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Mixed H_2/H_∞ State Feedback Attitude Control of Microsatellite Based on Extended LMI Method 认领 引用 被引量：2
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作者 Keke Shi Chuang Liu +1 位作者 Feng Wang Zhaowei Sun 《Journal of Harbin Institute of Technology(New Series)》 CAS 2016年第5期15-22,共8页
For the appearance of the additive perturbation of controller gain when the controller parameter has minute adjustment at the initial running stage of system,to avoid the adverse effects,this paper investigates the mi... For the appearance of the additive perturbation of controller gain when the controller parameter has minute adjustment at the initial running stage of system,to avoid the adverse effects,this paper investigates the mixed H_2/H_∞ state feedback attitude control problem of microsatellite based on extended LMI method.Firstly,the microsatellite attitude control system is established and transformed into corresponding state space form.Then,without the equivalence restriction of the two Lyapunov variables of H_2 and H∞performance,this paper introduces additional variables to design the mixed H_2/H_∞ control method based on LMI which can also reduce the conservatives.Finally,numerical simulations are analyzed to show that the proposed method can make the satellite stable within 20 s whether there is additive perturbation of the controller gain or not.The comparative analysis of the simulation results between extended LMI method and traditional LMI method also demonstrates the effectiveness and feasibility of the proposed method in this paper. 展开更多
关键词 microsatellite attitude control mixed H2 / H∞ additive perturbationcontrol state feedback control extended LMI method
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High precision attitude dynamic tracking control of a moving space target 认领 引用 被引量：9
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作者 Yunhua WU Mohong ZHENG +3 位作者 Wei HE Feng WANG Zhiming CHEN Bing HUA 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2019年第10期2324-2336,共13页
On-orbit spacecraft face many threats,such as collisions with debris or other spacecraft.Therefore,perception of the surrounding space environment is vitally important for on-orbit spacecraft.Spacecraft require a dyna... On-orbit spacecraft face many threats,such as collisions with debris or other spacecraft.Therefore,perception of the surrounding space environment is vitally important for on-orbit spacecraft.Spacecraft require a dynamic attitude tracking ability with high precision for such missions.This paper aims to address the above problem using an improved backstepping controller.The tracking mission is divided into two phases:coarse alignment and fine alignment.In the first phase,a traditional saturation controller is utilized to limit the maximum attitude angular velocity according to the actuator’s ability.For the second phase,the proposed backstepping controller with different virtual control inputs is applied to track the moving target.To fulfill the high precision attitude tracking requirements,a hybrid attitude control actuator consisting of a Control Moment Gyro(CMG)and Reaction Wheel(RW)is constructed,which can simultaneously avoid the CMG singularity and RW saturation through the use of an angular momentum optimal management strategy,such as null motion.Finally,five simulation scenarios were carried out to demonstrate the effectiveness of the proposed control strategy and hybrid actuator. 展开更多
关键词 Space moving target Attitude dynamic tracking Backstepping controller Improved virtual control input Hybrid actuator
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Preparation and Properties of Smart Thermal Control and Radiation Protection Materials for Multi-functional Structure of Small Spacecraft 认领 引用 被引量：3
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作者 shijie Zhang Xibin Cao +3 位作者 Yingqiang Luan Xinxin Ma Xiaohui Lin Xianren Kong 《Journal of Materials Science & Technology》 SCIE EI CAS CSCD 2011年第10期879-884,共6页
Considering the unique properties of small spacecraft, such as light weight, low power-consumption and high heat flux density, a new kind of lightweight boron carbide （B4C） radiation-protection coating material was ... Considering the unique properties of small spacecraft, such as light weight, low power-consumption and high heat flux density, a new kind of lightweight boron carbide （B4C） radiation-protection coating material was proposed. New techniques for preparing LSMO thermal control coating and B4C radiation-protection coating were developed. The sample piece of multi-functional structure was manufactured by using the proposed materials, and a series of performance tests, such as thermal control and radiation-protection behaviors were evaluated. Test results show that： the emissivity of the multi-functional structure varies from 0.42 to 0.86 at 240 K to 353 K and the phase transition temperature is about 260 K. The electron radiation-protection ability of the multi-functional structure is 3.3 times better than that of Al material. The performance index of this multi-functional structure can meet the requirements for space application in on-board electronic equipment. 展开更多
关键词 Coating material Phase transition temperature Temperature-dependent emissivity-variable Radiation-protection Spacecraft
