virginia Space Grant Consortium ~1.0” – 2.0” between top of can and Sub-SEM ring

36. Colorado Space Grant Consortium Virginia Space Grant Consortium 36 7. Can Integration to Launch Vehicle: Rocket skin is attached. Estimated Rocket skin length is ~66 inches. This does not include area for latching relays or other Wallops equipment. Colorado Space Grant Consortium Virginia Space Grant Consortium View port needed here. (See Section 9) Static and Dynamic port needed here. (See Section 9)

37. Colorado Space Grant Consortium Virginia Space Grant Consortium 37 Boulder: 3d Modeling in Solidworks Yields Preliminary Center of Gravity Functional Tests by System During Integration Testing of Completed Payload: Mission Simulation Moments Around 2 Orthogonal Axes - CG Correlation of Measured CG to Simulated 8. Testing:

38. Colorado Space Grant Consortium Virginia Space Grant Consortium 38 Wallops Space Center: Spin – Measure CG, Moment of Inertia (Single Disc) Vibration – Single Payload Disc on Vibration Table Bending – 5-Payload Can in Simulated Rocket Body This testing will occur with students during the week of March 24 – 27, 2008 at Wallops 8. Testing:

39. Colorado Space Grant Consortium Virginia Space Grant Consortium 39 9. Special Requests: Request #1 Substitute 2 Workshop experiment decks in one can and replace it with a camera deck to record flight for participants Can CG will be same as other can but this requires a view port

40. Colorado Space Grant Consortium Virginia Space Grant Consortium 40 9. Special Requests: Request #2 One of the goals of the workshop is to help develop a standard package to launch future sounding rocket payloads This concept is part of the sustainability for future workshops at Wallops Each future workshop would fly 1 – 3 paying customers (previous workshop participants) payloads in a RocketSat Can Would like to demonstrate this concept on the first flight with the 5 th Can This is payload is called RocketSat IV and is a CU undergraduate student payload being developed since September 2007

41. Colorado Space Grant Consortium Virginia Space Grant Consortium 41 9. Special Requests: Request #2 RocketSat IV has the following Mission Statement RocketSat IV will expand the knowledge of the composition of the upper atmosphere by measuring the concentrations of carbon dioxide and methane above 30km. - RocketSat IV would have a balanced CG and require no power or telemetry. - RocketSat IV would have the same weight as a normal Workshop Can (10 lbs) - RocketSat IV would be contained in the same Can system being used during the workshop - RocketSat IV would require a dynamic and static pressure port to sample atmosphere from apogee until a unspecified time before parachute deployment

42. Colorado Space Grant Consortium Virginia Space Grant Consortium 42 9. Special Requests: Request #2 - RocketSat IV consists of stainless steel tubing

43. Colorado Space Grant Consortium Virginia Space Grant Consortium 43 9. Special Requests: Request #2 - The tubing is vacated at apogee - As pressure increases, air is forced into the tube, compresses, and remains in the order that it was sampled - Sample is analyzed using laser analyzer after the flight Air

44. Colorado Space Grant Consortium Virginia Space Grant Consortium 44 9. Special Requests: Request #2 - Two sections of tubing will be used to collect separate samples from different durations of the flight. - One tubing will collect atmosphere from apogee to 30km where it will be sealed - The second tubing will collect atmosphere from apogee to just before the parachute deploys. Dynamic pressure port - Sample the low density air more effectively, we need to have dynamic pressure force air into the tubing. Static pressure port - For sampling purposes, we need a static pressure port to measure ambient pressure to identify the altitude.

45. Colorado Space Grant Consortium Virginia Space Grant Consortium 45 9. Special Requests: Request #2

46. Colorado Space Grant Consortium Virginia Space Grant Consortium 46 10. Summary of Final Configuration - Internal Configuration

47. Colorado Space Grant Consortium Virginia Space Grant Consortium 47 10. Summary of Final Configuration - Integrated Can Configuration Cans 1, 2, and 4

48. Colorado Space Grant Consortium Virginia Space Grant Consortium 48 10. Summary of Final Configuration - Integrated Can Configuration Can 3

49. Colorado Space Grant Consortium Virginia Space Grant Consortium 49 10. Summary of Final Configuration - Integrated Can Configuration Can 5

50. Colorado Space Grant Consortium Virginia Space Grant Consortium 50 10. Summary of Final Configuration - Launch Vehicle Integration

51. Colorado Space Grant Consortium Virginia Space Grant Consortium 51 10. Summary of Final Configuration - Skin with two access areas for: 1 View port 1 Static port 1 Dynamic port Total payload weight with cans ~100 pounds Payload section ~66 inches long Launch scheduled for June 27, 2008