Design and performance analysis of a conical-aerobrake, orbital-transfer vehicle conceptA Shuttle-compatible systems design based on the core concept of attachable modules for the major vehicle components is proposed. The principal features include a disposable cargo/extra-propellant tank module; a porous, radiative, backscattering drag-brake surface material of thin silica cloth; and a lightweight carbon-composite support structure. The mission payload capability for delivery, retrieval, and combined operations is determined for a broad range of missions including NASA/DOD requirements and extending through cis-lunar space. The effects of finite-rate surface catalysis, negative lift, and multiple atmospheric passes in reducing the aerothermal heating rates are also investigated. In addition, the structural and thermal-protection problems of the drag-brake support apparatus are analyzed and recommendations are proposed for future design refinements.
Document ID
19840036466
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Menees, G. P. (NASA Ames Research Center Moffett Field, CA, United States)
Park, C. (NASA Ames Research Center Moffett Field, CA, United States)
Wilson, J. F. (Informatics General Corp. Palo Alto, CA, United States)