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.

Biased optimal guidance law with specified velocity rendezvous angle constraint

2015 ◽  
Vol 119 (1220) ◽  
pp. 1287-1299 ◽  
Author(s):  
X. Xu ◽  
Y. Liang
Keyword(s):  
High Speed ◽  
Terminal Phase ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Time ◽  
Optimal Guidance ◽  
Simulation Results ◽  
Miss Distance ◽  
Simplified Mathematical Model ◽  
Distance Setting

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.

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.

A Discrete Sliding-Mode Guidance Law

2014 ◽  
Vol 137 (2) ◽  
Author(s):  
Di Zhou ◽  
Sheng Sun ◽  
Jing Yang Zhou ◽  
Kok Lay Teo
Keyword(s):  
Relative Motion ◽  
Finite Time ◽  
Sliding Mode ◽  
Discrete Form ◽  
Motion Equations ◽  
Guidance Law ◽  
Target Acceleration ◽  
Simulation Results

Based on the discrete form of the target-missile relative motion equations in plane, a discrete sliding-mode guidance (DSMG) law is proposed. All previous missile seeker's measurements are used in the design of the DSMG law to estimate the target acceleration such that noises in the seeker's measurements are effectively being smoothened. It is proved that the proposed DSMG law is finite time convergent. Quasi sliding-mode bands of the DSMG law are discussed, and the formula for calculating the terminal miss distances of the missile under the DSMG law are presented. Simulation results from a space interception process verify the effectiveness of the proposed method.

Application of optimal control law to laser guided bomb

2018 ◽  
Vol 122 (1251) ◽  
pp. 785-797
Author(s):  
Takieddine Mouada ◽  
Milos V. Pavic ◽  
Bojan M. Pavkovic ◽  
Sasa Z. Zivkovic ◽  
Mirko S. Misljen
Keyword(s):  
Noise Removal ◽  
Control Law ◽  
State Variables ◽  
Linear Quadratic ◽  
State Variable ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Differential Game Theory ◽  
Miss Distance ◽  
Guidance Laws

ABSTRACTThe paper presents a laser guided bomb guidance law based on the linear quadratic differential game theory, where a case of two perpendicular planes with two state variables in each plane has been considered. The Kalman filtering method has been used for noise removal from the measured signals and for estimation of the missing state variable values needed for the optimal guidance law. Optimisation has been conducted with respect to minimisation of the performance index. Comparative analysis of different guidance laws is done. A statistical analysis is performed to obtain the terminal miss distance in dependence on total flight time.

Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

2017 ◽  
Vol 231 (14) ◽  
pp. 2515-2536 ◽  
Author(s):  
Hui Wang ◽  
Jiang Wang ◽  
Defu Lin
Keyword(s):  
General Expression ◽  
Impact Angle ◽  
Acceleration Response ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Terminal Constraints ◽  
Miss Distance ◽  
Guidance Laws ◽  
Impact Angle Constraint

To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

Evaluation of Guidance Laws Performance Sing Genetic Algorithm

2014 ◽  
Vol 598 ◽  
pp. 723-730
Author(s):  
Mohamed Zakaria ◽  
Talaat Ibrahim ◽  
Alaa El Din Sayed Hafez ◽  
Hesham Abdin
Keyword(s):  
Genetic Algorithm ◽  
Differential Geometry ◽  
Standard Deviation ◽  
Optimization Process ◽  
Line Of Sight ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Simulation Results ◽  
Miss Distance ◽  
Guidance Laws

Several conditions affect the performance of guidance law like target parameters or delayed line of sight rate. A variable navigation ratio is used to enhance the performance of guidance law. In this paper a Genetic Algorithm is used to formulate different forms of variable gains and measure the miss distance. An optimization process is running to find the minimum miss distance. The average values and standard deviation of miss distance for all genetic algorithm individuals are calculated to measure the performance and robustness of guidance law. Two guidance laws are considered proportional navigation (PN) and differential geometry (DG). The simulation results show that the proportional navigation is superior to differential geometry performance in the presence of delayed line of sight rate.

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.

Research on Improved Extended Proportional Navigation Guidance

2013 ◽  
Vol 347-350 ◽  
pp. 980-984
Author(s):  
De Long Feng ◽  
Suo Chang Yang ◽  
Yun Zhi Yao ◽  
Ying Xi Liu
Keyword(s):  
Relative Motion ◽  
Motion Model ◽  
Improved Method ◽  
Proportional Navigation ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Simulation Results ◽  
Set Up ◽  
Proportional Navigation Guidance

This paper proposed an improved method on the basis of the extended proportional guidance law. The method solved the weak observability problem of system sate in guided missile attacking maneuvering target. It is simple in form and easy for engineering implementation. This paper set up relative motion model and the observability theory indexes. The improved propotional guidance law is simulated using the MATLAB language. The simulation results show that the method is reasonable, effective and improving the observability.

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 strategy for target protection with a defender in the pursuit-evasion scenario

2018 ◽  
Vol 15 (3) ◽  
pp. 289-301
Author(s):  
Qilong Sun ◽  
Naiming Qi ◽  
Mingying Huo
Keyword(s):  
Optimal Strategy ◽  
First Order ◽  
Pursuit Evasion ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Evasion Strategy ◽  
Simulation Results ◽  
Guidance Laws

The conflict among three players, an attacker, a defender, and a target, in the pursuit-evasion strategy context is investigated. The problem is derived for a defender launching from the target with the assumption that the guidance laws of the attacker and defender are linear in form. During the endgame, the target lures the attacker close to the defender based on the attacker’s reaction to the target. Two kinds of optimal guidance laws for protecting the target from the attacker are presented first. Showing that the two kinds of guidance laws are flawed, a new optimal guidance law is subsequently derived. Considering that the players’ control efforts are bounded by reality, the relevant parameters corresponding to the optimal guidance laws also need to be analyzed. For adversaries obeying first-order dynamics, the performance of the guidance laws is simulated for different parameters, and under reasonable parameter choices, the simulation results show that the new optimal guidance law can enable the target to assist the defender in effectively intercepting the attacker.

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