Three-Dimensional Nonlinear Optimal Guidance against Maneuvering Target with Large Initial Heading Error

2022 ◽  
Author(s):  
Hongyan Li ◽  
Shaoming He ◽  
Jiang Wang ◽  
Hyo-Sang Shin ◽  
Antonios Tsourdos
1995 ◽  
Vol 18 (3) ◽  
pp. 457-464 ◽  
Author(s):  
Renjith R. Kumar ◽  
Hans Seywald ◽  
Eugene M. Cliff

2021 ◽  
Vol 2021 ◽  
pp. 1-12
Author(s):  
Luo Zhe ◽  
Li Xinsan ◽  
Wang Lixin ◽  
Shen Qiang

In order to improve the autonomy of gliding guidance for complex flight missions, this paper proposes a multiconstrained intelligent gliding guidance strategy based on optimal guidance and reinforcement learning (RL). Three-dimensional optimal guidance is introduced to meet the terminal latitude, longitude, altitude, and flight-path-angle constraints. A velocity control strategy through lateral sinusoidal maneuver is proposed, and an analytical terminal velocity prediction method considering maneuvering flight is studied. Aiming at the problem that the maneuvering amplitude in velocity control cannot be determined offline, an intelligent parameter adjustment method based on RL is studied. This method considers parameter determination as a Markov Decision Process (MDP) and designs a state space via terminal speed and an action space with maneuvering amplitude. In addition, it constructs a reward function that integrates terminal velocity error and gliding guidance tasks and uses Q-Learning to achieve the online intelligent adjustment of maneuvering amplitude. The simulation results show that the intelligent gliding guidance method can meet various terminal constraints with high accuracy and can improve the autonomous decision-making ability under complex tasks effectively.


2015 ◽  
Vol 119 (1220) ◽  
pp. 1287-1299 ◽  
Author(s):  
X. Xu ◽  
Y. Liang

Abstract In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.


Author(s):  
Yi-Wei Chen ◽  
Yung-Lung Lee ◽  
Yen-Bin Chen

The fuzzy weighted input estimation (FWIE) is proposed in this paper to solve the problem of noise disturbance and combined with the three-dimensional motion equation of target trajectory to construct the tracking rule of fire control system. FWIE can estimate effectively the input data of maneuvering target acceleration to obtain the precise target state and solve the problems from the traditional Kalman filter which cannot compute the precise estimation of target state because of the input information in the system. Simulation results show that FWIE can estimate the change of target state rapidly and precisely compared with the extended Kalman filter and the proposed tracking rule can improve the fire control system to figure out the target intercepting points with shorter miss distance.


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