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Structures and Mechanisms Design Concepts for Adaptive Deployable Entry Placement TechnologySystem studies have shown that large deployable aerodynamic decelerators such as the Adaptive Deployable Entry and Placement Technology (ADEPT) concept can revolutionize future robotic and human exploration missions involving atmospheric entry, descent and landing by significantly reducing the maximum heating rate, total heat load, and deceleration loads experienced by the spacecraft during entry [1-3]. ADEPT and the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) [4] share the approach of stowing the entry system in the shroud of the launch vehicle and deploying it to a much larger diameter prior to entry. The ADEPT concept provides a low ballistic coefficient for planetary entry by employing an umbrella-like deployable structure consisting of ribs, struts and a fabric cover that form an aerodynamic decelerator capable of undergoing hypersonic flight. The ADEPT "skin" is a 3-D woven carbon cloth that serves as a thermal protection system (TPS) and as a structural surface that transfers aerodynamic forces to the underlying ribs [5]. This paper focuses on design activities associated with integrating ADEPT components (cloth, ribs, struts and mechanisms) into a system that can function across all configurations and environments of a typical mission concept: stowed during launch, in-space deployment, entry, descent, parachute deployment and separation from the landing payload. The baseline structures and mechanisms were selected via trade studies conducted during the summer and fall of 2012. They are now being incorporated into the design of a ground test article (GTA) that will be fabricated in 2013. It will be used to evaluate retention of the stowed configuration in a launch environment, mechanism operation for release, deployment and locking, and static strength of the deployed decelerator. Of particular interest are the carbon cloth interfaces, underlying hot structure, (Advanced Carbon- Carbon ribs) and other structural components (nose cap, struts, and main body) designed to withstand the pressure and extremely high heating experienced during planetary entry.
Document ID
20120018068
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Yount, Bryan C. (NASA Ames Research Center Moffett Field, CA, United States)
Arnold, James O. (NASA Ames Research Center Moffett Field, CA, United States)
Gage, Peter J. (Neerim Corp. Mountain View, CA, United States)
Mockelman, Jeffrey (Rensselaer Polytechnic Inst. Troy, NY, United States)
Venkatapathy, Ethiraj (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 25, 2013
Publication Date
September 5, 2012
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
ARC-E-DAA-TN5853
Meeting Information
Meeting: 22nd AIAA Aerodynamic Decelerator Systems Technology Conference
Location: Daytona Beach, FL
Country: United States
Start Date: March 25, 2013
End Date: March 28, 2013
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNA12AA89C
CONTRACT_GRANT: NNX09AG76A
Distribution Limits
Public
Copyright
Public Use Permitted.

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