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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. Mission Overview. 3. 4. 5. 2. 1. 6. Mission Overview.
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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
Mission Overview 3 4 5 2 1 6
Mission Overview • 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.
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.
Scientific Objectives • Characterize the performance of electrically active methods of reentry. • Proposed methods of reentry: • Magnetic Shield • Plasma Shield
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.
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.
Engineering Objectives • Develop standardized probe and deployment system. • Develop alternative sample return methods. • Develop a reliable and reusable standard electronic system.
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.
Concept of Operations Rocket skins are shed, probes are deployed.. 3 4 T = 2.8 min. Radio blackout. Probes activate and sample temperature data during reentry. 5 2 Probe chutes are deployed. Radio signal is reacquired and data is transmitted back to Wallops and backed up on the base station. Probes starts up and begins transmitting. T = 4.5 min. T = 1.3 min. 1 6 T = 5.5 min. T = 0 min. T = 15 min. Circuits initialize and begin collecting and transmitting data. Power and telemetry is shut down and data collection and transmission ceases. Splashdown.
Design Specifications- Mechanical • PES • Secure probes during accent. • Eject probes safely and reliably. • Protect supporting systems during reentry. • AHSS • Shield sensitive systems from heat during reentry • Slow reentry for reacquisition of signal. • Land system safely for potential recovery via hydrostatic orbit. • GRS • Shield sensitive systems from heat during reentry • Provide a mechanism to transport space samples inland.
Design Specifications- Electrical • PES • Deploy probes safely. • Receive telemetry from probes. • AHSS • Generate buffer zone. • Record temperature data. • Transmit data back to PES. • Deploy recovery system. • GRS • Record temperature data. • Transmits data back to PES. • Deploy recovery system. • Guide payload to land.