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A new method of choosing scales in wavelet transform for damping identification 认领 引用 被引量：5
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作者 何蕊 罗文波 王本利 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2008年第2期164-166,共3页
A systematic study of the method of selecting scales in wavelet transform for damping identification in frequency domain was carried out. A method to select the scale with the modulus at the maximum was developed by e... A systematic study of the method of selecting scales in wavelet transform for damping identification in frequency domain was carried out. A method to select the scale with the modulus at the maximum was developed by extending the range of scales. It is proved that using this method in small damping ratio and linear system, we can achieve better results in identification of the closely-spaced model. 展开更多
关键词 wavelet transform damping identification closely-spaced model
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Dual-quaternion-based modeling and control for motion tracking of a tumbling target 认领 引用 被引量：1
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作者 PENG Xuan SHI Xiaoping GONG Yupeng 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2019年第5期985-994,共10页
This paper investigates the problem of controlling a chasing spacecraft(chaser)to track and rendezvous with an uncontrolled target.Based on the actual situation,the torque-free motion of an axisymmetric prolate rigid ... This paper investigates the problem of controlling a chasing spacecraft(chaser)to track and rendezvous with an uncontrolled target.Based on the actual situation,the torque-free motion of an axisymmetric prolate rigid body is employed to represent the short-term attitude motion of the tumbling target.By taking advantage of the dual quaternion’s compact and efficient description of the general rigid motion,the coupled and integrated model of the 6-degree-of-freedom(6-DOF)relative motion between the chaser and the tumbling target is derived in the chaser’s body fixed frame after taking full consideration of coordinate transformation.Based on the logarithm of dual quaternion,a sliding mode control(SMC)law based on the exponential reaching law and the continuous relay function is brought forward to address the problem of synchronization control of the 6-DOF relative motion.Simulation results illustrate the effectiveness of the proposed method. 展开更多
关键词 tumbling target dual-quaternion coupled dynamics relative motion
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Integrated modeling of spacecraft relative motion dynamics using dual quaternion 认领 引用 被引量：1
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作者 PENG Xuan SHI Xiaoping GONG Yupeng 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2018年第2期367-377,共11页
To realize high accurate control of relative position and attitude between two spacecrafts, the coupling between position and attitude must be fully considered and a more precise model should be established. This pape... To realize high accurate control of relative position and attitude between two spacecrafts, the coupling between position and attitude must be fully considered and a more precise model should be established. This paper breaks the traditional divide and conquer idea, and uses a mathematical tool, namely dual quaternion to establish the integrated 6 degree-of-freedom(6-DOF) model of relative position and attitude, which describes the coupled relative motion in a compact and efficient form and needs less information of the target. Considering the complex operation rules and the unclarity of the current relative motion model in dual quaternion, necessary mathematical foundations are given at first, followed by clear and detailed modeling process and analysis. Finally a generalized proportion-derivative(PD) controller law is designed. The simulation results show that based on the integrated model established by dual quaternion, this control law can achieve a high control accuracy of relative motion. 展开更多
关键词 relative motion dual quaternion position and attitude coupling integrated modeling
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Influences of vacancy defects on thermal conductivities of Ge thin films 认领 引用 被引量：1
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作者 ZHANG Xingli SUN Zhaowei 《Rare Metals》 SCIE EI CAS CSCD 2011年第4期317-321,共5页
The effects of vacancy defects on the thermal conductivity of Ge thin films were investigated by employing molecular dynamics （MD） simula- tions and theoretical analysis based on the Boltzmann equation. Both the MD ... The effects of vacancy defects on the thermal conductivity of Ge thin films were investigated by employing molecular dynamics （MD） simula- tions and theoretical analysis based on the Boltzmann equation. Both the MD and theoretical results show that the lattice thermal conductivity dramatically decreases with the increasing of vacancy concentration at 400 and 500 K. In addition, the dependence of vacancy concentration on the thermal conductivity of Ge thin films becomes less sensitive as the temperature increases. Theoretical results also confirm that the major part of the lattice thermal conductivity reduction is associated with the point-defect scattering and phonon-phonon scattering processes. 展开更多
