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Marginalized particle filter for spacecraft attitude estimation from vector measurements 被引量:3
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作者 Yaqiu LIU Xueyuan JIANG guangfu ma 《控制理论与应用(英文版)》 EI 2007年第1期60-66,共7页
An algorithm based on the marginalized particle filters (MPF) is given in details in this paper to solve the spacecraft attitude estimation problem: attitude and gyro bias estimation using the biased gyro and vecto... An algorithm based on the marginalized particle filters (MPF) is given in details in this paper to solve the spacecraft attitude estimation problem: attitude and gyro bias estimation using the biased gyro and vector observations. In this algorithm, by marginalizing out the state appearing linearly in the spacecraft model, the Kalman filter is associated with each particle in order to reduce the size of the state space and computational burden. The distribution of attitude vector is approximated by a set of particles and estimated using particle filter, while the estimation of gyro bias is obtained for each one of the attitude particles by applying the Kalman filter. The efficiency of this modified MPF estimator is verified through numerical simulation of a fully actuated rigid body. For comparison, unscented Kalman filter (UKF) is also used to gauge the performance of MPE The results presented in this paper clearly derfionstrate that the MPF is superior to UKF in coping with the nonlinear model. 展开更多
关键词 Attitude estimation Particle filter SPACECRAFT Nonlinear filter QUATERNION
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Backstepping-based distributed coordinated tracking formultiple uncertain Euler-Lagrange systems 被引量:4
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作者 yanchao sun wenjia wang +2 位作者 guangfu ma zhuo li chuanjiang li 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2016年第5期1083-1095,共13页
Based on the idea of backstepping design, distributedcoordinated tracking problems under directed topology are discussedfor multiple Euler-Lagrange (EL) systems. The dynamicleader case is considered. First, with the... Based on the idea of backstepping design, distributedcoordinated tracking problems under directed topology are discussedfor multiple Euler-Lagrange (EL) systems. The dynamicleader case is considered. First, with the parameter-linearity property,a distributed coordinated adaptive control scheme is proposedfor EL systems in the presence of parametric uncertainties.Then, subject to nonlinear uncertainties and external disturbances,an improved adaptive control algorithm is developed by usingneural-network (NN) approximation of nonlinear functions. Bothproposed algorithms can make tracking errors for each followerultimately bounded. The closed-loop systems are investigated byusing the combination of graph theory, Lyapunov theory, and BarbalatLemma. Numerical examples and comparisons with othermethods are provided to show the effectiveness of the proposedcontrol strategies. 展开更多
关键词 multi-agent systems Euler-Lagrange (EL) system coordinatedtracking backstepping control distributed control.
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Finite-time attitude tracking control for spacecraft without angular velocity measurements 被引量:1
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作者 Li Yuan guangfu ma +1 位作者 Chuanjiang Li Boyan Jiang 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2017年第6期1174-1185,共12页
The output feedback control for spacecraft attitude tracking system is investigated in this study. It is assumed that angular velocity measurements are not available for feedback control.A technique named adding power... The output feedback control for spacecraft attitude tracking system is investigated in this study. It is assumed that angular velocity measurements are not available for feedback control.A technique named adding power integrator(API) is adopted to estimate the pseudo-angular-velocity. Then we design a finite-time attitude control law, which only utilizes the relative attitude information. The stability analyses of the feedback system are proved as well, which shows the attitude tracking errors will converge into a region of zero even the external disturbances exist. The simulation results illustrate the high precision and robust attitude control performance of the proposed control strategy. 展开更多
关键词 output feedback spacecraft attitude stabilization finite-time control
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Fast fixed-time three-dimensional terminal guidance with non-concave trajectory constraint
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作者 Youmin GONG Yanning GUO +2 位作者 Yueyong LYU Dongyu LI guangfu ma 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第3期208-218,共11页
Focusing on the non-concave trajectory constraint,a sliding-mode-based nonsingular feedback fast fixed-time three-dimensional terminal guidance of rotor unmanned aerial vehicle landing,planetary landing and spacecraft... Focusing on the non-concave trajectory constraint,a sliding-mode-based nonsingular feedback fast fixed-time three-dimensional terminal guidance of rotor unmanned aerial vehicle landing,planetary landing and spacecraft rendezvous and docking terminal phase with external disturbance is investigated in this paper.Firstly,a fixed-time observer based on real-time differentiator is developed to compensate for the external disturbance,whose estimation error can converge to zero after a time independent of the initial state.Then,a sliding surface ensuring fixed-time convergence is presented.This sliding surface can guarantee that the vehicle achieves a non-concave trajectory,which is better for avoiding collision and maintaining the visibility of the landing site or docking port.Next,the nonsingular guidance ensuring the fixed-time convergence of the sliding surface is proposed,which is continuous and chatter free.At last,three numerical simulations of Mars landing are performed to validate the effectiveness and correctness of the designed scheme. 展开更多
关键词 THREE-DIMENSIONAL Terminal guidance Non-concave trajectory constraint Fast fixed-time control Sliding mode control
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Spacecraft formation-containment flying control with time-varying translational velocity 被引量:6
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作者 Liangming CHEN Chuanjiang LI +2 位作者 Yanning GUO guangfu ma Baolong ZHU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第1期271-281,共11页
