现代航天器通常携带大量的液体推进剂,在轨运行时推进剂的消耗将导致等效模型参数的改变.为了获取准确的等效模型参数并将其引入GNC(guidance,navigation and control)系统闭环控制,提高航天器的姿态控制精度,文章提出一种基于平方根容...现代航天器通常携带大量的液体推进剂,在轨运行时推进剂的消耗将导致等效模型参数的改变.为了获取准确的等效模型参数并将其引入GNC(guidance,navigation and control)系统闭环控制,提高航天器的姿态控制精度,文章提出一种基于平方根容积卡尔曼滤波(SR-CKF)的等效模型参数在轨辨识策略.首先,为了建立适用于金属膜片贮箱的等效模型,在等效球摆模型的悬挂点施加扭簧-阻尼器以等效金属膜片对推进剂的刚度-阻尼效应,并借助Kane方法建立了航天器刚-液耦合动力学方程.其次,针对状态反馈反步控制器中等效模型参数未知的情形,提出一种基于SR-CKF的等效模型参数在轨辨识策略.该策略可在航天器完成一次大角度姿态机动任务的同时,根据星载角速度计数据在线辨识出等效模型的各项参数以及贮箱内推进剂的剩余量,并预测出推进剂的分布运动状态.最后,数值仿真结果表明了提出的在轨辨识策略的有效性和必要性.文章的工作对于航天器GNC系统中等效模型的校准迭代、研究推进剂在轨晃动行为及预测航天器服役年限具有重要参考价值.展开更多
The displacement feedback with time delay considered is introduced in order to enhance the vibration isolation performance of a high-static-low-dynamic stiffness(HSLDS) vibration isolator. Such feedback is detailedly ...The displacement feedback with time delay considered is introduced in order to enhance the vibration isolation performance of a high-static-low-dynamic stiffness(HSLDS) vibration isolator. Such feedback is detailedly analyzed from the viewpoint of equivalent damping. Firstly, the primary resonance of the controlled HSLDS vibration isolator subjected to a harmonic force excitation is obtained based on the multiple scales method and further verified by numerical integration. The stability of the primary resonance is subsequently investigated. Then, the equivalent damping is defined to study the effects of feedback gain and time delay on primary resonance. The condition of jump avoidance is obtained with the purpose of eliminating the adverse effects induced by jumps. Finally, the force transmissibility of the controlled HSLDS vibration isolator is defined to evaluate its isolation performance. It is shown that an appropriate choice of feedback parameters can effectively suppress the force transmissibility in resonant region and reduce the resonance frequency. Furthermore, a wider vibration isolation frequency bandwidth can be achieved compared to the passive HSLDS vibration isolator.展开更多
In the paper, the problem of H∞ decentralized state feedback control for largescale systems is described. An algorithm is proposed which uses the method of a feasible direction matrix. The algorithm only requires the...In the paper, the problem of H∞ decentralized state feedback control for largescale systems is described. An algorithm is proposed which uses the method of a feasible direction matrix. The algorithm only requires the solution of an algebraic Riccati equation (ARE) and makes the H∞norm of the closedloop transfer function matrix from disturbance inputs to controlled outputs less than a given constant which ensure the stability of the overall controlled system at each iteration. The given example shows that the convergence of the algorithm is satisfactory.展开更多
The problem of global stabilization by state feedback for a class of time-delay nonlinear system is considered. By constructing the appropriate Lyapunov-Krasovskii functionals (LKF) and using the backstepping design, ...The problem of global stabilization by state feedback for a class of time-delay nonlinear system is considered. By constructing the appropriate Lyapunov-Krasovskii functionals (LKF) and using the backstepping design, a linear state feedback controller making the closed-loop system globally asymptotically stable is constructed.展开更多
It is a complicated nonlinear controlling problem to conduct a two-dimensional trajectory correction of rockets.By establishing the aerodynamic correction force mathematical model of rockets on nose cone swinging,the ...It is a complicated nonlinear controlling problem to conduct a two-dimensional trajectory correction of rockets.By establishing the aerodynamic correction force mathematical model of rockets on nose cone swinging,the linear control is realized by the dynamic inverse nonlinear controlling theory and the three-time-scale separation method.The control ability and the simulation results are also tested and verified.The results show that the output responses of system track the expected curve well and the error is controlled in a given margin.The maximum correction is about±314 m in the lengthwise direction and±1 212 m in the crosswise direction from the moment of 5 s to the drop-point time when the angle of fire is 55°.Thus,based on the dynamic inverse control of feedback linearization,the trajectory correction capability of nose cone swinging can satisfy the requirements of two-dimensional ballistic correction,and the validity and effectiveness of the method are proved.展开更多
研究了n比特随机量子系统实时状态估计及其反馈控制的问题.对于连续弱测量(Continuous weak measurement, CWM)过程存在高斯噪声的情况,基于在线交替方向乘子法(Online alternating direction multiplier method,OADM)推导出一种适用于...研究了n比特随机量子系统实时状态估计及其反馈控制的问题.对于连续弱测量(Continuous weak measurement, CWM)过程存在高斯噪声的情况,基于在线交替方向乘子法(Online alternating direction multiplier method,OADM)推导出一种适用于n比特随机量子系统的实时量子状态估计算法,即QSE-OADM (Quantum state estimation based on OADM).运用李雅普诺夫方法设计控制律,实现基于实时量子状态估计的反馈控制,并证明所提控制律的收敛性.以2比特随机量子系统为例进行数值仿真实验,通过与基于QST-OADM (Quantum state tomography based on OADM)算法和OPG-ADMM (Online proximal gradient-based alternating direction method of multipliers)算法的量子反馈控制方案的性能对比,验证了所提控制方案的优越性.展开更多
文摘现代航天器通常携带大量的液体推进剂,在轨运行时推进剂的消耗将导致等效模型参数的改变.为了获取准确的等效模型参数并将其引入GNC(guidance,navigation and control)系统闭环控制,提高航天器的姿态控制精度,文章提出一种基于平方根容积卡尔曼滤波(SR-CKF)的等效模型参数在轨辨识策略.首先,为了建立适用于金属膜片贮箱的等效模型,在等效球摆模型的悬挂点施加扭簧-阻尼器以等效金属膜片对推进剂的刚度-阻尼效应,并借助Kane方法建立了航天器刚-液耦合动力学方程.其次,针对状态反馈反步控制器中等效模型参数未知的情形,提出一种基于SR-CKF的等效模型参数在轨辨识策略.该策略可在航天器完成一次大角度姿态机动任务的同时,根据星载角速度计数据在线辨识出等效模型的各项参数以及贮箱内推进剂的剩余量,并预测出推进剂的分布运动状态.最后,数值仿真结果表明了提出的在轨辨识策略的有效性和必要性.文章的工作对于航天器GNC系统中等效模型的校准迭代、研究推进剂在轨晃动行为及预测航天器服役年限具有重要参考价值.
