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第37届中国控制会议

作者： Liqian Dou Hui Du Wenjing Liu School of Electrical Engineering and Automation Beijing Institute of Control Engineering

This paper proposed a terminal sliding mode control strategy based on a type-2 fuzzy disturbance observer（FDO）for the spacecraft with liquid slosh and flexible structure（SLF）.The type-2 fuzzy logic system（FLS） has a better behavior than type-1 FLS on handling the ***,the type-2 FDO was adopted to estimate the whole uncertainties which contains the perturbations caused by the liquid fuel slosh and flexible structure,the unknown elements of the model and the external ***,the terminal sliding mode surface was designed to ensure the system stability and ***,the stability of the proposed control scheme was proved based on the Lyapunov stability ***,numerical simulations showed the effectiveness and advantages of the proposed method.

关键词： type-2 FDO coupled spacecraft liquid slosh flexible structure terminal sliding mode

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Heteroclinic bifurcations in attitude maneuver of coupled slosh-spacecraft with flexible appendage

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Science China(Technological Sciences) 2011年第8期54卷 2090-2099页

作者： YUE BaoZeng SONG XiaoJuan Department of Mechanics School of Aerospace Engineering Beijing Institute of Technology Beijing 100081 China

In this paper, the chaotic dynamics in an attitude transition maneuver of a slosh-spacecraft coupled with flexible appendage in going from minor axis to major axis spin under the influence of dissipative effects due to fuel slosh and a small flexible appendage constrained to only torsional vibration is investigated. The slosh-spacecraft coupled with flexible appendage in attitude maneuver carrying a sloshing liquid is considered as multi-body system with the sloshing motion modeled as a spherical pendulum. The focus in this paper is that the dynamics of the liquid and flexible appendage vibration are coupled. The equations of motion are derived and transformed into a form suitable for the application of Melnikov’s method. Melnikov’s integral is used to predict the transversal intersections of the stable and unstable manifolds for the perturbed system. An analytical criterion for chaotic motion is derived in terms of system parameters. This criterion is evaluated for its significance to the design of spacecraft. The dependence of the onset of chaos on quantities such as body shape and magnitude of damping values, fuel fraction and torsional vibration frequency of flexible appendage are investigated. In addition, we show that a spacecraft carrying a sloshing liquid, after passive reorientation maneuver, will end up with periodic limit motion other than a final major axis spin because of the intrinsic non-linearity of fuel slosh. Furthermore, an extensive numerical simulation is carried out to validate the Melnikov’s analytical result.

关键词： chaotic attitude maneuver liquid-filled spacecraft flexible appendage liquid slosh

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