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Extended optimal guidance law with impact angle and acceleration constriants 被引量:8
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作者 Ran Li Qunli Xia Qiuqiu Wen 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2014年第5期868-876,共9页
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 obje... 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. 展开更多
关键词 impact angle constraint optimal guidance law accel- eration command guidance order.
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Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints 被引量:7
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作者 LI Ran WEN Qiuqiu +1 位作者 TAN Wangchun ZHANG Yijie 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2018年第1期142-151,共10页
In this paper, a new adaptive optimal guidance law with impact angle and seeker’s field-of-view(FOV) angle constraints is proposed. To this end, the generalized optimal guidance law is derived first. A changeable imp... In this paper, a new adaptive optimal guidance law with impact angle and seeker’s field-of-view(FOV) angle constraints is proposed. To this end, the generalized optimal guidance law is derived first. A changeable impact angle weighting(IAW) coefficient is introduced and used to modify the guidance law to make it adaptive for all guidance constraints. After integrating the closed-form solution of the guidance command with linearized engagement kinematics, the analytic predictive models of impact angle and FOV angle are built, and the available range of IAW corresponding to constraints is certain. Next, a calculation scheme is presented to acquire the real-time value of IAW during the entire guidance process. When applying the proposed guidance law, the IAW will keep small to avoid a trajectory climbing up to limit FOV angle at an initial time but will increase with the closing target to improve impact position and angle accuracy, thereby ensuring that the guidance law can juggle orders of guidance accuracy and constraints control. 展开更多
关键词 optimal guidance law impact angle constraint fieldof-view(FOV) angle constraint weighting coefficient
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Design of Closed Loop Optimal Guidance Law Using Neural Networks 被引量:1
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作者 ZHOU Rui 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2002年第2期98-102,共5页
It is generally impossible to obtain the analytic optimal guidance law for complex nonlinear guidance systems of homing missiles,and the open loop optimal guidance law is often obtained by numerical methods,which can ... It is generally impossible to obtain the analytic optimal guidance law for complex nonlinear guidance systems of homing missiles,and the open loop optimal guidance law is often obtained by numerical methods,which can not be used directly in practice.The neural networks are trained off line using the optimal trajectory of the missile produced by the numerical open loop optimal guidance law,and then,the converged neural networks are used on line as the feedback optimal guidance law in real time.The research shows that different selections of the neural networks inputs,such as the system state variables or the rate of LOS(line of sight),may have great effect on the performances of the guidance systems for homing missiles.The robustness for several guidance laws is investigated by simulations,and the modular neural networks architectures are used to increase the approximating and generalizing abilities in the large state space.Some useful conclusions are obtained by simulation results. 展开更多
关键词 neural networks missile guidance optimal guidance law proportional navigation guidance
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Advanced optimal guidance law with maneuvering targets
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作者 WEN Qiu-qiu XIA Qun-li LI Ran 《Journal of Beijing Institute of Technology》 EI CAS 2014年第1期8-15,共8页
Based on optimal theory, the advanced optimal guidance law (AOGL) is derived for the interception endgame of maneuvering targets in step mode. The guidance system dynamics, target maneuvering dynamics and accelerati... Based on optimal theory, the advanced optimal guidance law (AOGL) is derived for the interception endgame of maneuvering targets in step mode. The guidance system dynamics, target maneuvering dynamics and acceleration, gravity acceleration are considered and their effects are dy- namically cancelled out in guidance law. A four states Kalman filter is designed to estimate the re- quired states for AOGL. Simulation results show the AOGL is less sensitive to errors caused by target maneuvering and guidance system lag, and it needs less missile acceleration in most time of guidance especially at the end of intercept than other guidance laws. Especially its acceleration is zero at the end of intercept when attacking maneuvering target. 展开更多
关键词 target maneuvering optimal guidance law system aerodynamic miss distance
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Kinetic Optimal Midcourse Guidance Law for Air-to-Air Missiles
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作者 常超 林德福 +2 位作者 祁载康 农雨林 程振轩 《Journal of Beijing Institute of Technology》 EI CAS 2009年第4期452-456,共5页
A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta grade numerical method is proposed to find the optimal trajectory. Real data of an Mr-to-air m... A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta grade numerical method is proposed to find the optimal trajectory. Real data of an Mr-to-air missile is referred to for comparing results using the kinetic optimal midcourse guidance law with those under both the kinematic optimal guidance law and singular perturbation sub-optimal guidance law, wherein the latter two laws are modified in this paper by adding a vertical g-bias command to each law for the sake of trajectory shaping. Simulation results show that using the new kinetic optimal mideourse guidance law can help save energy and maximize terminal velocity effectively. 展开更多
关键词 optimal guidance law simplified Runge-Kutta grade method terminal velocity
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