ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Line-of-sight Pointing Control of Spacecraft Actuated by Two Flywheels Considering Input Saturation
Received date: 2012-05-14
Revised date: 2012-09-10
Online published: 2013-03-29
Supported by
National Basic Research Program of China (2012CB720000); National Natural Science Foundation of China (61174201)
The attitude maneuver control of a spacecraft controlled by two flywheels with nonzero initial angular momentum is investigated in this paper. To deal with the pointing control of line-of-sight outside the plane of the two-flywheel-axis, a desired final attitude generation algorithm and an input anti-saturation sliding mode control algorithm are developed. First, the necessary conditions for actuating the line-of-sight toward a specified direction is obtained based on an analysis of the spacecraft's feasible attitude when its attitude remains motionless. Then, the desired attitude of the spacecraft with minimum pointing error between the line-of-sight and the specified direction is obtained under such conditions. Finally, an input anti-saturation sliding mode control algorithm is proposed after linearizing the dimension-reduced state equations. Simulation results and analysis illustrate the feasibility and effectiveness of the proposed algorithms.
Key words： spacecraft; underactuate; line-of-sight; attitude control; input saturation
CUI Hutao , CHENG Xiaojun . Line-of-sight Pointing Control of Spacecraft Actuated by Two Flywheels Considering Input Saturation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(3) : 644 -654 . DOI: 10.7527/S1000-6893.2013.0102
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