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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

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Mission Overview

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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.

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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.

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Scientific Objectives

oCharacterize the performance of electrically active methods of reentry.

oProposed methods of reentry: oMagnetic ShieldoPlasma Shield

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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.

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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.

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Engineering Objectives

o Develop standardized probe and deployment system.

o Develop alternative sample return methods.

o Develop a reliable and reusable standard electronic system.

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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.

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Concept of Operations

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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.

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Design Overview

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RockSat X 2012 Mechanical Concept

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Design Specifications- Mechanical

oPESo Secure probes during accent.o Eject probes safely and reliably.o Protect supporting systems during reentry.

oAHSSo Shield sensitive systems from heat during reentryo Slow reentry for reacquisition of signal.o Land system safely for potential recovery via hydrostatic orbit.

oGRSo Shield sensitive systems from heat during reentryo Provide a mechanism to transport space samples inland.

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Design Specifications- Electrical

oPES

o Deploy probes safely.o Receive telemetry from probes.

oAHSS

o Generate buffer zone.o Record temperature data.o Transmit data back to PES.o Deploy recovery system.

oGRS

o Record temperature data.o Transmits data back to PES.o Deploy recovery system.o Guide payload to land.

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AstroX Team

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Management

Astro-X TeamAstro-X Team

Shawn CarrolRockSat-X Project

Manager

Lia MatthewsRockSat-X Project

Manager

Dr. Paul JohnsonFaculty Advisor

(Open)Team Leader

Michael StephensStudent Advisor

Eric RobinsonStudent Advisor

Alex AntonacciMechanical Engineering

Bryan OvercastMechanical Engineering

Marshall MooreElectrical

Engineering

Andrew HellquistMechanical Engineering

Jeffrey WattersMechanical Engineering

Matthew LehmitzMath and Science

Joe BackstromPhysics

Jonathan MeltonMechanical Engineering

Tal WammenCivil Engineering

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Questions?