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Nonlinear hierarchy-structured predictive control design for a generic hypersonic vehicle

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Science China(Technological Sciences) 2013年第8期56卷 2025-2036页

作者： WANG Peng TANG GuoJian liu luhua WU Jie College of Aerospace Science and Engineering National University of Defense Technology

A hierarchy-structured predictive controller is designed and analyzed for rotation motion dynamics of a generic hypersonic vehicle(GHV).This vehicle model has fast variability,is highly nonlinear,and includes uncertain *** controller contains two subsystems,the inner-fast-loop nonlinear generable predictive controller(NGPC)and the outer-slow-loop NGPC,both of which are designed by the closed-form optimal generable predictive control ***,the heavy on-line computational burden in the classical predictive control method is *** hierarchy structure of the control system decreases the relative degree of each subsystem and helps increase the dynamic response speed of the attitude *** order to improve the robustness of the control system,a feedback correction algorithm is proposed that corrects the calculation error between the predictive model and the real dynamic *** studies are conducted for the trimmed cruise conditions of an altitude of 33.5 km and Mach 15 to investigate the responses of the vehicle to the step commands of angle of attack,sideslip angle,and bank *** simulation studies demonstrate that the proposed controller is robust with respect to the parametric uncertainties and atmospheric disturbance,and meets the performance requirements of GHV with acceptable control inputs.

关键词： generic hypersonic vehicle flight control predictive control hierarchy-structured robustness

Three-dimensional nonlinear coupling guidance for hypersonic vehicle in dive phase

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Science China(Technological Sciences) 2014年第9期57卷 1824-1833页

作者： ZHU JianWen liu luhua TANG GuoJian BAO WeiMin College of Aerospace Science and Engineering National University of Defense Technology China Aerospace Science and Technology Corporation

Three-dimensional(3D)nonlinear diving guidance strategy considering the coupling between longitudinal and lateral motions for hypersonic vehicle is investigated in this *** constructs the complete nonlinear coupling motion equation without any approximations based on diving relative motion relationship directly,and converts it into linear state space equation with the same relative degree by feedback *** the linear equation,slide mode control with strong robustness is employed to design the guidance law,and 3D diving guidance law which can satisfy terminal impact point and falling angle constraints with high precision is obtained by substituting the previous control law into the origin nonlinear guidance ***,regarding lateral overload as the standard,hybrid control strategy which can take full advantage of the excellent characters of both bank-to-turn(BTT)and skid-to-turn(STT)controls is designed to improve the guidance accuracy ***,the results of CAV-H vehicle guidance test show that the algorithm can realize high accuracy guidance even if serious motion coupling exists,and has strong robustness to the path disturbances and navigation errors as well.

关键词： hypersonic vehicle 3D diving guidance coupling feedback linearization slide mode control hybrid control strategy

Rapid Generation of Boost Trajectory for Boost-Glide Missile 36

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Rapid Generation of Boost Trajectory for Boost-Glide Missile

Footprint Determination for Entry Vehicles Based on Three-Dimensional Acceleration Profile 36

第36届中国控制会议

作者： Peijun Zhang Ruizhi He luhua liu Guojian Tang College of Aerospace Science and Engineering National University of Defense Technology

ISBN: (纸本)9781538629185

A rapid boost trajectory generation algorithm is presented in this paper,considering the new requirements of hypersonic boost-glide missiles,such as the low terminal altitude,high velocity,and wide range *** algorithm divides the boost trajectory into the longitudinal and lateral *** the longitudinal sub-plane,the angle of pitch is designed as the time segment *** maximum angle of attack and the pitch rate are selected as the key parameters to be *** iteration scheme is used to calculate the key parameters,according to the strict terminal altitude and velocity *** the lateral sub-plane,an analytical calculation of the azimuth angle is proposed based on the theory of spherical triangle,which guarantees an initial aiming at the preselected ***,new boost modes,such as intermittent boost mode and low altitude direct boost mode,are *** trajectory characteristics and the application prospect are deeply ***,a three-stage solid rocket is used in the *** results demonstrate that the algorithm can rapidly generate the boost trajectory for hypersonic boost-glide missile and achieve complex flight missions.

关键词： Boost-glide Missile Boost Phase Trajectory Generation Newton Iteration

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Footprint Determination for Entry Vehicles Based on Three-Di...

Chaotification Method for the Glide Midcourse Trajectory

第36届中国控制会议

作者： Ruizhi He luhua liu Guojian Tang Weimin Bao College of Aerospace Science and Engineering National University of Defense Technology China Aerospace Science and Technology Corporation

ISBN: (纸本)9781538629185

In this paper,a footprint determination algorithm for entry vehicles based on three-dimensional acceleration profile is proposed,which solves the problem of fast determination of the entry coverage with complex *** aerodynamic adjustment capability is greatly improved since both the angle of attack and bank are regarded as primary variables,and in this way larger entry footprint is ***,due to the introduction of quasi-equilibrium glide condition（QEGC）,the altitude of the entry trajectory changes smoothly without ***,based on the QEGC,a new type of longitudinal acceleration corridor and lateral lift to drag corridor are designed,and the profiles are chose as the interpolation results of the upper and lower ***,based on PID theory,a three-dimensional profile tracker is designed to realize the corresponding entry ***,the traversal of the interpolation parameters in the corridors is carried out,and the entry footprint satisfying various complex constraints is *** approach is tested using Common Aero Vehicle-H model,and the results demonstrate that the proposed algorithm can determinate the footprint of entry vehicles rapidly while satisfying all the path and terminal constraints.

