The objective of drift counteraction optimal control is to maximize the time that a given system satisfies prescribed constraints. This paper describes novel open-loop and receding horizon/model predictive control-based approaches to solve this problem. To illustrate the potential for drift counteraction optimal control applications to spacecraft operational life extension, two examples of geostationary satellite station keeping near the end of satellite operational life and spacecraft attitude control considering the effects of reaction wheel failures and reaction wheel speed saturation are presented. For the satellite station-keeping problem, the objective is to counteract drift imposed by orbital perturbations and maximize the time before prescribed position constraints are violated, given fuel limitations. For the attitude control problem, the spacecraft is subject to disturbances from solar radiation pressure; and tight pointing constraints need to be satisfied for as long as possible using reaction wheels. The cases of underactuated spacecraft (one or two reaction wheels) and fully actuated spacecraft are treated.

Spacecraft drift counteraction optimal control: Open-loop and receding horizon solutions

Bemporad A.
2018

Abstract

The objective of drift counteraction optimal control is to maximize the time that a given system satisfies prescribed constraints. This paper describes novel open-loop and receding horizon/model predictive control-based approaches to solve this problem. To illustrate the potential for drift counteraction optimal control applications to spacecraft operational life extension, two examples of geostationary satellite station keeping near the end of satellite operational life and spacecraft attitude control considering the effects of reaction wheel failures and reaction wheel speed saturation are presented. For the satellite station-keeping problem, the objective is to counteract drift imposed by orbital perturbations and maximize the time before prescribed position constraints are violated, given fuel limitations. For the attitude control problem, the spacecraft is subject to disturbances from solar radiation pressure; and tight pointing constraints need to be satisfied for as long as possible using reaction wheels. The cases of underactuated spacecraft (one or two reaction wheels) and fully actuated spacecraft are treated.
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/20.500.11771/20193
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