A non-contact spacecraft architecture with extended stochastic state observer based control for gravity mission

doi:10.23919/JSEE.2021.000039

Journal of Systems Engineering and Electronics ›› 2021, Vol. 32 ›› Issue (2): 460-472.doi: 10.23919/JSEE.2021.000039

• CONTROL THEORY AND APPLICATION • Previous Articles Next Articles

A non-contact spacecraft architecture with extended stochastic state observer based control for gravity mission

Sheng LIU¹(), He LIAO^2,*(), Jinjin XIE³(), Yufei XU³(), Yi XU³(), Zhongxin TANG³(), Chuang YAO³()

¹ School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
² School of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
³ Research Center, Shanghai Institute of Satellite Engineering, Shanghai 201109, China

Received:2020-06-09 Online:2021-04-29 Published:2021-04-29
Contact: He LIAO E-mail:liushenglonely@163.com;liaohe_crane@nuaa.edu.cn;xiejin1002@163.com;xyf_nuaa@126.com;healwoolanti@163.com;yujishenlan@163.com;yaochuang0@126.com
About author:|LIU Sheng was born in 1984. He received his M.S. degree from Shanghai Institute of Satellite Engineering, Shanghai, China in 2008. He is currently a doctor candidate of the School of Astronautics, Northwestern Polytechnical University, Xi’an, China. His research interests include attitude control of advanced spacecraft, and experimental analysis of air bearing devices. E-mail: liushenglonely@163.com||LIAO He was born in 1984. He received his B.S. degree in mechanical engineering from Nanchang Institute of Aeronautical Technology, Nanchang, China, in 2005, and M.S. and Ph.D. degrees from the School of Astronautics, Harbin Institute of Technology, Harbin, China, in 2007 and 2011, respectively. He is currently an associate professor with the School of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing, China. His research interests include spacecraft dynamics and control, nonlinear estimation and active vibration isolation. E-mail: liaohe_crane@nuaa.edu.cn||XIE Jinjin was born in 1986. He received his B.S. degree in measurement, and control technology and instrumentations from Southeast University, Nanjing, China, in 2008, and Ph.D. degree in precision instruments and machinery from Beihang University, Beijing, China, in 2016. He is currently a senior engineer with Shanghai Institute of Satellite Engineering, Shanghai, China. His research interests include vibration control of flywheels, theoretical and experimental analysis of magnetic levitation devices and spacecraft attitude control. E-mail: xiejin1002@163.com||XU Yufei was born in 1984. She received her B.S. and Ph.D. degrees from the School of Automation, Nanjing University of Aeronautics and Astronautics, Nanjing, China, in 2006 and 2011, respectively. She is currently a senior engineer with Shanghai Institute of Satellite Engineering, Shanghai, China. Her research interests include fault diagnosis and fault tolerant control, spacecraft dynamic modeling, active vibration control and attitude control of advanced spacecraft. E-mail: xyf_nuaa@126.com||XU Yi was born in 1987. He received his B.S. and M.S. degrees in communication engineering from Chengdu University of Electronic Science and Technology, Chengdu, China, in 2008 and 2011, respectively. He is currently a senior engineer with Shanghai Institute of Satellite Engineering, Shanghai, China. His research interests include spacecraft design, spacecraft dynamics and control, communication technology for satellite-to-satellite tracking, and active vibration isolation. E-mail: healwoolanti@163.com||TANG Zhongxin was born in 1985. He received his B.S. and Ph.D. degrees in the School of Astronautics from Beihang University, Beijing, China, in 2008 and 2014, respectively. He is currently a senior engineer with Shanghai Institute of Satellite Engineering, Shanghai, China. His research interests include spacecraft orbit design, spacecraft formation flying, theoretical and experimental analysis of air bearing devices, and spacecraft dynamics and attitude control of advanced spacecraft. E-mail: yujishenlan@163.com||YAO Chuang was born in 1993. He received his B.S. and M.S. degrees in the School of Astronautics from Beihang University, Beijing, China, in 2015 and 2018, respectively. He is currently an engineer with Shanghai Institute of Satellite Engineering, Shanghai, China. His research interests include spacecraft orbit design and drag-free control, experimental analysis of air bearing devices, spacecraft dynamics and attitude control of advanced spacecraft, and dynamic modeling identification. E-mail: yaochuang0@126.com
Supported by:
This work was supported by the National Natural Science Foundation of China (51705327; 51805329), the Fundamental Research Funds for the Central Universities of China (NS2020065), and the Natural Science Foundation of Shanghai (19ZR1453300);This work was supported by the National Natural Science Foundation of China (51705327; 51805329), the Fundamental Research Funds for the Central Universities of China (NS2020065), and the Natural Science Foundation of Shanghai (19ZR1453300)

Abstract

Abstract:

A novel non-contact spacecraft architecture with the extended stochastic state observer for disturbance rejection control of the gravity satellite is proposed. First, the precise linear driving non-contact voice-coil actuators are used to separate the whole spacecraft into the non-contact payload module and the service module, and to build an ideal loop with precise dynamics for disturbance rejection control of the payload module. Second, an extended stochastic state observer is enveloped to construct the overall nonlinear external terms and the internal coupled terms of the payload module, enabling the controller design of the payload module turned into the linear form with simple bandwidth-parameterization tuning in the frequency domain. As a result, the disturbance rejection control of the payload module can be explicitly achieved in a timely manner without complicated tuning in actual implementation. Finally, an extensive numerical simulation is conducted to validate the feasibility and effectiveness of the proposed approach.

Key words: non-contact spacecraft architecture, extended stochastic state observer, disturbance rejection control, non-contact voice-coil actuators, bandwidth-parameterization tuning

Sheng LIU, He LIAO, Jinjin XIE, Yufei XU, Yi XU, Zhongxin TANG, Chuang YAO. A non-contact spacecraft architecture with extended stochastic state observer based control for gravity mission[J]. Journal of Systems Engineering and Electronics, 2021, 32(2): 460-472.

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Parameter	Simulation condition
Earth gravity model	J₂, J₃, J₄
Magnetic field model	International geomagnetic reference field model
Atmospheric drag model	Exponential model
Solar radiation pressure model	Photon radiation
Mass of PM/kg	200
Mass of SM/kg	1 200
Inertial matrix of PM	$\left[ {\begin{array}{*{20}{c}} {20}&{ - 0.2}&1 \\ { - 0.2}&{35}&{0.5} \\ 1&{0.5}&{36} \end{array}} \right]$
Inertial matrix of SM	$\left[ {\begin{array}{*{20}{c}} {230}&{ - 14}&6 \\ { - 14}&{345}&1 \\ 6&1&{388} \end{array}} \right]$

Parameter	Simulation condition
Noise spectral density of accelerometer/(m/s²/Hz^1/2)	2×10^?12
Accelerometer bandwidth/Hz	5×10^?3 to 0.1
Position noise of GPS/m	30
Velocity noise of GPS/(m/s)	0.3
Noise of relative position sensor/μm	10
Noise of star tracker/ (″)	10
Noise spectral density of NCVCA/(μN/Hz^1/2)	2
Noise spectral density of thruster/(mN/Hz^1/2)	30

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A non-contact spacecraft architecture with extended stochastic state observer based control for gravity mission

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