Topex orbit sustenance maneuver design
Abstract
A trade-off analysis between maneuver period, execution errors, and orbit determination uncertainties is carried out for the Ocean Topography Experiment spacecraft for a given nodal equatorial constraint. Semimajor axis and eccentricity are controlled with minimum impulse using the linear theory of optimal transfer between close coplanar near-circular orbits. Ellipses of equal minimum and average maneuver periods are presented in the (3 execution error, 3 orbit determination uncertainty) space for different nodal equatorial constraints enabling the determination of the appropriate combination of execution errors and orbit determination uncertainties that guarantees a mission required minimum maneuver period for a given nodal deadband.
- Publication:
-
AIAA, Aerospace Sciences Meeting
- Pub Date:
- January 1982
- Bibcode:
- 1982aiaa.meetQQ...K
- Keywords:
-
- Orbital Maneuvers;
- Satellite Observation;
- Stationkeeping;
- Topex;
- Trajectory Optimization;
- Circular Orbits;
- Equators;
- Ocean Dynamics;
- Tradeoffs;
- Transfer Orbits;
- Water Circulation;
- Astrodynamics