General solution for the optimal trajectory of an AFE-type spacecraftThe Aeroassisted Flight Experiment (AFE) involves the Space Shuttle-based launch and subsequent recovery of an experimental spacecraft, simulating a transfer from GEO to LEO. One such AFE transfer is presently considered under assumed conditions of identical orbital planes, circular initial and final orbits, and given initial phase angle in conjunction with a free final phase angle. The aeroassisted trajectory involves preatmospheric, GEO-to-entry, postatmospheric, and exit-to-LEO phases; the optimal trajectory is obtained by minimizing the total characteristic velocity.
Document ID
19920032130
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Miele, A. (Rice Univ. Houston, TX, United States)
Wang, T. (Rice University Houston, TX, United States)