3D optimal defensive guidance strategy with safe distance

2019 ◽  
Vol 41 (15) ◽  
pp. 4285-4300
Author(s):  
Feng Fang ◽  
Yuanli Cai ◽  
Faryar Jabbari
Keyword(s):  
Optimal Control ◽  
Analytical Solutions ◽  
Three Dimensional ◽  
Safe Distance ◽  
Active Defense ◽  
Pursuit Evasion ◽  
Guidance Law ◽  
3D Space ◽  
Optimal Guidance ◽  
Forward Extension

This work investigates the active defense problem wherein a target aircraft launches a defending missile (i.e. a defender) to intercept an attacking missile in three-dimensional (3D) space. The novelty of this work includes: adding a safe distance for the target, which protects the target from being influenced by defensive interception, and designing a new 3D defensive guidance strategy without linearization to meet different guidance requirements. The defensive guidance strategy combines the approach of analyzing 3D pursuit-evasion engagement and the optimal control to obtain the guidance law. The approach derives the analytical solutions of 3D pursuit-evasion engagement, and a fast algorithm to predict the trajectory of attacking missile is proposed based on these analytical solutions. The advantages of this guidance strategy include incorporation of the added safe distance requirement directly without hindering the ability of the optimal guidance law to meet other requirements, and straight-forward extension for advanced scenarios where multi-defenders intercept the attacking missile simultaneously from different directions. The performance of the 3D defensive guidance law is evaluated via simulations.

scholarly journals Evasion-Pursuit Strategy against Defended Aircraft Based on Differential Game Theory

2019 ◽  
Vol 2019 ◽  
pp. 1-12
Author(s):  
Qilong Sun ◽  
Minghui Shen ◽  
Xiaolong Gu ◽  
Kang Hou ◽  
Naiming Qi
Keyword(s):  
Game Theory ◽  
Differential Game ◽  
Optimal Strategies ◽  
Open Loop ◽  
Active Defense ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Differential Game Theory ◽  
One To One ◽  
The One

The active defense scenario in which the attacker evades from the defender and pursues the target is investigated. In this scenario, the target evades from the attacker, and the defender intercepts the attacker by using the optimal strategies. The evasion and the pursuit boundaries are investigated for the attacker when the three players use the one-to-one optimal guidance laws, which are derived based on differential game theory. It is difficult for the attacker to accomplish the task by using the one-to-one optimal guidance law; thus, a new guidance law is derived. Unlike other papers, in this paper, the accelerations of the target and the defender are unknown to the attacker. The new strategy is derived by linearizing the model along the initial line of sight, and it is obtained based on the open-loop solution form as the closed-loop problem is hard to solve. The results of the guidance performance for the derived guidance law are presented by numerical simulations, and it shows that the attacker can evade the defender and intercept the target successfully by using the proposed strategy.

Time-energy optimal guidance strategy for realistic interceptor using pseudospectral method

2020 ◽  
Vol 42 (13) ◽  
pp. 2361-2371 ◽  
Author(s):  
Arunava Banerjee ◽  
Mashuq Nabi ◽  
T. Raghunathan
Keyword(s):  
Optimal Control ◽  
Pseudospectral Method ◽  
Two Dimensional ◽  
Energy Usage ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Legendre Pseudospectral Method ◽  
The Cost ◽  
Guidance Laws

This paper proposes the use of Legendre pseudospectral method (PSM) to obtain the optimal guidance strategy for a two-dimensional interceptor problem. An optimal control problem is formulated that addresses the conflicting objective of minimizing the energy usage, along with minimizing the time taken by missile to capture the target. The PSM-based guidance strategy is compared with other conventional guidance laws such as pure proportional navigation (PPN) guidance law and also evolutionary algorithm inspired differential evolution tuned proportional navigation (DEPN) guidance law. A scheme by which the PSM guidance strategy can be applied online is also included in this paper. The cost function value and the interception time indicates the superiority of the PSM-based guidance strategy.

3D Guidance Law with INS/IR Integration for Increasing Penetration Force

2012 ◽  
Vol 548 ◽  
pp. 719-723
Author(s):  
Qiang Xing ◽  
Wan Chun Chen ◽  
Bao Yin Ming
Keyword(s):  
Electromagnetic Interference ◽  
Three Dimensional ◽  
Guidance System ◽  
Flight Vehicle ◽  
Guidance Law ◽  
Infrared Seeker ◽  
Optimal Guidance ◽  
Penetration Force ◽  
Modern Warfare ◽  
3D Guidance

In the modern warfare, the trajectory of flight vehicle was required to have the ability to be adjusted in specified shape to increasing the penetration force. This paper deals with the guidance law and data fusion system to impact a target in specified direction for precision guided munitions. A three-dimensional guidance law is designed by combining the optimal guidance law and terminal acceleration tuning methodology. A new configuration of Extended Kalman Filter (EKF) is employed to obtain the range and angle information from INS and infrared seeker to improve the survivability of guidance system in the circumstance with strong electromagnetic interference.

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.

Novel guidance model and its application for optimal re-entry guidance

2018 ◽  
Vol 122 (1257) ◽  
pp. 1811-1825
Author(s):  
C.W. Jiang ◽  
G.F. Zhou ◽  
B. Yang ◽  
C.S. Gao ◽  
W.X. Jing
Keyword(s):  
Three Dimensional ◽  
Impact Angle ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Entry Guidance ◽  
Independent Variable ◽  
Guidance Laws ◽  
Terminal Guidance ◽  
Impact Angle Constraint ◽  
Guidance Model

ABSTRACTAiming at three-dimensional (3D) terminal guidance problem, a novel guidance model is established in this paper, in which line-of-sight (LOS) range is treated as an independent variable, describing the relative motion between the vehicle and the target. The guidance model includes two differential equations that describe LOS’s pitch and yaw motions in which the pitch motion is separately decoupled. This model avoids the inaccuracy of simplified two-dimensional (2D) guidance model and the complexity of 3D coupled guidance model, which not only maintains the accuracy but also simplifies the guidance law design. The application of this guidance model is studied for optimal re-entry guidance law with impact angle constraint, which is presented in the form of normal overload. Compared with optimal guidance laws based on traditional guidance model, the proposed one based on novel guidance model is implemented with the LOS range instead of time-to-go, which avoids the problem of the time-to-go estimation of traditional optimal guidance laws. Finally, the correctness and validity of the guidance model and guidance law are verified by numerical simulation. The guidance model and guidance law proposed in this paper provide a new way for the design of terminal guidance.

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