Optimal Formation Trajectory-Planning Using Parameter Optimization Technique

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Some methods have been presented to get optimal formation trajectories in the step of configuration or reconfiguration, which subject to constraints of collision avoidance and final configuration. In this study, a method for optimal formation trajectory-planning is introduced in view of fuel/time minimization using parameter optimization technique which has not been applied to optimal trajectory-planning for satellite formation flying. New constraints of nonlinear equality are derived for final configuration and constraints of nonlinear inequality are used for collision avoidance. The final configuration constraints are that three or more satellites should be placed in an equilateral polygon of the circular horizontal plane orbit. Several examples are given to get optimal trajectories based on the parameter optimization problem which subjects to constraints of collision avoidance and final configuration. They show that the introduced method for trajectory-planning is well suited to trajectory design problems of formation flying missions.
Publisher
한국우주과학회
Issue Date
2004-08
Keywords

trajectory-planning; formation flying; collision avoidance; parameter optimization

Citation

Journal of Astronomy and Space Sciences, Vol.21, No.3, pp.209-220

ISSN
1225-052X
URI
http://hdl.handle.net/10203/21905
Appears in Collection
AE-Journal Papers(저널논문)
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