A simple control-guidance law for low-thrust coplanar orbital transfer maneuvers is investigated. The law is based on classical control theory, and is intended to circumvent the two-point boundary value problem difficulties encountered in the optimal control approach as applied to orbit maneuvering. The proposed guidance law is fairly insensitive to uncertainties in control parameters such as thrust level, thrust direction, and the initial time of the maneuver. The performance index is based on a trade-off between time and fuel expenditure, for missions in which the maneuver must be performed in one single phase because of operational time constraints. Constant or variable thrusts are admitted.
Novel Control-Guidance Law for Low-Thrust Orbit Maneuver
1990
8 pages
Report
No indication
English
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