关键词： entry vehicles footprint determination three-dimensional profile QEGC adjustable angle of attack

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Journal of Harbin Institute of Technology(New series) 2024年

作者： Fangzhen liu luhua liu Chao Ou School of Aeronautics and Astronautics Sun Yat-Sen University Shenzhen Key Laboratory of Intelligent Microsatellite Constellation School of Aeronautics and Astronautics Huazhong University of Science and Technology China Aerodynamics Research and Development Center

In order to enhance the penetration performance of hypersonic gliding vehicle,a chaotification method of gliding midcourse based on flight dynamics is proposed. Firstly,a chaotic series-based angle of attack(AOA)control algorithm and an AOA switching control algorithm considering flight altitude are proposed in this study based on a simple chaotic system with considerations of AOA constraints and process constraints. Secondly,the Lyapunov exponent algorithm of continuous system is applied to verify the chaotic characteristic of flight trajectories. Thirdly,a stability region analysis method is proposed based on a conservative dynamics,which can be applied to the stability region analysis of general complex dynamics. Finally,the simulations show that both control algorithms can realize the chaotification of trajectories,and the flight trajectories obtained by the AOA switching control algorithm are feasible.

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临近空间飞行器纵向逆控制系统设计

国防科技大学学报 2012年第3期34卷 29-32,37页

作者：王鹏刘鲁华吴杰国防科技大学航天与材料工程学院湖南长沙410073

建立了临近空间飞行器无动力滑翔阶段的纵向运动模型,并应用动态逆方法推导了模型的逆系统。系统相对阶等于绕质心运动模型的系统阶数,实现了绕质心运动模型的线性化。为了克服纵向运动模型的隐动态和参数的不确定性,在内环动态逆控制... 详细信息

建立了临近空间飞行器无动力滑翔阶段的纵向运动模型,并应用动态逆方法推导了模型的逆系统。系统相对阶等于绕质心运动模型的系统阶数,实现了绕质心运动模型的线性化。为了克服纵向运动模型的隐动态和参数的不确定性,在内环动态逆控制器的基础上,设计了外环最优调节器。仿真结果表明:飞行器纵向逆控制系统可以准确跟踪俯仰角或攻角指令,并对参数不确定性和外界干扰具有较好的鲁棒性,具有工程适用性。

关键词：临近空间滑翔纵向模型动态逆最优控制鲁棒性

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一种统计意义下最优接近轨道快速搜索算法

中国空间科学技术 2006年第4期26卷 26-31页

作者：刘鲁华郑伟汤国建国防科学技术大学航天与材料工程学院长沙410073

设计空间监视卫星时,需要分析设计卫星与大量被监视空间飞行器的接近能力。通过具体仿真实例提出了一种基于摄动模型的快速最优接近轨道搜索方法,可以大大提高仿真速度,仿真结果证实了该方法的有效性,统计参数通过了精确模型的确认,也... 详细信息

设计空间监视卫星时,需要分析设计卫星与大量被监视空间飞行器的接近能力。通过具体仿真实例提出了一种基于摄动模型的快速最优接近轨道搜索方法,可以大大提高仿真速度,仿真结果证实了该方法的有效性,统计参数通过了精确模型的确认,也验证了算法的可信性。

关键词：航天监视卫星轨道搜索算法

带有模糊干扰观测器的高超声速飞行器一体化制导控制方法

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国防科技大学学报 2016年第5期38卷 86-93页

作者：赵暾王鹏刘鲁华吴杰国防科技大学航天科学与工程学院湖南长沙410073

为充分利用高超声速飞行器在俯冲段的质心运动与绕质心运动之间的耦合作用和飞行过程中的不确定性,基于模糊干扰观测器提出三维一体化制导与控制问题。根据飞行器的动力学方程以及飞行器-目标的视线角相对运动方程,推导出适用于倾斜转... 详细信息

为充分利用高超声速飞行器在俯冲段的质心运动与绕质心运动之间的耦合作用和飞行过程中的不确定性,基于模糊干扰观测器提出三维一体化制导与控制问题。根据飞行器的动力学方程以及飞行器-目标的视线角相对运动方程,推导出适用于倾斜转弯控制的一体化制导控制模型。针对模型中的不确定性采用模糊干扰观测器进行补偿,并使用块动态面方法设计一种一体化制导控制律。通过选取适当的李雅普诺夫函数证明闭环系统状态的一致毕竟有界性。仿真结果验证了该一体化制导控制方法的有效性和鲁棒性。

关键词：高超声速飞行器模糊干扰观测器一体化制导控制块动态面反演控制

无配体参与的铱催化的苄位二级碳氢键的硼化反应

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有机化学 2021年第4期41卷 1572-1581页

作者：刘路华杜荣荣徐森苗中国科学院兰州化学物理研究所羰基合成与选择氧化国家重点实验室兰州730000 中国科学院大学北京100049

报道了无外加配体参与的以吡唑作为导向基团的铱催化的sp^(3)碳氢键的区域选择性硼化反应.在催化量的[Ir(OMe)(cod)]_(2)存在下,该反应能够顺利地将苄位的二级碳氢键转化成碳硼键.该反应具有非常广谱的官能团兼容性,能够以良好到优秀的... 详细信息

报道了无外加配体参与的以吡唑作为导向基团的铱催化的sp^(3)碳氢键的区域选择性硼化反应.在催化量的[Ir(OMe)(cod)]_(2)存在下,该反应能够顺利地将苄位的二级碳氢键转化成碳硼键.该反应具有非常广谱的官能团兼容性,能够以良好到优秀的产率生成相应的产物.此外,导向基团吡唑能够通过臭氧接转化成酰胺.

关键词：碳氢键活化铱合成方法硼化