This paper investigates the problem of Spacecraft Formation-Containment Flying Control(SFCFC)when the desired translational velocity is time-varying.In SFCFC problem,there are multiple leader spacecraft and multiple f... This paper investigates the problem of Spacecraft Formation-Containment Flying Control(SFCFC)when the desired translational velocity is time-varying.In SFCFC problem,there are multiple leader spacecraft and multiple follower spacecraft and SFCFC can be divided into leader spacecraft’s formation control and follower spacecraft’s containment control.First,under the condition that only a part of leader spacecraft can have access to the desired time-varying translational velocity,a velocity estimator is designed for each leader spacecraft.Secondly,based on the estimated translational velocity,a distributed formation control algorithm is designed for leader spacecraft to achieve the desired formation and move with the desired translational velocity simultaneously.Then,to ensure all follower spacecraft converge to the convex hull formed by the leader spacecraft,a distributed containment control algorithm is designed for follower spacecraft.Moreover,to reduce the dependence of the designed control algorithms on the graph information and increase system robustness,the control gains are changing adaptively and the parametric uncertainties are handled,respectively.Finally,simulation results are provided to illustrate the effectiveness of the theoretical results. 展开更多
关键词 Adaptive GAIN technique Distributed CONTROL Formation-containment FORMATION CONTROL SPACECRAFT FORMATION FLYING
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Three-dimensional finite-time cooperative guidance for multiple missiles without radial velocity measurements 被引量:19
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作者 Teng LYU Chuanjiang LI +1 位作者 Yanning GUO guangfu ma 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2019年第5期1294-1304,共11页
In order to simultaneously attack a target with impact angle constraint in threedimensional(3-D) space, a novel distributed cooperative guidance law for multiple missiles under directed communication topologies is pro... In order to simultaneously attack a target with impact angle constraint in threedimensional(3-D) space, a novel distributed cooperative guidance law for multiple missiles under directed communication topologies is proposed without radial velocity measurements. First, based on missiles-target 3-D relative motion equations, the multiple missiles cooperative guidance model with impact angle constraint is constructed. Then, in Line-of-Sight(LOS) direction, based on multiagent system cooperative control theory, one guidance law with directed topologies is designed with strict proof, which can guarantee finite time consensus of multiple missiles' impact times. Next, in elevation direction and azimuth direction of LOS, based on homogeneous system stability theory and integral sliding mode control theory, two guidance laws are proposed respectively with strict proof, which can guarantee LOS angles converge to desired values and LOS angular rates converge to zero in finite time. Finally, the effectiveness of the designed cooperative guidance law is demonstrated through simulation results. 展开更多
关键词 3-D cooperative guidance Directed communication TOPOLOGIES Finite time Impact angle CONSTRAINT RADIAL VELOCITY MEASUREMENTS
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Data-driven model-free adaptive attitude control of partially constrained combined spacecraft with external disturbances and input saturation 被引量:5
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作者 Han GAO guangfu ma +1 位作者 Yueyong LYU Yanning GUO 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2019年第5期1281-1293,共13页
This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a... This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a novel dynamic linearization data model for the partially constrained combined spacecraft with external disturbances is established. The generalized disturbances composed of external disturbances and dynamic linearization errors are then reconstructed by a Discrete Extended State Observer(DESO). With the dynamic linearization data model and reconstructed information, a DESO-MFAC strategy for the combined spacecraft is proposed based only on input and output data. Next, the input saturation is overcome by introducing an antiwindup compensator. Finally, numerical simulations are carried out to demonstrate the effectiveness and feasibility of the proposed controller when the dynamic properties of the partially constrained combined spacecraft are completely unknown. 展开更多
关键词 Attitude CONTROL COMBINED SPACECRAFT DATA-DRIVEN CONTROL Discrete Extended State Observer(DESO) Input SATURATION
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Conjoint analysis of crowbar switching scheme and its resistancebased on statistical sampling for LVRT of DFIG 被引量:1
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作者 Yanbin QU Le GAO +2 位作者 guangfu ma Huihui SONG Shitao WANG 《Journal of Modern Power Systems and Clean Energy》 SCIE EI CSCD 2019年第3期558-567,共10页
An active crowbar protective circuit is an effective and common approach for low voltage ride through(LVRT) of a doubly-fed induction generator(DFIG). The crowbar resistance value and its switching scheme both have cr... An active crowbar protective circuit is an effective and common approach for low voltage ride through(LVRT) of a doubly-fed induction generator(DFIG). The crowbar resistance value and its switching scheme both have crucial effects on safety recovery. The effects encountered are correlative dependence and interplay so that analyzing them from a single factor, as most existing LVRT control methods would do, obtains a partial optimal solution. This paper combines these two factors toanalyze their coordination effects on the LVRT control,and to also investigate whether the global optimal performance of these factors can be achieved. The principles for resistance selection and the schemes for crowbar switching are discussed first. Next, the coupling relationship is ana-lyzed based on statistical sampling simulation data with different resistance values and various switching schemes.The results demonstrate that their coordination has critical influence on rotor peak current, DC-link voltage and reactive power. The optimal coordination will be different according to specific requirements. Hence the global optimal combination could be achieved when all requirements are taken into consideration. 展开更多
关键词 DOUBLY-FED induction generator(DFIG) Active CROWBAR Switching scheme RESISTANCE value Statistical sampling data
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Attitude control without angular velocity measurement for flexible satellites 被引量:1
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作者 Qinghua ZHU guangfu ma +1 位作者 Xiaoting WANG Aiguo WU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2018年第6期1345-1351,共7页
In this paper, by using quaternion models, the problem of attitude control is investigated for a class of flexible satellites. Two control laws are presented for the considered flexible satellite models to guarantee c... In this paper, by using quaternion models, the problem of attitude control is investigated for a class of flexible satellites. Two control laws are presented for the considered flexible satellite models to guarantee convergence of the closed-loop systems without using angular velocity measurement. One is in the form of a partial state feedback for the case where the modal variable is available, and the other is in the form of an observer-based partial state feedback for the case where the modal variable cannot be measured. Finally, an example is employed to illustrate the effectiveness of the proposed control laws. 展开更多
关键词 Attitude control Flexible satellites Modal variables Quaternion models PASSIVITY
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