Avoiding collisions with resident space objects
Abstract
The minimum velocity impulse maneuver that can be employed by a satellite at a specific time to allow 'safe' passage with all other known satellites for a specific time in the future is determined. A technique employed for defining the maneuver is based on the linearization of the problem about the nominal 'nonmaneuvered' orbit; it uses partial derivatives relating position and velocity at the locations of the closest approach to the proposed maneuver-velocity impulse. It is shown that this approach is efficient in terms of computer resources since it employs a linearized representation and recursive formulas to reduce the computation time required at each point investigated in the 'velocity' space. The Program Design Language representation of a simple scheme for examining the 'velocity' space is presented, and a test case is discussed.
- Publication:
-
Astrodynamics 1989
- Pub Date:
- 1990
- Bibcode:
- 1990asdy.conf..417S
- Keywords:
-
- Collision Avoidance;
- Satellite Perturbation;
- Space Debris;
- Safety Factors;
- Spacecraft Maneuvers;
- Astrodynamics