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Line-of-sight rates extraction of roll-pitch seeker under anti-infrared decoy state

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Journal of Systems Engineering and Electronics 2021年第1期32卷 178-196页

作者： LI Yue HE Lei xia qunli School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Sichuan Institute of Aerospace Systems Engineering Chengdu 610100China

In this paper,the method of extracting guidance information such as the line-of-sight(LOS)rates under the anti-infrared decoy state for the roll-pitch seeker is *** systems which are used to describe the angles transform are *** LOS angles reconstruction model of the roll-pitch seeker in inertial space is established.A Kalman filter model for extracting LOS rates of the roll-pitch seeker is *** this model,the target performs constant acceleration(CA)model *** error model of LOS rates extraction under infrared decoy state is *** existing methods of extracting LOS rates under anti-infrared decoy state are listed in this *** from the existing methods,a novel method that uses extrapolated values of target accelerations as filter measurements is proposed to solve the guidance information extraction problem under the anti-infrared decoy *** simulations are conducted to verify the effectiveness of the proposed method under different target maneuvering models such as the CA model,the CA extended model and the singer *** simulation results show that the proposed method of extracting guidance information such as LOS rates for the rollpitch seeker under the anti-infrared decoy state is effective.

关键词： line-of-sight(LOS)rate extraction roll-pitch seeker anti-infrared decoy Kalman filter target maneuver

Study of trajectory optimization using terminal-node adaptive-altered spline algorithm

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Journal of Systems Engineering and Electronics 2009年第3期20卷 551-557页

作者： xia qunli Guo Tao Qi Zaikang School of Aerospace Science and Engineering Beijing Inst. of Technology Beijing 100081 P. R. China

The advantage of using a spline function to evaluate the trajectory parameters optimization is discussed. A new method that using adaptive varied terminal-node spline interpolation for solving trajectory optimization is proposed. And it is validated in optimizing the trajectory of guided bombs and extended range guided munitions （ERGM）. The solutions are approximate to the real optimization results. The advantage of this arithmetic is that it can be used to solve the trajectory optimization with complex models. Thus, it is helpful for solving the practical engineering optimization problem.

关键词： trajectory optimization optimization control parameter optimization spline interpolation

An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

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Journal of Systems Engineering and Electronics 2020年第1期31卷 168-184页

作者： ZHANG Wenjie FU Shengnan LI Wei xia qunli School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China School of Mechatronical Engineering Beijing Institute of TechnologyBeijing 100081China

An integral sliding mode guidance law(ISMGL)combined with the advantages of the integral sliding mode control(SMC)method is designed to address maneuvering target interception problems with impact angle *** relative motion equation of the missile and the target considering the impact angle constraint is established in the longitudinal plane,and an integral sliding mode surface is *** proposed guidance law resolves the existence of a steady-state error problem in the traditional *** a guidance law ensures that the missile hits the target with an ideal impact angle in finite time and the missile is kept highly robust throughout the interception *** adopting the dynamic surface control method,the ISMGL is designed considering the impact angle constraints and the autopilot dynamic *** to the Lyapunov stability theorem,all states of the closed-loop system are finally proven to be uniformly *** results are compared with the general sliding mode guidance law and the trajectory shaping guidance law,and the findings verify the effectiveness and superiority of the ISMGL.

关键词： impact angle constraint integral sliding mode maneuvering target Lyapunov stability dynamic characteristic

Extended optimal guidance law with impact angle and acceleration constriants

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Journal of Systems Engineering and Electronics 2014年第5期25卷 868-876页

作者： Ran Li qunli xia Qiuqiu Wen Department of Aerospace Beijing Institute of Technology China North Industries Group Corporation

The extended optima straints of miss distance and Schwartz inequality. To reduce guidance law with terminal conmpact angle is derived by the terminal acceleration and eliminate gravity disturbance absolutely, the object function, which designs the weight of control command to be the power function of time-to-go＇s reciprocal, is given. And the gravity is considered when building the state equation. Based on the parsing express of the guidance command change with varying time and adjoint system analysis method, the command characteristics and the non-dimensional miss distance of the guidance law are analyzed, a design principle of guidance order coefficients is discussed. Finally, based on the requirement of engineering, the method to calculate the guidance condition and maximal required acceleration of the guidance law is given. The simulation demonstrates that not only the guidance law can satisfy the terminal position and impact angle constraints, but also the terminal acceleration can be converged toward zero, which will support a good situation for the terminal angle of attacking control.

关键词： impact angle constraint optimal guidance law accel- eration command guidance order.

Robust missile autopilot design based on dynamic surface control

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Journal of Systems Engineering and Electronics 2023年第1期34卷 160-171页

作者： ZHOU Jianping LI Wei xia qunli JIANG Huan School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China

Since the dynamical system and control system of the missile are typically nonlinear, an effective acceleration tracking autopilot is designed using the dynamic surface control(DSC)technique in order to make the missile control system more robust despite the uncertainty of the dynamical parameters and the presence of disturbances. Firstly, the nonlinear mathematical model of the tail-controlled missile is decomposed into slow acceleration dynamics and fast pitch rate dynamics based on the naturally existing time scale separation. Secondly, the controller based on DSC is designed after obtaining the linear dynamics characteristics of the slow and fast subsystems. An extended state observer is used to detect the uncertainty of the system state variables and aerodynamic parameters to achieve the compensation of the control law. The closed-loop stability of the controller is derived and rigorously analyzed. Finally, the effectiveness and robustness of the design is verified by Monte Carlo simulation considering different initial conditions and parameter uptake. Simulation results illustrate that the missile autopilot based DSC controller achieves better performance and robustness than the other two well-known *** method proposed in this paper is applied to the design of a missile autopilot, and the results show that the acceleration tracking autopilot based on the DSC controller can ensure accurate tracking of the required commands and has better performance.

