Effects of transient propellant dynamics on deployment of large liquid stages in zero-gravity with application to Shuttle/CentaurThis paper describes the application of a recently developed CFD program, HYDR-3D, to the analysis of separation of the Centaur G-Prime vehicle from the Shuttle Orbiter. The typical application presented illustrates a particularly difficult design task - deployment of a large, liquid-filled, densely packaged vehicle from a manned vehicle. Since it represents a potential catastrophic hazard, a vast number of conditions and parameters must be analyzed to ensure tolerance of at least two credible failures. Validation of the HYDR-3D program against zero- and low-gravity experimental data is also presented. Using the fluid dynamics program, this approach can be used confidently to analyze and determine design requirements for a variety of OTV/space-station deployment and docking problems.
Document ID
19870028606
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Martin, R. E. (General Dynamics Corp. Space Systems Div., San Diego, CA, United States)