Co-operative 3D salvo attack of multiple missiles under switching topologies subject to time-varying communication delays

2019 ◽  
Vol 123 (1262) ◽  
pp. 464-483
Author(s):  
X.L. Ai ◽  
L.L. Wang ◽  
Y.C. Shen
Keyword(s):  
Initial Conditions ◽  
Sufficient Conditions ◽  
Time Varying ◽  
Communication Delays ◽  
Proportional Navigation ◽  
Stationary Target ◽  
Switching Topologies ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Proportional Navigation Guidance

ABSTRACTThis study focuses on the co-operative salvo attack problem of multiple missiles against a stationary target under jointly connected switching topologies subject to time-varying communication delays. By carefully exploring certain features of the typical pure proportional navigation guidance law, a two-stage distributed guidance scheme is proposed without any information on time-to-go in this study to realise the simultaneous attack of multiple missiles. In the first guidance stage, a co-operative guidance law is proposed using local neighbouring communications only to achieve consensus on range-to-go and heading error to provide favourable initial conditions for the latter phase, in which switching topologies and time-varying communication delays are taken into account when obtaining sufficient conditions of consensus in terms of linear matrix inequalities. Then, missiles disconnect from each other and are guided individually by the typical pure proportional navigation guidance law with the same navigation gain to realise salvo attack in the second guidance phase. Finally, numerical simulations are carried out to clearly validate the theoretical results.

scholarly journals Distributed target-encirclement guidance law for cooperative attack of multiple missiles

2020 ◽  
Vol 17 (3) ◽  
pp. 172988142092914
Author(s):  
Pengpeng Yan ◽  
Yonghua Fan ◽  
Ruifan Liu ◽  
Mingang Wang
Keyword(s):  
Lyapunov Stability Theory ◽  
Line Of Sight ◽  
Consensus Protocol ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Distributed Target ◽  
The Impact ◽  
Simultaneous Attack ◽  
Proportional Navigation Guidance

The target-encirclement guidance problem for many-to-one missile-target engagement scenario is studied, where the missiles evenly distribute on a target-centered circle during the homing guidance. The proposed distributed target-encirclement guidance law can achieve simultaneous attack of multiple missiles in different line-of-sight directions. Firstly, the decentralization protocols of desired line-of-sight angles are constructed based on the information of neighboring missiles. Secondly, a biased proportional navigation guidance law that can arbitrarily designate the impact angle is cited. The missiles can achieve all-aspect attack on the target in an encirclement manner by combining the biased proportional navigation guidance law and dynamic virtual targets strategy. Thirdly, the consensus protocol of simultaneous attack is designed, which can guarantee that all missiles’ time-to-go estimates achieve consensus asymptotically, and the convergence of the closed-loop system is proved strictly via the Lyapunov stability theory. Finally, numerical simulation results demonstrate the performance and feasibility of the proposed distributed target-encirclement guidance law in different engagement situations.

Field-of-view-constrained impact angle control guidance with error convergence before interception considering speed changes

2020 ◽  
pp. 095441002094201
Author(s):  
Jinrae Kim ◽  
Namhoon Cho ◽  
Youdan Kim
Keyword(s):  
Impact Angle ◽  
Field Of View ◽  
Time Varying ◽  
Angle Error ◽  
Proportional Navigation ◽  
Stationary Target ◽  
Guidance Law ◽  
Independent Variable ◽  
Angle Interval ◽  
The Impact

An impact angle control guidance law is proposed for stationary target interception considering missile's field-of-view limit and speed changes. The proposed impact angle control guidance law is structured as a biased proportional navigation with a time-varying bias. The proposed guidance law does not involve any switching logic for maintaining lock-on; hence, the guidance command is continuous during the entire engagement. Unlike the most existing studies, the proposed method guarantees that the impact angle error converges to zero before interception without the constant-speed assumption. To realize these desirable properties, the positive invariance of the bounded look angle interval and the change of independent variable are utilized. Numerical simulations are conducted to demonstrate the performance of the proposed guidance law.

Interactive Multiple Model Filter for Tracking a Pursuer With Proportional Navigation Guidance Law

2018 ◽  
Vol 140 (8) ◽  
Author(s):  
Runle Du ◽  
Xinguang Zou ◽  
Di Zhou ◽  
Jiaqi Liu
Keyword(s):  
Relative Velocity ◽  
Accurate Estimation ◽  
Time Varying ◽  
Multiple Model ◽  
Motion Model ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Model Filter ◽  
Interactive Multiple Model ◽  
Proportional Navigation Guidance

This paper addresses a pursuer tracking problem where the pursuer's acceleration is given by a proportional navigation (PN) guidance law with a time-varying navigation ratio which varies with the relative range between the pursuer and its target. Based on a motion model that exactly describes the relative motion and the PN guidance law, a novel filter for tracking such a pursuer is designed using interactive multiple model (IMM) algorithm and unscented Kalman filtering (UKF) technique. This filter is able to accurately estimate the relative range, relative velocity, and the acceleration of pursuer even if the pursuer adopts a PN guidance law with time-varying navigation ratio. The proposed tracking method is evaluated in extensive Monte Carlo simulations. It is shown that accurate estimation results have been obtained, and the model probabilities in the IMM UKF filter are consistent with real situations.

Cooperative Salvo Attack Using Guidance Law of Multiple Missiles

2015 ◽  
Vol 19 (2) ◽  
pp. 301-306 ◽  
Author(s):  
Jie Zeng ◽  
◽  
Lihua Dou ◽  
Bin Xin
Keyword(s):  
Mean Value ◽  
Stationary Target ◽  
Impact Time ◽  
State Variable ◽  
Guidance Law ◽  
Multiple Missiles ◽  
The Common ◽  
The Mean ◽  
Guidance Problem ◽  
Common Target

In this article, a guidance problem for cooperative salvo attack of multiple missiles against a single stationary target is investigated. The proposed guidance law combines the well-known PNG law and cooperative acceleration command, which is based on the feedback of state error between the current missile and the mean value of participant missiles. The state variable in this paper is used as the approximate calculation of time-to-go. The cooperative acceleration command is designed to adjust the flight path and impact time, which leads the multi-missiles to hit the common target simultaneously. During the engagement, the velocities of missiles are not changed and presetting impact time is not needed. Simulation results show the effectiveness of the proposed guidance law.

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