关键词： acceleration autopilot nonlinear missile dynamics time-scale separation extended state observer dynamic surface control(DSC)

Multiconstraint adaptive three-dimensional guidance law using convex optimization

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Journal of Systems Engineering and Electronics 2020年第4期31卷 791-803页

作者： FU Shengnan LIU xiaodong ZHANG Wenjie xia qunli School of Mechatronical Engineering Beijing Institute of TechnologyBeijing 100081China Beijing Aerospace Automatic Control Institute Beijing 100854China School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China

The traditional guidance law only guarantees the accuracy of attacking a target. However, the look angle and acceleration constraints are indispensable in applications. A new adaptive three-dimensional proportional navigation(PN) guidance law is proposed based on convex optimization. Decomposition of the three-dimensional space is carried out to establish threedimensional kinematic engagements. The constraints and the performance index are disposed by using the convex optimization method. PN guidance gains can be obtained by solving the optimization problem. This solution is more rapid and programmatic than the traditional method and provides a foundation for future online guidance methods, which is of great value for engineering applications.

关键词： proportional navigation(PN) adaptive guidance law three-dimensional space second-order cone programming(SOCP) convex optimal control

Multiple-constraint cooperative guidance based on two-stage sequential convex programming

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Chinese Journal of Aeronautics 2020年第1期33卷 296-307页

作者： Wei DONG Qiuqiu WEN qunli xia Shengjiang YANG School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Beijing Aerospace Technology Institute Beijing 100074China

An improved approach is presented in this paper to implement highly constrained cooperative guidance to attack a stationary *** problem with time-varying Proportional Navigation(PN)gain is first formulated as a nonlinear optimal control problem,which is difficult to solve due to the existence of nonlinear kinematics and nonconvex *** convexification treatments and discretization,the solution to the original problem can be approximately obtained by solving a sequence of Second-Order Cone Programming(SOCP)problems,which can be readily solved by state-of-the-art Interior-Point Methods(IPMs).To mitigate the sensibility of the algorithm on the user-provided initial profile,a Two-Stage Sequential Convex Programming(TSSCP)method is presented in ***,numerical simulations under different mission scenarios are conducted to show the superiority of the proposed method in solving the cooperative guidance *** research indicated that the TSSCP method is more tractable and reliable than the traditional methods and has great potential for real-time processing and on-board implementation.

关键词： Convex optimization Cooperative guidance Guidance Multiple constraints Second-order cone programming Sequential convex programming

Deep reinforcement learning and its application in autonomous fitting optimization for attack areas of UCAVs

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Journal of Systems Engineering and Electronics 2020年第4期31卷 734-742页

作者： LI Yue QIU xiaohui LIU xiaodong xia qunli School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Science and Technology on Electro-Optic Control Laboratory Luoyang 471000China Beijing Aerospace Automatic Control Research Institute Beijing 100854China

The ever-changing battlefield environment requires the use of robust and adaptive technologies integrated into a reliable platform. Unmanned combat aerial vehicles(UCAVs) aim to integrate such advanced technologies while increasing the tactical capabilities of combat aircraft. As a research object, common UCAV uses the neural network fitting strategy to obtain values of attack areas. However, this simple strategy cannot cope with complex environmental changes and autonomously optimize decision-making problems. To solve the problem, this paper proposes a new deep deterministic policy gradient(DDPG) strategy based on deep reinforcement learning for the attack area fitting of UCAVs in the future battlefield. Simulation results show that the autonomy and environmental adaptability of UCAVs in the future battlefield will be improved based on the new DDPG algorithm and the training process converges quickly. We can obtain the optimal values of attack areas in real time during the whole flight with the well-trained deep network.

关键词： attack area neural network deep deterministic policy gradient(DDPG) unmanned combat aerial vehicle(UCAV)

Impact time control using biased proportional navigation for missiles with varying velocity

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Chinese Journal of Aeronautics 2020年第3期33卷 956-964页

作者： Guoxin SUN Qiuqiu WEN Zhiqiang XU qunli xia School of Aerospace Beijing Institute of TechnologyBeijing 100081China Harbin Jiancheng Industry Company Limited Harbin 150030China

A feasible guidance scheme with impact time constraint is proposed for attacking a stationary target by missiles with time-varying *** main idea is to replace the constant velocity with the future mean velocity;therefore, the existing time-to-go estimation algorithm of the proportional navigation guidance law can be improved to adapt to varying *** order to obtain the prediction of the velocity profile, the velocity differential equation to the downrange is derived, which can be numerically integrated between the current downrange and the target position by the on-board ***, a third-order polynomial is introduced to fit the velocity profile in order to calculate the future mean *** the beginning of each guidance loop, the future mean velocity is predicted and the time-to-go information is updated, based on which a novel biased proportional navigation guidance law is established to achieve the impact time ***,numerical simulation results verified the effectiveness of the time-to-go estimation algorithm and the proposed law.

关键词： Guidance Homing missiles Impact time Proportional navigation guidance Time-varying velocity