Preliminary structural design of a lunar transfer vehicle aerobrake

Details Preliminary structural design of a lunar transfer vehicle aerobrake Preliminary structural design of a lunar transfer vehicle aerobrake

Feb 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992aiaa.confq....b&link_type=abstract

AIAA, Aerospace Design Conference, Irvine, CA, Feb. 3-6, 1992. 13 p.

Other

Aerobraking, Lunar Spacecraft, Orbit Transfer Vehicles, Structural Design, Finite Element Method, Lunar Module, Lunar Orbits, Spacecraft Configurations, Thermal Protection

Scientific paper

An aerobrake for a lunar transfer vehicle was designed through the use of the Taguchi design method, structural finite element analyses, and structural sizing routines. A minimum weight aerobrake structural configuration was the objective of the study. Six design parameters were chosen to represent the aerobrake structural configuration. The design parameters included honeycomb core thickness, diameter-to-depth ratio, shape, material, number of concentric ring frames and number of radial frames. Each parameter had 3 levels. The optimum aerobrake configuration resulting from the study was approximately half the weight of the average of all the other experimental configurations. The parameters having the most significant impact on the aerobrake structural weight were identified.

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