基金Project(KYLX15_0256)supported by the Funding of Jiangsu Innovation Program for Graduate Education,ChinaProject(SV2015-KF-01)supported by the Open Project of State Key Laboratory for Strength and Vibration of Mechanical Structures,ChinaProject(XZA15003)supported by the Fundamental Research Funds for the Central Universities,China
文摘The displacement feedback with time delay considered is introduced in order to enhance the vibration isolation performance of a high-static-low-dynamic stiffness(HSLDS) vibration isolator. Such feedback is detailedly analyzed from the viewpoint of equivalent damping. Firstly, the primary resonance of the controlled HSLDS vibration isolator subjected to a harmonic force excitation is obtained based on the multiple scales method and further verified by numerical integration. The stability of the primary resonance is subsequently investigated. Then, the equivalent damping is defined to study the effects of feedback gain and time delay on primary resonance. The condition of jump avoidance is obtained with the purpose of eliminating the adverse effects induced by jumps. Finally, the force transmissibility of the controlled HSLDS vibration isolator is defined to evaluate its isolation performance. It is shown that an appropriate choice of feedback parameters can effectively suppress the force transmissibility in resonant region and reduce the resonance frequency. Furthermore, a wider vibration isolation frequency bandwidth can be achieved compared to the passive HSLDS vibration isolator.
基金theNational+4 种基金 Natural Science Foundation of China
文摘In the paper, the problem of H∞ decentralized state feedback control for largescale systems is described. An algorithm is proposed which uses the method of a feasible direction matrix. The algorithm only requires the solution of an algebraic Riccati equation (ARE) and makes the H∞norm of the closedloop transfer function matrix from disturbance inputs to controlled outputs less than a given constant which ensure the stability of the overall controlled system at each iteration. The given example shows that the convergence of the algorithm is satisfactory.
基金Supported by the "973" Project of P. R. China (G1998020300)
文摘The problem of global stabilization by state feedback for a class of time-delay nonlinear system is considered. By constructing the appropriate Lyapunov-Krasovskii functionals (LKF) and using the backstepping design, a linear state feedback controller making the closed-loop system globally asymptotically stable is constructed.
基金Project(9140A05030109HK01)supported by Equipment Pre-research Foundation,China
文摘It is a complicated nonlinear controlling problem to conduct a two-dimensional trajectory correction of rockets.By establishing the aerodynamic correction force mathematical model of rockets on nose cone swinging,the linear control is realized by the dynamic inverse nonlinear controlling theory and the three-time-scale separation method.The control ability and the simulation results are also tested and verified.The results show that the output responses of system track the expected curve well and the error is controlled in a given margin.The maximum correction is about±314 m in the lengthwise direction and±1 212 m in the crosswise direction from the moment of 5 s to the drop-point time when the angle of fire is 55°.Thus,based on the dynamic inverse control of feedback linearization,the trajectory correction capability of nose cone swinging can satisfy the requirements of two-dimensional ballistic correction,and the validity and effectiveness of the method are proved.
文摘研究了n比特随机量子系统实时状态估计及其反馈控制的问题.对于连续弱测量(Continuous weak measurement, CWM)过程存在高斯噪声的情况,基于在线交替方向乘子法(Online alternating direction multiplier method,OADM)推导出一种适用于n比特随机量子系统的实时量子状态估计算法,即QSE-OADM (Quantum state estimation based on OADM).运用李雅普诺夫方法设计控制律,实现基于实时量子状态估计的反馈控制,并证明所提控制律的收敛性.以2比特随机量子系统为例进行数值仿真实验,通过与基于QST-OADM (Quantum state tomography based on OADM)算法和OPG-ADMM (Online proximal gradient-based alternating direction method of multipliers)算法的量子反馈控制方案的性能对比,验证了所提控制方案的优越性.