关键词 molecular dynamics thermal conductivity vacancy defects thin films germanium
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Predicting test data of aluminum honeycomb sandwich board based on volterra adaptive filters 认领 引用 被引量：2
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作者 何蕊 罗文波 +1 位作者 王本利 孔宪仁 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2011年第1期145-148,共4页
Random vibration test was done on aluminum honeycomb sandwich board. The result suggested that chaotic behavior is found in the test data. The Volterra expression can not be gained from the input and output data direc... Random vibration test was done on aluminum honeycomb sandwich board. The result suggested that chaotic behavior is found in the test data. The Volterra expression can not be gained from the input and output data directly in this paper. The state space reconstruction was used to convert the system observed data into the quasi-input/output pairs, and the second-order Voherra adaptive filter was used to predict the test data. It is shown that combining the state space reconstruction with the Volterra adaptive filter, these chaotic series could be accurately predicted. 展开更多
关键词 chaotic behavior： Voherra： aluminum honeycomb sandwich board： random test
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Response regimes of narrow-band stochastic excited linear oscillator coupled to nonlinear energy sink 认领 引用 被引量：8
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作者 Xiong Huai Kong Xianren +1 位作者 Yang Zhenguo Liu Yuan 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2015年第2期457-468,共12页
This paper draws attention to the issue of the vibration absorption of nonlinear mechani- cal system coupled to nonlinear energy sink （NES） under the impact of the narrow band stochastic excitation. Firstly, based o... This paper draws attention to the issue of the vibration absorption of nonlinear mechani- cal system coupled to nonlinear energy sink （NES） under the impact of the narrow band stochastic excitation. Firstly, based on the complex-averaging method and frequency detuning methodology, response regimes of oscillators have been researched under the linear impact of coupling a nonlinear attachment with less relativistic mass and an external sinusoidal forcing, of which results turn out that the quasi-periodicity response regime of system which occurs when the external excitation amplitude exceeds the critical values will be the precondition of the targeted energy transfer. Secondly, basing on the path integration method, vibration suppression of NES has been researched when it is affected by a main oscillator with a narrow band stochastic force in the form of trigono- metric functions, of which results show that response regimes are affected by the amplitude of stochastic excitation and the disturbance strength. Finally, all these conclusions have been approved by the numerical verification and coincided with the theoretical analysis; meanwhile, after the com- paring analysis with the optimal linear absorber, it turns out that the NES which is affected by the narrow band stochastic force could also suppress the vibration of system with a better effect. 展开更多
关键词 Nonlinear energy sink Path integration method Stochastic excitation Targeted energy transfer Vibration absorption
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Adaptive Synchronization of Networked Euler-Lagrange Systems with Directed Switching Top ology 认领 引用 被引量：1
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作者 GUO Hai-Bo LI Hua-Yi +2 位作者 ZHONG Wei-Chao ZHANG Shi-Jie CAO Xi-Bin 《自动化学报》 EI CAS CSCD 北大核心 2014年第11期2541-2548,共8页
In this paper, the cooperative control problem of networked Euler-Lagrange systems with parametric uncertainties and unidirectional interaction is addressed under dynamically changing topology. As the communication gr... In this paper, the cooperative control problem of networked Euler-Lagrange systems with parametric uncertainties and unidirectional interaction is addressed under dynamically changing topology. As the communication graph evolves over time, a distributed control law via local effective interactions is designed. Adaptive techniques are used to deal with parametric uncertainties in the dynamics. With a continuous Lyapunov function, it is obtained that synchronization can still be achieved asymptotically as long as the union graph of the switching topologies has a directed spanning tree frequently enough. Extensions to disturbance rejection problems are also addressed using simple disturbance-observer or sliding mode control scheme. Illustrative examples with comparing simulation in the context of attitude synchronization of five non-identical spacecraft are further presented to show the effectiveness of the proposed cooperative control strategy. 展开更多
关键词 拉格朗日系统 自适应同步 欧拉 网络 开关 Lyapunov函数 参数不确定性 易学
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Dynamics Analysis of Nonlinear Energy Sink for Metal-Rubber Vibration Absorber 认领 引用 被引量：1
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作者 Xianren Kong Huai Xiong +1 位作者 Yuan Liu Zhenguo Yang 《Journal of Harbin Institute of Technology(New Series)》 CAS 2017年第5期39-45,共7页
