DYNAMIC ANALYSIS AND PRELIMINARY DESIGN FOR SATELLITE GUIDANCE SUBSYSTEM
MARTIN CO BALTIMORE MD
Pagination or Media Count:
A self-contained guidance and control system for a hypothetical, unmanned one-year mission in space is presented. System operation is based on the use of altitude measurements to define the in-plane orbit parameters and preselected star occultation time measurements to define the orbit plane orientation parameters. Over-all system operation is presented and system errors are evaluated, using an IBM 7090 computer program. A detailed description of each of the subsystems is given and the reliability of these systems is predicted for the one-year mission, using component failure rate data. It is shown that the system could be instrumented using state-of-the-art hardware. A preliminary missions analysis indicates that the system would have considerable utility in manned satellite missions requiring exit from orbit and rendezvous with earth-based target points.
- Celestial Mechanics
- Unmanned Spacecraft