Fuel Slosh Energy Dissipation on a Spinning Body
HUGHES AIRCRAFT CO EL SEGUNDO CA SPACEAND COMMUNICATIONS GROUP
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The purpose of the report is to serve as an interim documentation of the fuel slosh investigation program to date. Additional testing at inertia ratios near 0.6 and 1.1 is presently scheduled for early 1972. This testing together with the testing already completed, is intended to establish an empirical energy dissipation equation that will permit scaling test and flight data for arbitrary roll-to-pitch ratios. Such scaling is critical for determining spacecraft stability margins for vehicle configurations inertially dissimilar to the Intelsat IV and HS-318 designs.
- Liquid Rocket Propellants
- Unmanned Spacecraft