Fully reusable launch vehicle concepts being studied for post-Shuttle era transports present major challenges for the structural design of large propellant tankage. The dominant structural elements are internal tankage for both cryogenic and non-cryogenic propellants which must operate in a broad range of thermal environments while meeting requirements for low weight and reusability. Several approaches to integral tank design are discussed and an analysis of a hot structure honeycomb sandwich tank for a circular body vehicle is presented.
Structural design of integral tankage for advanced space transportation systems
In: Structures, Structural Dynamics and Materials Conference ; 1982 ; New Orleans, LA
1982-01-01
Miscellaneous
No indication
English
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