Recent advances in the application of the nonlinear energy sink under a sinusoidal excitation make it possible to investigate metal-rubber vibration absorber. To provide such a vibration absorber for the integrated sp... Recent advances in the application of the nonlinear energy sink under a sinusoidal excitation make it possible to investigate metal-rubber vibration absorber. To provide such a vibration absorber for the integrated spacecraft platform,we analyze the targeted energy transfer of the simplified model with nonlinear energy sink using the complex-variables averaging method. Theoretical study shows two quasi-periodic responses that are essentially different in this nonlinear system. The steady-state response which is one of two quasi-periodic responses is caused by the linear instability of system,and another one appears as a result of the nonlinear normal modes between the linear and nonlinear oscillators,resulting from the energy transfer of different oscillators,and it can be used to vibration absorber. Secondly,this paper also discusses the performance of the proposed nonlinear absorber by using the phase portraits. All conclusion derived by the analytic model is verified numerically and the results are consistent with numerical simulations. 展开更多
关键词 nonlinear energy sink targeted energy transfer metal-rubber vibration absorber complex-variables averaging methods
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Applying of Switch Strong Tracking UKF in Spacecraft Autonomous Celestial Navigation 认领 引用
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作者 Jingjing Li Huayi Li Yingchun Zhang 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2015年第1期79-84,共6页
Star & Horizon sensor based autonomous navigation methods play an increasingly important role in spacecraft celestial navigation. However,the measurements of star sensors and horizon sensor are frequently affected... Star & Horizon sensor based autonomous navigation methods play an increasingly important role in spacecraft celestial navigation. However,the measurements of star sensors and horizon sensor are frequently affected by uncertain noises from space environment. To improve the estimation precision,a state estimation algorithm named Switch Strong Tracking Unscented Kalman Filter( SSTUKF) is presented. Firstly,the adaptive fading factor is deduced through the adoption of unknown instrumental diagonal matrixes to real time rectify the measurement covariance matrix. Secondly,according to the deduction of Chebyshev law of large numbers,innovation criterion is introduced during estimation to decrease the unnecessary calculation. Finally,SSTUKF is suggested through the adoption of adaptive fading factor and innovation criterion. The filter can switch between the normal filter mode and adaptive filter mode. As the calculation of innovation criterion is less than the adaptive fading factor,SSTUKF improves the estimation efficiency. To demonstrate the effectiveness,SSTUKF is applied to Star & Horizon sensor based autonomous navigation system with uncertain measurement noises. The simulation results verify the proposed algorithm. 展开更多
关键词 autonomous navigation adaptive filter unscented tr
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Satellite proximate interception vector guidance based on differential games 认领 引用 被引量：21
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作者 Dong YE Mingming SHI Zhaowei SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2018年第6期1352-1361,共10页
This paper studies the proximate satellite interception guidance strategies where both the interceptor and target can perform orbital maneuvers with magnitude limited thrusts. This problem is regarded as a pursuit-eva... This paper studies the proximate satellite interception guidance strategies where both the interceptor and target can perform orbital maneuvers with magnitude limited thrusts. This problem is regarded as a pursuit-evasion game since satellites in both sides will try their best to capture or escape. In this game, the distance of these two players is small enough so that the highly nonlinear earth-centered gravitational dynamics can be reduced to the linear Clohessy-Wiltshire（CW） equations. The system is then simplified by introducing the zero effort miss variables. Saddle solution is formulated for the pursuit-evasion game and time-to-go is estimated similarly as that for the exoatmospheric interception. Then a vector guidance is derived to ensure that the interception can be achieved in the optimal time. The proposed guidance law is validated by numerical simulations. 展开更多
关键词 Differential games Saddle solution Satellite interception Time-to-go estimation Zero effort miss trajectory
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Research on improved integrated FDD/FTC with effectiveness factors 认领 引用 被引量：4
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作者 Xueqin Chen Yuhai Ma +1 位作者 Feng Wang Yunhai Geng 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2012年第5期768-774,共7页
