Physics
Scientific paper
Dec 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992stin...9313379b&link_type=abstract
Unknown
Physics
Aerobraking, Optimization, Orbit Transfer Vehicles, Spacecraft Design, Structural Analysis, Structural Weight, Weight Reduction, Design Analysis, Finite Element Method, Honeycomb Structures, Shapes, Thickness Ratio
Scientific paper
An aerobrake structural concept for a lunar transfer vehicle was weight optimized through the use of the Taguchi design method, finite element analyses, and element sizing routines. Six design parameters were chosen to represent the aerobrake structural configuration. The design parameters included honeycomb core thickness, diameter-depth ratio, shape, material, number of concentric ring frames, and number of radial frames. Each parameter was assigned three levels. The aerobrake structural configuration with the minimum weight was 44 percent less than the average weight of all the remaining satisfactory experimental configurations. In addition, the results of this study have served to bolster the advocacy of the Taguchi method for aerospace vehicle design. Both reduced analysis time and an optimized design demonstrated the applicability of the Taguchi method to aerospace vehicle design.
Bush Lance B.
Rehder John J.
Rowell Lawrence F.
Unal Resit
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