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Contemporary Impact Analysis Methodology for Planetary Sample Return MissionsDevelopment of an Earth entry vehicle and the methodology created to evaluate the vehicle's impact landing response when returning to Earth is reported. NASA's future Mars Sample Return Mission requires a robust vehicle to return Martian samples back to Earth for analysis. The Earth entry vehicle is a proposed solution to this Mars mission requirement. During Earth reentry, the vehicle slows within the atmosphere and then impacts the ground at its terminal velocity. To protect the Martian samples, a spherical energy absorber called an impact sphere is under development. The impact sphere is composed of hybrid composite and crushable foam elements that endure large plastic deformations during impact and cause a highly nonlinear vehicle response. The developed analysis methodology captures a range of complex structural interactions and much of the failure physics that occurs during impact. Numerical models were created and benchmarked against experimental tests conducted at NASA Langley Research Center. The postimpact structural damage assessment showed close correlation between simulation predictions and experimental results. Acceleration, velocity, displacement, damage modes, and failure mechanisms were all effectively captured. These investigations demonstrate that the Earth entry vehicle has great potential in facilitating future sample return missions.
Document ID
20160010614
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Perino, Scott V.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Bayandor, Javid
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Samareh, Jamshid A.
(NASA Langley Research Center Hampton, VA, United States)
Armand, Sasan C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 29, 2016
Publication Date
June 4, 2015
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 52
Issue: 4
e-ISSN: 1533-6794
Subject Category
Astrodynamics
Report/Patent Number
NF1676L-18648
Funding Number(s)
WBS: WBS 346620.04.07.01.01.02
Distribution Limits
Public
Copyright
Other

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