Minimizing the Effects of Impulsive Orbit Maneuver Uncertainty
Publication: Journal of Aerospace Engineering
Volume 31, Issue 5
Abstract
The terminal state error under impulse orbit maneuver uncertainty is minimized using the linear covariance method. A new actuation-error model is proposed for practical engineering application, which requires that the thrust direction be aligned with the impulse vector. The polar angle in the error model can be adjusted to reduce the terminal error. This paper studies two impulse-maneuver problems, including short-range orbit rendezvous and translunar midcourse correction. First the state transition matrices for the two problems are provided. Then the control error matrix is derived under impulse-magnitude and impulse-direction errors. The terminal linear covariance matrix is obtained by considering both navigation and actuation errors. Finally, the optimal polar angle is numerically solved by the golden-section search. Numerical examples are provided to verify the proposed method for the analytical linear covariance matrix and the optimal polar angle.
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Acknowledgments
This work is supported in part by the National Natural Scientific Foundation of China (Grant No. 11772104) and the Postdoctoral Scientific Research Developmental Found of Heilongjiang Province (Grant No. LBHQ16078).
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Published In
Journal of Aerospace Engineering
Volume 31 • Issue 5 • September 2018
Copyright
©2018 American Society of Civil Engineers.
History
Received: Nov 29, 2017
Accepted: Mar 7, 2018
Published online: Jun 5, 2018
Published in print: Sep 1, 2018
Discussion open until: Nov 5, 2018
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