Near-Optimal Guidance Law for Ballistic Missile Interception

1997 ◽  
Vol 20 (2) ◽  
pp. 355-361 ◽  
Author(s):  
John J. Dougherty ◽  
Jason L. Speyer
Keyword(s):  
Ballistic Missile ◽  
Guidance Law ◽  
Optimal Guidance

Optimal Sliding-Mode Terminal Guidance Law Design of Airborne Boost-Phase Ballistic Missile Interception

2010 ◽  
Vol 40-41 ◽  
pp. 15-20
Author(s):  
Yan Kai Cui ◽  
Li Fu ◽  
Xiao Geng Liang ◽  
Ling Luo
Keyword(s):  
Control Theory ◽  
Sliding Mode ◽  
Ballistic Missile ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Motion Characteristic ◽  
Vehicle Motion ◽  
Proportional Navigation Law ◽  
Terminal Guidance

Aiming at terminal guidance law design of airborne boost-phase ballistic missile interception under acceleration of target without availability, we study on optimal sliding-mode terminal guidance law design of Kinetic-Kill Vehicle. Motion characteristic and infrared characteristic of ballistic missile are analyzed basing on founding ballistic missile boost-phase motion equations. Optimal terminal guidance law of Kinetic-Kill Vehicle is designed basing on undershoot quantity least and energy minimum. Optimal guidance law and augmented proportional navigation law having the same form is proved in theory. Optimal sliding-mode terminal guidance law is designed under acceleration of target without availability, using optimal control theory and sliding-mode control theory. Simulation show that optimal sliding-mode terminal guidance law satisfies required index, reaching the aim to direct hit the target. The correctness and effectiveness of the optimal sliding-mode guidance law are proved.

Optimal Guidance Law Design for Interception of Ballistic Missiles during the Boost Phase

2011 ◽  
Vol 135-136 ◽  
pp. 655-659
Author(s):  
Wei Wen Zhou ◽  
Xiao Geng Liang
Keyword(s):  
Cost Function ◽  
Estimation Method ◽  
Ballistic Missile ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Ballistic Missiles

An optimal guidance law for interception of ballistic missile during the boost phase is presented in this paper. The kinematics characteristics of tactical missile during its boost phase are analyzed firstly. Then based on the kinematics given and assumption, the relative kinematics equations between target and missile are established. Optimal guidance law via LQ optimization is derived under the specified cost function. The time-to-go estimation method is also given in the paper. In the end of this paper, simulation is executed and the results validate that the deduced guidance law satisfy the direct hit index.

Guidance Law Design for Space-Based Anti-Missile Boost Phase Intercept

2011 ◽  
Vol 301-303 ◽  
pp. 1749-1753
Author(s):  
He Huang ◽  
Zhi Fu Zhu
Keyword(s):  
Relative Motion ◽  
Minimum Energy ◽  
Motion Equation ◽  
Ballistic Missile ◽  
Direct Impact ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Simulation Results ◽  
Miss Distance

Guidance law The optimal direct-impact guidance law for space-based anti-missile of ballistic missile in boost phase is considered. First the relative motion equation between missile and target is built, then the optimal guidance law based on terminal miss distance is designed. using minimum energy as the optimum index. The simulation results show the effectiveness of our guidance law.

Optimal Guidance Law Based on Virtual Sliding Target

2017 ◽  
Vol 30 (3) ◽  
pp. 04016097 ◽  
Author(s):  
Mohiyeddin Mozaffari ◽  
Behrouz Safarinejadian ◽  
Tahereh Binazadeh
Keyword(s):  
Guidance Law ◽  
Optimal Guidance

scholarly journals Fast guidance method of lunar landing based on dynamic programming

2021 ◽  
Vol 39 (1) ◽  
pp. 159-166
Author(s):  
Hongqian Zhao ◽  
Honghua Dai ◽  
Zhaohui Dang
Keyword(s):  
Lunar Surface ◽  
Process Time ◽  
Rescue Mission ◽  
Emergency Rescue ◽  
Whole Process ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Multi Stage ◽  
Process Guidance ◽  
Time Optimal

In this paper, a novel multi-stage trajectory transfer and fixed-point landing time optimal guidance method for the lunar surface emergency rescue mission is proposed. Firstly, the whole process motion and dynamics model for the lunar surface emergency rescue with four stages are established. Then, in the initial orbit transfer phase, the Lambert algorithm based on "prediction + correction" is designed for the non spherical gravitational perturbation of the moon. In the powered descent phase, the Hamiltonian function is used to design a time suboptimal explicit guidance law that can be applied in orbit in real time. Finally, aiming at the multi-stage global time optimal guidance, the whole time process guidance law is obtained by establishing the allowable control set for each stage in the whole process. The simulation results show that compared with the piecewise optimal control method, the present method has better optimization effect and shorter whole process time. It is of great significance to the possible emergency rescue mission of manned lunar exploration in the future.

Design and Instruction Solution of an Optimal Guidance Law for Ship-Air Missile beyond Visual Range

2012 ◽  
Vol 433-440 ◽  
pp. 3831-3836
Author(s):  
Yong Tao Zhao ◽  
Yun An Hu
Keyword(s):  
Control Variable ◽  
Linear Quadratic ◽  
Linear Quadratic Optimal Control ◽  
Guidance Law ◽  
The Earth ◽  
Optimal Guidance ◽  
Quadratic Optimal Control ◽  
Simulation Results ◽  
Visual Range ◽  
Terminal Guidance

For the case of ship-air missile intercepting the low target beyond visual range by ship-ship coordination, the instruction solution model was presented and an optimal guidance law was designed considering the effect of the curvature of the earth. In the midcourse and terminal guidance segment, the optimal guidance law was designed through applying the concept of the pseudo control variable and the theory of the linear quadratic optimal control. The information of the target was described in the launch coordinates through coordinate transformation to realize the instruction solution for the designed guidance law. The simulation results show that the model of the instruction solution is correct and the designed guidance law is feasible.

An Optimal Guidance Law with Velocity Rendezvous Angle Constraint

2015 ◽  
Vol 22 (8) ◽  
pp. 8-11
Author(s):  
徐兴元 XU Xing-yuan ◽  
郭晨鲜 GUO Chen-xian ◽  
潘晓东 PAN Xiao-dong ◽  
宋晓娜 SONG Xiao-na
Keyword(s):  
Guidance Law ◽  
Optimal Guidance
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