This paper investigates the integrated fault detection and diagnosis（FDD） with fault tolerant control（FTC） method of the control system with recoverable faults.Firstly,a quasi-linear parameter-varying（QLPV） mode... This paper investigates the integrated fault detection and diagnosis（FDD） with fault tolerant control（FTC） method of the control system with recoverable faults.Firstly,a quasi-linear parameter-varying（QLPV） model is set up,in which effectiveness factors are modeled as time-varying parameters to quantify actuators and sensors faults.Based on the certainty equivalency principle,replacing the real time states in the nonlinear term of the QLPV model with the estimated states,the parameters and states can be estimated by a two-stage Kalman filtering algorithm.Then,a polynomial eigenstructure assignment（PEA） controller with time-varying parameters and states is designed to guarantee the performance of the system with recoverable faults.Finally,mathematical simulation is performed to validate the solution in a satellite closed-loop attitude control system,and simulation results show that the solution is fast and effective for on-orbit real-time computation. 展开更多
关键词 fault detection and diagnosis fault tolerant control Kalman filter satellite attitude control
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Predictive control for satellite formation keeping 认领 引用 被引量：5
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作者 He Donglei Cao Xibin 《Journal of Systems Engineering and Electronics》 SCIE EI 2008年第1期161-166,共6页
Based on a Hill equation and a nonlinear equation describing the desired and real dynamics of relative motion separately,a predictive controller is brought forward,which makes the real state track the desired ones to ... Based on a Hill equation and a nonlinear equation describing the desired and real dynamics of relative motion separately,a predictive controller is brought forward,which makes the real state track the desired ones to keep satellite formation.The stability and robustness of the controller are analyzed.Finally,comparing the simulation results of the proposed controller with that of the traditional,proportional-differential controller shows that the former one is capable of keeping the satellite formation more favorably,considering the disturbances such as the J2 perturbations. 展开更多
关键词 predictive control satellites formation low-thrust technology Lyapunov theorem
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Relative navigation for satellite formation flight using a continuous-discrete converted measurement Kalman filter 认领 引用
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作者 雪丹 曹喜滨 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2008年第4期450-454,共5页
The present paper develops an approach of relative orbit determination for satellite formation flight.Inter-satellite measurements by the onboard devices of the satellite were chosen to perform this relative navigatio... The present paper develops an approach of relative orbit determination for satellite formation flight.Inter-satellite measurements by the onboard devices of the satellite were chosen to perform this relative navigation,and the equations of relative motion expressed in the Earth Centered Inertial frame were used to eliminate the assumption of the circular reference orbit.The relative orbit estimation was achieved through a continuous-discrete converted measurement Kalman filter design,in which the measurements were transformed to the inertial frame to avoid the linearization error of the observation equation.In addition,the situation of the coarse measurement period(only microwave radar measurements are available)existing was analyzed.The numerical simulation results verify the validity of the navigation approach,and it has been proved that this approach can be applied to the formation with an elliptical reference orbit. 展开更多
关键词 satellite formation flight relative navigation continuous-discrete converted measurement Kalman filter
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Distributed adaptive prescribed-time orbit containment control for satellite cluster flight 认领 引用 被引量：1
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作者 Tingting ZHANG Shijie ZHANG +1 位作者 Huayi LI Xiangtian ZHAO 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第8期342-357,共16页
The distributed prescribed-time orbit containment control for the satellite cluster flight with multiple dynamic leaders is investigated.The directed information communication topology between followers is taken into ... The distributed prescribed-time orbit containment control for the satellite cluster flight with multiple dynamic leaders is investigated.The directed information communication topology between followers is taken into account in the overall paper.When the satellite mass is assumed to be constant,a distributed prescribed-time orbit containment controller is,firstly,presented to drive the followers into the dynamic convex hull produced by multiple leaders.Then,the parameter uncertainty is considered,and a prescribed-time sliding mode estimator is introduced to estimate the desired velocity of each follower.Based on the estimated state,a novel distributed adaptive prescribed-time orbit containment control scheme is proposed.The Lyapunov stability theory is utilized to prove the prescribed-time stability of the closed-loop system.Finally,several numerical simulations and comparison of different control methods are provided to verify the effectiveness and superiority of the proposed control method. 展开更多
关键词 Satellite cluster Orbit containment control Prescribed-time control Parameter uncertainty Directed communication graph
