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Research Papers

Minimum-Time Eigenaxis Rotation Maneuvers for a Spacecraft With Three Axis Reaction Wheels

[+] Author and Article Information
Haoyu Wang

School of Astronautics,
Beihang University,
New Main Building,
Room B1126,
Beijing 100191, China
e-mail: wanghaoyu@sa.buaa.edu.cn

Guowei Zhao

School of Astronautics,
Beihang University,
New Main Building,
Room B1126,
Beijing 100191, China
e-mail: zhaoguowei@buaa.edu.cn

Hai Huang

School of Astronautics,
Beihang University,
New Main Building,
Room B1126,
Beijing 100191, China
e-mail: hhuang@buaa.edu.cn

1Corresponding author.

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received July 30, 2014; final manuscript received June 13, 2015; published online August 13, 2015. Assoc. Editor: Umesh Vaidya.

J. Dyn. Sys., Meas., Control 137(11), 111004 (Aug 13, 2015) (11 pages) Paper No: DS-14-1304; doi: 10.1115/1.4030912 History: Received July 30, 2014

This paper proposes a planning method of the theoretically fastest slew path, and correspondingly, an analytical open-loop control law for the minimum-time eigenaxis rotation of spacecraft with three reaction wheels. The path planning and the control law are based on the angular momentum conservation of the spacecraft system. Then, a control scheme is also proposed to correct the maneuver error caused by model uncertainties. The control law and control scheme are verified in numerical simulation cases. The results show that the control law would realize the fastest slew path for an eigenaxis rotation, and the control scheme is feasible in shortening the slew time.

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References

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Figures

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Fig. 1

The spacecraft system with three reaction wheels

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Fig. 2

ω history for the minimum-time eigenaxis rotation

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Fig. 3

ω· history for the minimum-time eigenaxis rotation

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Fig. 4

The platform and the eigenaxis

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Fig. 5

Histories of ω and its components

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Fig. 6

Histories of the quaternions of the platform

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Fig. 7

Histories of ω and its components when the model parameter uncertainties are considered

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Fig. 8

Histories of quaternion components when the model parameter uncertainties are considered

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Fig. 9

Histories of the platform angular velocity components using the standard linear quaternion feedback regulator

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Fig. 10

Histories of the control torques on the reaction wheels using the standard linear quaternion feedback regulator

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