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An improved nonlinear control strategy for deep space formation flying spacecraft

Acta Mechanica Sinica 2009年第6期25卷 847-856页

作者： peng li pingyuan cui hutao cui deep space exploration research center,harbin institute of technology, 150080 harbin, china deep space exploration research center Harbin Institute of Technology Harbin China

This paper aims to provide further study on the nonlinear modeling and controller design of formation flying spacecraft in deep space missions. First, in the Sun-Earth system, the nonlinear formation dynamics for the circular restricted three-body problem （CRTBP） and elliptic restricted three-body problem （ERTBP） are presented. Then, with the Floquet mode method, an impulsive controller is developed to keep the Chief on the desired Halo orbit. Finally, a nonlinear adaptive control scheme based on Nonzero set- point LQR and neural network is proposed to achieve high precision formation maneuver and keeping. The simulation results indicate that the proposed nonlinear control strategy is reasonable as it considers not only the orbit keeping of the Chief, but also the formation modeling inaccuracy. Moreover, the nonlinear adaptive control scheme is effective to improve the control accuracy of the formation keeping.

关键词： spacecraft formation flying. libration pointHalo orbit - Nonlinear control

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UPF based autonomous navigation scheme for deep space probe

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Journal of Systems Engineering and Electronics 2008年第3期19卷 529-536页

作者： li peng cui hutao cui pingyuan deep space exploration research center Harbin Inst. of Technology Harbin 150080 P. R. China

The autonomous "celestial navigation scheme" for deep space probe departing from the earth and the autonomous "optical navigation scheme" for encountering object celestial body are presented. Then, aiming at the conditions that large initial estimation errors and non-Gaussian distribution of state or measurement errors may exist in orbit determination process of the two phases, UPF (unscented particle filter) is introduced into the navigation schemes. By tackling nonlinear and non-Gaussian problems, UPF overcomes the accuracy influence brought by the traditional EKF (extended Kalman filter), UKF (unscented Kalman filter), and PF (particle filter) schemes in approximate treatment to nonlinear and non-Gaussian state model and measurement model. The numerical simulations demonstrate the feasibility and higher accuracy of the UPF navigation scheme.

关键词： control and navigation technology of aircraft nonlinear and non-Gaussian unscented particle filter autonomous orbit determination celestial navigation optical navigation.

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