1. University of Wyoming Michael Stephens, Eric Robinson, Alex Antonacci, Andrew Hellquist, Joe Backstrom, Bryan Overcast, Jeffrey Watters, Jonathan Melton, Marshall Moore, Matthew Lehmitz, Tal Wammen October 5, 2011 1

2. Mission Overview 2 1 2 3 4 5 6

3.  To design and build a standardized probe deployment system to test advanced reentry concepts including guided reentry and electrically active heat shielding.  These concepts as well as a standardized delivery mechanism will provide a foundation to build future experiments. 3

4. Systems Overview  Probe Ejection System (PES) “PEZ”  Ejects probes and supports their flight with telemetry.  Advanced Heat Shield System (AHSS) “OZ”  Uses electrically active systems to reduce heat during reentry.  Guided Reentry System (GRS)  Attempts to maneuver the probe to an environment that makes recovery easier and more cost effective. 4

5. Scientific Objectives o Characterize the performance of electrically active methods of reentry. o Proposed methods of reentry: o Magnetic Shield o Plasma Shield 5

6. Purpose of Reentry Methods  Create a lighter weight heat shield system than current passive methods.  Create a high performance heat shield that reduces heat more than passive methods.  Establish a re-useable heat shielding system.  Reduce cost.  Simplify aerodynamic design requirements.  Establish robust and reliable heat shield system. 6

7. Details of Potential Reentry Methods  Magnetic Shield: Utilize magnetic system to increase the buffer zone between the surface of the payload and the plasma generated during reentry.  Plasma System: Establish a continuous shockwave ahead of the payload that will cause the plasma generated during reentry to divert around the payload also increasing the buffer zone. 7

8. Engineering Objectives o Develop standardized probe and deployment system. o Develop alternative sample return methods. o Develop a reliable and reusable standard electronic system. 8

9. Success Criteria  Reduce heat on reentry of a probe.  Confirm results with control probe.  Successfully recover control probe.  Create a standardized probe deployment platform enabling future progression in the field. 9

10. Concept of Operations 10 1 2 3 4 5 6 Circuits initialize and begin collecting and transmitting data. Probes starts up and begins transmitting. Rocket skins are shed, probes are deployed.. Power and telemetry is shut down and data collection and transmission ceases. Splashdown. Probe chutes are deployed. Radio signal is reacquired and data is transmitted back to Wallops and backed up on the base station. Radio blackout. Probes activate and sample temperature data during reentry. T = 0 min. T = 1.3 min. T = 2.8 min. T = 4.5 min. T = 5.5 min. T = 15 min.

11. Design Overview 11

12. RockSat X 2012 Mechanical Concept 12

13. Design Specifications- Mechanical o PES o Secure probes during accent. o Eject probes safely and reliably. o Protect supporting systems during reentry. o AHSS o Shield sensitive systems from heat during reentry o Slow reentry for reacquisition of signal. o Land system safely for potential recovery via hydrostatic orbit. o GRS o Shield sensitive systems from heat during reentry o Provide a mechanism to transport space samples inland. 13

14. Design Specifications- Electrical o PES o Deploy probes safely. o Receive telemetry from probes. o AHSS o Generate buffer zone. o Record temperature data. o Transmit data back to PES. o Deploy recovery system. o GRS o Record temperature data. o Transmits data back to PES. o Deploy recovery system. o Guide payload to land. 14

15. AstroX Team 15

16. Management 16

17. Questions? 17