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New three-dimensional guidance law for BTT missiles based on differential geometry and Lie-group

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Journal of Systems Engineering and Electronics 2011年第4期22卷 684-690页

作者： Shuangchun Peng Liang Pan Tianjiang Hu Lincheng Shen College of Mechatronic Engineering and Automation National University of Defense Technology Changsha 410073 P. R. China

A new non-decoupling three-dimensional guidance law is proposed for bank-to-turn （BTT） missiles with the motion coupling problem. In this method, the different geometry is taken for theoretically modeling on B-IT missiles＇ motion within the threedimensional style without information loss, and meanwhile, Liegroup is utilized to describe the line-of-sight （LOS） azimuth when the terminal angular constraints are considered. Under these cir- cumstances, a guidance kinematics model is established based on differential geometry. Then, corresponding to no terminal angular constraint and terminal angular constraints, guidance laws are re- spectively designed by using proportional control and generalized proportional-derivative （PD） control in SO（3） group. Eventually, simulation results validate that this developed method can effectively avoid the complexity of pure Lie-group method and the information loss of the traditional decoupling method as well.

关键词： three-dimensional guidance law differential geometry,Lie-group control bank-to-turn (BTT).

three-dimensional suboptimal guidance law for fly-over and shoot-down smart ammunition via virtual target

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Journal of Beijing Institute of Technology 2014年第4期23卷 443-451页

作者：杨喆吴炎烜范宁军王正杰 National Key Laboratory of Science and Technology on Electro-mechanical Dynamic Control School of Mechatronic EngineeringBeijing Institute of Technology

An optimal burst height is required for the fly-over and shoot-down smart ammunition with an EFP warhead at the instant of explosion which brings a special requirement to the miss distance of the terminal guidance law. In this paper, a guidance law based on the virtual target scheme is proposed. First, the practical pursuit-evasion issue between the ammunition and the target with specific miss distance is transformed into a virtuai pursuit-evasion problem with zero miss distance. Secondly, a complete three-dimensional pursuit-evasion kinematics model is established without any simplifications. And then, a suboptimal guidance law is designed based on the θ-D method which has constraints of the elevation and azimuth angular velocity of the virtual line of sight （LOS）. Finally, in order to verify the performance of the proposed guidance law, three test cases are conducted. Numericai results show that under the proposed terminal guidance law, the smart ammunition not only can fly above the target with an optimal burst height but also have a smaller normal acceleration on the terminal trajectory.

关键词： three-dimensional guidance law virtual target fly-over and shoot-down θ-D method

three-dimensional adaptive finite-time guidance law for intercepting maneuvering targets

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Chinese Journal of Aeronautics 2017年第6期30卷 1985-2003页

作者： Yujie SI Shenmin SONG Center for Control Theory and guidance Technology Harbin Institute of Technology Harbin 150001 China

To intercept maneuvering targets at desired impact angles, a three-dimensional terminal guidance problem is investigated in this study. Because of a short terminal guidance time, a finitetime impact angle control guidance law is developed using the fast nonsingular terminal sliding mode control theory. However, the guidance law requires the upper bound of lumped uncertainty including target acceleration, which may not be accurately obtained. Therefore, by adopting a novel reaching law, an adaptive sliding mode guidance law is provided to release the drawback. At the same time, this method can accelerate the convergence rate and weaken the chattering phenomenon to a certain extent. In addition, another novel adaptive guidance law is also derived; this ensures systems asymptotic and finite-time stability without the knowledge of perturbations *** simulations have demonstrated that all the three guidance laws have effective performances and outperform the traditional terminal guidance laws.

关键词： Adaptive control Finite-time guidance law Impact angle Sliding mode control three-dimensional guidance law

three-dimensional nonlinear H_2/H_∞ guidance law based upon approach of solving the state feedback Nash balance point

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Journal of Harbin Institute of Technology(New Series) 2010年第3期17卷 383-388页

作者：桑保华姜长生 College of Aviation Technology Nanjing University of Aeronautics and Astronautics Dept. of Automation Engineering Nanjing University of Aeronautics and Astronautics

Based upon the theory of the nonlinear quadric two-person nonzero-sum differential game,the fact that the time-limited mixed H2/H∞ control problem can be turned into the problem of solving the state feedback Nash balance point is mentioned. Upon this,a theorem about the solution of the state feedback control is given,the Lyapunov stabilization of the nonlinear system under this control is proved,too. At the same time,this solution is used to design the nonlinear H2/H∞ guidance law of the relative motion between the missile and the target in three-dimensional(3D) space. By solving two coupled Hamilton-Jacobi partial differential inequalities(HJPDI),a control with more robust stabilities and more robust performances is obtained. With different H∞ performance indexes,the correlative weighting factors of the control are analytically designed. At last,simulations under different robust performance indexes and under different initial conditions and under the cases of intercepting different maneuvering targets are carried out. All results indicate that the designed law is valid.

关键词： nonlinear system,mixed H2/H∞ control state feedback Nash balance point two-person nonzero-sum differential game three-dimensional guidance law

three-dimensional Finite-time guidance law with impact angle constraints 36

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Three-dimensional Finite-time guidance Law with impact angle...