Robust intercept guidance law with predesigned zero-effort miss distance convergence for capturing maneuvering targets

2020 ◽  
Vol 357 (2) ◽  
pp. 1118-1136
Author(s):  
Xiaodong Yan ◽  
Shi Lyu
Keyword(s):  
Guidance Law ◽  
Maneuvering Targets ◽  
Miss Distance

Joint Design and Application of Adaptive Filter and Optimal Control

1999 ◽  
Author(s):  
Yu Hong Ren ◽  
Zhong Liang Jing
Keyword(s):  
Adaptive Filter ◽  
High Performance ◽  
Guidance And Control ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Optimal Guidance ◽  
Kaiman Filter ◽  
Efficient Scheme ◽  
Miss Distance ◽  
And Control

Abstract Kaiman filter is well suited for application to the problems of missile guidance and control. In this paper, we make use of the Kaiman filter theory to develop an efficient scheme for estimating the current states of maneuvering targets, and optimal guidance law is applied in order for a high performance index of miss distance. This scheme is designed to suit for tracking several types of target if aircraft can not provide much known information regarding maneuvering targets before launching missile. It is shown how an adaptive filter based on Current Statistical Model can be applied in conjunction with the optimal guidance law to improve system attacking performance and to relax the requirements of maneuvering target acceleration information during tracking and attacking.

Impact Angle Constrained Guidance Law for Intercepting Non-maneuvering Targets Avoiding Obstacles

2022 ◽  
Author(s):  
Prajapati D. Dharmendrabhai ◽  
Akash Gholap ◽  
Nikhil K. Singh ◽  
Sikha Hota
Keyword(s):  
Impact Angle ◽  
Guidance Law ◽  
Maneuvering Targets

Design and Simulation of Guidance Law for a Kind of Flight Test Missile

2012 ◽  
Vol 538-541 ◽  
pp. 2887-2891
Author(s):  
Yu Qian ◽  
Xiao Jun Xiang ◽  
Jun Li Yang
Keyword(s):  
Flight Test ◽  
Target Point ◽  
Impact Point ◽  
Integral Term ◽  
Guidance Law ◽  
Velocity Information ◽  
The Difference ◽  
Miss Distance ◽  
Midcourse Guidance ◽  
The Impact

To reduce the miss distance of flight test missile, the midcourse guidance law is studied in this paper. The nonlinear projectile dynamic model is developed at first, and then designed the midcourse guidance law with the impact point prediction information. The guidance law was designed using the difference between predicting impact point and target point. To improve the guidance law’s performance, this research inducted the predicted impact point’s velocity information and integral term into guidance law command. At the end, the simulation was developed. The results of simulation show that the guidance law designed in this study is successful and it can satisfy the test missile’s flight mission requirements.

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