New Set of Attitude Parameters Dedicated to Relative Attitude Maneuvers
Publication: Journal of Aerospace Engineering
Volume 33, Issue 4
Abstract
A new set of attitude parameters that minimize the eigenangle between a body-fixed frame and a target reference frame was developed for application to rapid attitude maneuver of a spacecraft. The target reference frame is defined by using the pointing vector from the spacecraft to the target. Attitude kinematics based on the new set of attitude parameters is subsequently derived. To accomplish fast attitude maneuver, a cascade-saturation controller is then designed based on the proposed attitude parameters. The constraints of slew rate and control torque are considered in the proposed cascade-saturation controller. The stability of the resulting closed-loop system is proved by the Lyapunov theory. Simulation results verify that the proposed parameters are well-suited for spacecraft rapid target acquisition and tracking control.
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Data Availability Statement
Some data that support the findings of this study are available from the corresponding author upon reasonable request. The data aforementioned refers to the data corresponding to all simulation results, which contain quaternion, MRTPs, angular velocity, relative eigenangle, eigenaxis relative to target frame, command torque and eigenangle error.
Acknowledgments
Funded under the National Natural Science Foundation of China (61503093, 91438202, 61603115, 61903214), Project Agreement No. AUGA5710053114 with Harbin Institute of Technology, and Open Fund of National Defense Key Discipline Laboratory of Micro-Spacecraft Technology (Grant Number HIT.KLOF.MST.201502).
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Published In
Journal of Aerospace Engineering
Volume 33 • Issue 4 • July 2020
Copyright
©2020 American Society of Civil Engineers.
History
Received: Jun 23, 2017
Accepted: Nov 27, 2019
Published online: Mar 24, 2020
Published in print: Jul 1, 2020
Discussion open until: Aug 24, 2020
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