Multi-agent cooperative multi-model adaptive guidance law

2021 ◽  
pp. 1-27
Author(s):  
S.B. Wang ◽  
S.C. Wang ◽  
Z.G. Liu ◽  
S. Zhang ◽  
Y. Guo
Keyword(s):  
Adaptive Estimation ◽  
Control Input ◽  
Control Effort ◽  
Cooperative Strategies ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Multi Agent ◽  
Homing Missiles ◽  
Analytical Expressions ◽  
Guidance Laws

ABSTRACT A multi-agent engagement scenario is considered in which a high-value aircraft launches two defenders to intercept two homing missiles aimed at the aircraft. Under the assumption that all aircrafts have first-order linear dynamic characteristics, a combined multiple-mode adaptive estimation (MMAE) and a two-way cooperative optimal guidance law are proposed for the target–defenders team. Considering the full cooperation of the target and both the two defenders, the two-way cooperative strategies provide the analytical expressions for their optimal control input, enabling the target–defenders team to intercept the missiles with minimal control effort. To successfully intercept the missiles, MMAE is used to identify the guidance laws adopted by the missiles and estimate their states. The simulation results show that the target cooperating with the defenders to perform lure manoeuvres for the missiles can improve the guidance performance of the defenders as well as reduce the control effort of the defenders for intercepting the missiles.

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.

Cooperative guidance laws for simultaneous attack against a target with unknown maneuverability

2018 ◽  
Vol 233 (7) ◽  
pp. 2518-2535 ◽  
Author(s):  
Xiaoqian Wei ◽  
Jianying Yang
Keyword(s):  
New Approach ◽  
Maneuvering Target ◽  
Guidance Law ◽  
New Strategy ◽  
Multi Agent ◽  
Cooperation Protocol ◽  
Distributed Cooperation ◽  
Guidance Laws ◽  
Simultaneous Attack ◽  
Adaptive Control Law

This paper designs new guidance laws for the simultaneous multi-agent interception of a maneuvering target with unknown acceleration. The new approach achieves additional benefits as follows. (1) The completely distributed cooperation protocol ensures that the simultaneous attack task can be completed. (2) The disturbance observer and the adaptive control law can solve the coordinated attack problem with an unknown target acceleration. (3) The design of the guidance law requires only neighbor-derived information rather than global information, which increases the practicability of the new strategy. Numerical simulations with comparisons demonstrate the effectiveness and superiority of the proposed method.

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.

Optimal cooperative guidance with guaranteed miss distance in three-body engagement

2016 ◽  
Vol 232 (3) ◽  
pp. 492-504 ◽  
Author(s):  
Feng Fang ◽  
Yuan-Li Cai
Keyword(s):  
Linear Quadratic ◽  
Control Effort ◽  
Guidance Law ◽  
Cooperative Guidance ◽  
The One ◽  
Three Body ◽  
The Cost ◽  
Miss Distance ◽  
Penalty Weight ◽  
Guidance Laws

The three-body engagement where a target aircraft protects itself by using a cooperative defender missile to intercept an attacking missile is investigated. It is formulated as a constrained linear quadratic optimal problem. Two different optimal cooperative guidance laws for the target and defender are proposed in two cooperation schemes. Since any control effort to reduce the miss distance to smaller than missile’s lethal radius is wasted, the guidance laws are derived to achieve an upper bound on the missile–defender miss distance. In the two-way cooperation scheme, the target and the defender act as a team. How the target makes a trade-off between aiding the defender and evading the missile is investigated by considering both the missile–target zero-effort miss distance and the control effort into the cost function. Without the penalty weight on the missile–target zero-effort miss distance, the two-way minimum control effort guidance laws are available. In the one-way cooperation scheme, the target uses a known evasion strategy independently. The optimal cooperative guidance law is derived for minimizing the control effort of the defender. Simulation results show that these proposed guidance laws can provide a specified missile–defender miss distance and save the control effort compared with the zero-miss-distance guidance law. Two-way cooperation scheme outperforms one-way cooperation scheme.

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.

scholarly journals Generalized Guidance Formulation for Impact Angle Interception with Physical Constraints

Aerospace ◽  
2021 ◽  
Vol 8 (10) ◽  
pp. 307
Author(s):  
Hyeong-Geun Kim ◽  
Jun-Yong Lee
Keyword(s):  
Impact Angle ◽  
Field Of View ◽  
Line Of Sight ◽  
Physical Constraints ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Rate Profile ◽  
Homing Missiles ◽  
Impact Angles ◽  
General Guidance

