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Analysis and sizing of Mars aerobrake structureA cone-sphere aeroshell structure for aerobraking into Martian atmosphere is studied. Using this structural configuration, a space frame load-bearing structure is proposed. To generate this structure efficiently and to perform a variety of studies of several configurations, a mesh generator that utilizes only a few configurational parameters is developed. A finite element analysis program that analyzes space frame structures was developed. A sizing algorithm that arrives at a minimum mass configuration was developed and integrated into the finite element analysis program. A typical 135-ft-diam aerobrake configuration was analyzed and sized. The minimum mass obtained in this study using high modulus graphite/epoxy composite material members is compared with the masses obtained from two other aerobrake structures using lightweight erectable tetrahedral truss and part-spherical truss configurations. Excellent agreement for the minimum mass was obtained with the three different aerobrake structures. Also, the minimum mass using the present structure was obtained when the supports were not at the base but at about 75 percent of the base diameter.
Document ID
19930048294
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Raju, I. S.
(Analytical Services and Materials, Inc. Hampton, VA, United States)
Craft, W. J.
(North Carolina Agricultural and Technical State Univ. Greensboro, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 30
Issue: 1
ISSN: 0022-4650
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
93A32291
Funding Number(s)
CONTRACT_GRANT: NAGW-1331
Distribution Limits
Public
Copyright
Other

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