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Non-cooperative target recognition and relative motion estimation with inertial measurement unit assistance 认领 引用
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作者 Xiangtian ZHAO Shiqiang WANG +2 位作者 Chao ZHANG Shijie ZHANG Yafei ZHAO 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第4期469-483,共15页
This study investigated the problems of non-cooperative target recognition and relative motion estimation during spacecraft rendezvous maneuvers.A structure integrating an Inertial Measurement Unit(IMU)and a visual ca... This study investigated the problems of non-cooperative target recognition and relative motion estimation during spacecraft rendezvous maneuvers.A structure integrating an Inertial Measurement Unit(IMU)and a visual camera was presented.The angular velocity output of the IMU was used to calculate the motion trajectories of star points in multiple image frames,which can highlight the motion of non-cooperative targets with respect to the image background to improve the probability of target recognition.To solve the problem of target misidentification caused by new star points entering the field of view,a target-tracking link based on IMU prediction was introduced to track the position of the target in the image.Furthermore,a measurement model was constructed using the line-of-sight vector generated from target recognition,and the relative motion state was estimated using a Huber-based non-linear filter.Semi-physical and numerical simulations were performed to evaluate the effectiveness and efficiency of the proposed method. 展开更多
关键词 Non-cooperative target Target recognition and tracking Vision/IMU fusion Block matching Robust state estimation
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Demonstration-enhanced policy search for space multi-arm robot collaborative skill learning 认领 引用 被引量：2
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作者 Tian GAO Chengfei YUE +1 位作者 Xiaozhe JU Tao LIN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第3期462-473,共12页
The increasing complexity of on-orbit tasks imposes great demands on the flexible operation of space robotic arms, prompting the development of space robots from single-arm manipulation to multi-arm collaboration. In ... The increasing complexity of on-orbit tasks imposes great demands on the flexible operation of space robotic arms, prompting the development of space robots from single-arm manipulation to multi-arm collaboration. In this paper, a combined approach of Learning from Demonstration (LfD) and Reinforcement Learning (RL) is proposed for space multi-arm collaborative skill learning. The combination effectively resolves the trade-off between learning efficiency and feasible solution in LfD, as well as the time-consuming pursuit of the optimal solution in RL. With the prior knowledge of LfD, space robotic arms can achieve efficient guided learning in high-dimensional state-action space. Specifically, an LfD approach with Probabilistic Movement Primitives (ProMP) is firstly utilized to encode and reproduce the demonstration actions, generating a distribution as the initialization of policy. Then in the RL stage, a Relative Entropy Policy Search (REPS) algorithm modified in continuous state-action space is employed for further policy improvement. More importantly, the learned behaviors can maintain and reflect the characteristics of demonstrations. In addition, a series of supplementary policy search mechanisms are designed to accelerate the exploration process. The effectiveness of the proposed method has been verified both theoretically and experimentally. Moreover, comparisons with state-of-the-art methods have confirmed the outperformance of the approach. 展开更多
关键词 Space multi-arm collaboration Demonstrations .Reinforcement Learning Probabilistic Movement Primitives Relative Entropy Policy Search Policy search mechanism
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A novel two-stage extended Kalman filter algorithm for reaction flywheels fault estimation 认领 引用 被引量：10
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作者 Chen Xueqin Sun Rui +2 位作者 Jiang Wancheng Jia Qingxian Zhang Jinxiu 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2016年第2期462-469,共8页
This paper investigates the problem of two-stage extended Kalman filter （TSEKF）-based fault estimation for reaction flywheels in satellite attitude control systems （ACSs）. Firstly, based on the separate-bias princ... This paper investigates the problem of two-stage extended Kalman filter （TSEKF）-based fault estimation for reaction flywheels in satellite attitude control systems （ACSs）. Firstly, based on the separate-bias principle, a satellite ACSs with actuator fault is transformed into an augmented nonlinear discrete stochastic model; then, a novel TSEKF is suggested such that it can simultane- ously estimate satellite attitude information and actuator faults no matter they are additive or mul- tiplicative; finally, the proposed approach is respectively applied to estimating bias faults and loss of effectiveness for reaction flywheels in satellite ACSs, and simulation results demonstrate the effec- tiveness of the proposed fault estimation approach. 展开更多
关键词 Fault estimation Reaction flywheels Satellite attitude control sys-tems Separate-bias principle Two-stage extended Kalmanfilter
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