This paper proposes an optimal impact angle control guidance law for homing missiles with a narrow field-of-view of the seekers. As groundwork for designing a guidance law, we first present a general guidance structure that can achieve any terminal constraint of the line-of-sight rate based on the optimal control theory. We configure the desired profile of the line-of-sight rate using a saturation function whose exact form is determined to satisfy the required boundary conditions. By combining the line-of-sight rate profile with the optimal guidance structure, we develop a guidance law that achieves an impact angle interception with the field-of-view constraint. Herein, as the entire guidance structure is derived based on exact kinematics without any approximation, the proposed law ensures the accurate impact angle interception for various engagement scenarios. This precise consideration of the engagement kinematics also accurately ensures the energy optimality of preventing the excessive use of control inputs when homing. To evaluate the performance of the proposed method, numerical simulations with various engagement scenarios are conducted, and the results demonstrate that the proposed law allows missiles to accurately intercept their targets with the desired impact angles and without violating the prescribed field-of-view constraint.

scholarly journals Adaptive Estimation and Cooperative Guidance for Active Aircraft Defense in Stochastic Scenario

Sensors ◽  
2019 ◽  
Vol 19 (4) ◽  
pp. 979 ◽  
Author(s):  
Feng Fang ◽  
Yuanli Cai ◽  
Zhenhua Yu
Keyword(s):  
Adaptive Estimation ◽  
Posteriori Probability ◽  
Multiple Model ◽  
Linear Quadratic ◽  
Control Effort ◽  
A Posteriori Probability ◽  
Active Defense ◽  
Cubature Kalman Filter ◽  
Cooperative Guidance ◽  
Guidance Laws

The active aircraft defense problem is investigated for the stochastic scenario wherein a defending missile (or a defender) is employed to protect a target aircraft from an attacking missile whose pursuit guidance strategy is unknown. For the purpose of identifying the guidance strategy, the static multiple model estimator (sMME) based on the square-root cubature Kalman filter is proposed, and each model represents a potential attacking missile guidance strategy. Furthermore, an estimation enhancement approach is provided by using pseudo-measurement. For each model in the sMME, the model-matched cooperative guidance laws for the target and defender are derived by formulating the active defense problem as a constrained linear quadratic problem, where an accurate defensive interception and the minimum evasion miss distance are both considered. The proposed adaptive cooperative guidance laws are the result of mixing the model-matched optimal cooperative guidance laws in the criterion of maximum a posteriori probability in the framework of the sMME. By adopting the adaptive cooperative guidance laws, the target can facilitate the defender’s interception with the attacking missile with less control effort. Also, simulation results show that the proposed guidance laws increase the probability of successful target protection in the stochastic scenario compared with other defensive guidance laws.

The approach of partial stabilisation in design of discrete-time robust guidance laws against manoeuvering targets

2020 ◽  
Vol 124 (1277) ◽  
pp. 1114-1127
Author(s):  
M.H. Shafiei ◽  
N. Vazirpour
Keyword(s):  
Discrete Time ◽  
Three Dimensional ◽  
Line Of Sight ◽  
Control Input ◽  
Lyapunov Theorem ◽  
Digital Controllers ◽  
Guidance Law ◽  
Short Time ◽  
Guidance Laws ◽  
Guidance Problem

ABSTRACTIn this paper, a robust three-dimensional guidance law against manoeuvering targets is designed using the approach of discrete-time partial stabilisation. In the proposed method, the equations of the guidance problem are divided into two subsystems where the asymptotic stability is desired only for the first one. The control input of the second subsystem is designed such that the collision to be ensured in a short time. Despite recent advances in technology and implementation of digital controllers, the design of guidance laws with the approach of discrete-time partial stabilisation has not been done, till now. One of the advantages of this paper is to design a discrete-time guidance law even with the difficulties of the discrete-time Lyapunov theorem. Moreover, the Lyapunov function is chosen based on the physics of the guidance problem (making the rate of line of sight (LOS) rotation close to zero), and it is shown that it is not possible to asymptotically stabilise the system in the case of manoeuvering targets. Nevertheless, to guarantee the collision with the target, it is enough to limit the rotation rate of LOS to a small value. Finally, simulation results are given to show the appropriate performance of the proposed guidance law.

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.

Variational method-based distributed optimal guidance laws for multi-attackers’ simultaneous attack

2021 ◽  
pp. 014233122098143
Author(s):  
Xiaoqian Wei ◽  
Jianying Yang ◽  
Xiangru Fan
Keyword(s):  
Variational Method ◽  
Calculation Algorithm ◽  
Relative State ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Single Target ◽  
Directed Spanning Tree ◽  
A Chain ◽  
Guidance Laws ◽  
Simultaneous Attack

To solve the problem of cooperative encirclement and simultaneous attack of multiple unmanned aerial vehicles, variational method and Hamiltonian optimization are utilized to design an optimal attack trajectory of multiple attackers pursuing a single target that has fixed initial relative state, fixed final relative state and fixed duration of the attack under condition that the acceleration of the target being estimable. When terminal relative state and attack duration are unknown, online calculation algorithm is used to compute a chain of key intermediate points to create the guidance law and ensure successful deliverance of multiple attackers’ simultaneous attack of the target. The only requirement for the multi-attacker communication network is that it contains a directed spanning tree. The guidance laws can function properly as long as one or more attacker can observe the target. The novel guidance laws practicability are verified by simulation results.

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