Approach to collision avoidance optimal maneuvers with perturbation analysis

Paper number

IAC-06-B6.P.2.05

Author

Mr. Chen Lei, National University of Defense Technology, China

Coauthor

Dr. Han Lei, National University of Defense Technology, China

Coauthor

Dr. Ma Zhihao, National University of Defense Technology, China

Year

2006

Abstract

The need for collision avoidance maneuvers is increasing as the number of satellites and debris increases. Some methods have been developed to solve the problem, such as Russell P. Patera’s method based on Collision Probability Methodology (2003). But the collision trend has not been discussed seriously in these methods, and it may lead to another collision possibly in a short period of time because of perturbation effects. The relative motion between active satellite and collision object is discussed in the paper, the method with perturbation analysis is presented to avoid the second collision after collision avoidance maneuver.
The relative motion of satellite and object is composed of three periodic motion, such as short-periodic motion caused by spherical curse, long-periodic motion caused by circular motion, and long-long-periodic motion caused by perturbation. Thus it is important to design collision avoidance maneuver with perturbation analysis.  
The authors presented an analytic method of collision detection in IAC-04-IAA [1].5.12.P.02, which is based on SGP4/SDP4 models. It is different from Hoots (1984) in considering secular effects, which can be applied in maneuver design. In that paper we found that collision must happen in the two points of intersection between two orbits, and the trend of intersection points is determined by  the perturbation. The approach to optimal maneuver is based on the trend.
The Jacobbi matrix between the trend and the impulse of active satellite is computed with semi-analytic method, and the sensitivity is analyzed between active satellite and any object which may be collided possibly. The optimal maneuver is obtained with the help of sensitivity integration. The method is proved by numerical simulation.

Abstract document

IAC-06-B6.P.2.05.pdf

Manuscript document

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