scholarly journals Cooperative Guidance Law with Predefined-Time Convergence for Multimissile Systems

2021 ◽  
Vol 2021 ◽  
pp. 1-13
Author(s):  
Liang Jing ◽  
Changzhu Wei ◽  
Liang Zhang ◽  
Naigang Cui
Keyword(s):  
Angular Rate ◽  
Fixed Time ◽  
Line Of Sight ◽  
Consensus Protocol ◽  
Impact Time ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Cooperative Guidance ◽  
The Impact ◽  
Guidance Laws

To intercept the maneuvering target through multimissile cooperation, predefined-time cooperative guidance (PTCG) law is presented with constraints including the impact time and the line-of-sight (LOS) angle. In order to achieve simultaneous interception, we propose a PTCG law in the LOS direction based on a predefined-time consensus protocol, which guarantees the achievement of consensus on each missile’s impact time within the predefined time. Furthermore, to ensure the predefined-time convergence of the LOS angle and the predefined-time convergence of the LOS angular rate, a PTCG law with a fixed-time disturbance observer (FxTDO) is presented in the normal direction of the LOS. Compared with the traditional finite-time or fixed-time cooperative guidance laws, the proposed PTCG law predefines the upper bound of the settling time as an explicit parameter. Finally, the simulation results of the PTCG law verify the efficiency of the proposed method.

Fixed-time cooperative guidance for multiple missiles with impact angle constraint

2021 ◽  
pp. 095441002110480
Author(s):  
Xinghe Zhou ◽  
Weihong Wang ◽  
Zhenghua Liu
Keyword(s):  
Sliding Mode ◽  
Angular Rate ◽  
Fixed Time ◽  
Impact Angle ◽  
Terminal Sliding Mode ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Cooperative Guidance ◽  
Impact Angle Constraint

For the guidance problem of multiple missiles attacking a maneuvering target simultaneously in plane, a novel fixed-time distributed cooperative guidance law with impact angle constraint is designed in this paper. The design process of distributed cooperative guidance law can be roughly divided into two parts. First, based on the nonsingular terminal sliding mode control, a cooperative guidance law on the line-of-sight (LOS) direction is developed, which can guarantee that all missiles hit the maneuvering target simultaneously. Second, another guidance law in normal direction of the LOS direction is designed to achieve the fixed-time convergence of LOS angular rate and LOS angle. Finally, numerical simulations verify the effectiveness of the proposed cooperative guidance law for different engagement scenarios.

scholarly journals Three-Dimensional Fixed-Time Cooperative Guidance Law With Impact Angle Constraint and Prespecified Impact Time

IEEE Access ◽  
2021 ◽  
Vol 9 ◽  
pp. 29755-29763
Author(s):  
Mu Lin ◽  
Xiangjun Ding ◽  
Chunyan Wang ◽  
Li Liang ◽  
Jianan Wang
Keyword(s):  
Three Dimensional ◽  
Fixed Time ◽  
Impact Angle ◽  
Impact Time ◽  
Guidance Law ◽  
Cooperative Guidance ◽  
Impact Angle Constraint

scholarly journals Fixed-Time Cooperative Guidance Law With Angle Constraint for Multiple Missiles Against Maneuvering Target

IEEE Access ◽  
2020 ◽  
Vol 8 ◽  
pp. 73268-73277
Author(s):  
Liang Jing ◽  
Liang Zhang ◽  
Jifeng Guo ◽  
Naigang Cui
Keyword(s):  
Fixed Time ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Cooperative Guidance

Impact Time Control Guidance Law Considering Seeker's Field-of-View Constraint Without Time-to-Go Information

2016 ◽  
Vol 20 (3) ◽  
pp. 412-417
Author(s):  
Zhe Yang ◽  
◽  
Defu Lin ◽  
Luyao Zang
Keyword(s):  
Sliding Mode ◽  
Field Of View ◽  
Impact Time ◽  
Time Control ◽  
Guidance Law ◽  
Heading Angle ◽  
One And Many ◽  
The Look ◽  
The Impact ◽  
Guidance Laws

Accurate time-to-go estimation with large heading angle error is difficult for homing guidance laws, especially for the impact time control. Considering this, a new cooperative guidance law which requires no time-to-go estimation is investigated. First, the impact time control problem is transformed to the look angle command tracking problem. The look angle command guarantees that the range-to-go error converges to zero asymptotically. Then the proposed guidance law considering the seeker's field-of-view constraint is derived using sliding mode control to track the desired look angle signal. Numerical simulations are performed to verify the effectiveness of the proposed guidance law for one-to-one and many-to-one engagement scenarios.

Guidance laws based on model predictive control and target manoeuvre estimator

2016 ◽  
Vol 38 (12) ◽  
pp. 1509-1519 ◽  
Author(s):  
Shaoming He ◽  
Defu Lin
Keyword(s):  
Stability Analysis ◽  
Model Predictive Control ◽  
Predictive Control ◽  
Angular Rate ◽  
Tracking Error ◽  
Small Region ◽  
Line Of Sight ◽  
Guidance Law ◽  
Angle Tracking ◽  
Guidance Laws

A new composite guidance law for intercepting manoeuvring targets with desired terminal line-of-sight (LOS) angle constraint is proposed in this paper. The presented guidance law is derived through generalized model predictive control (GMPC) augmented by a target manoeuvre estimator. More specifically, the target manoeuvre estimator is used to estimate and compensate for the unknown target manoeuvre online while the GMPC is used to obtain optimal LOS angle tracking performance. Stability analysis shows that the LOS angle tracking error and the LOS angular rate can converge to a sufficiently small region around zero asymptotically. The effectiveness of the proposed guidance law is validated by applying it to a surface-to-air missile for intercepting a head-on manoeuvring target under different scenarios.

Sliding mode guidance for impact time and angle constraints

2017 ◽  
Vol 232 (16) ◽  
pp. 2961-2977 ◽  
Author(s):  
Shashi Ranjan Kumar ◽  
Debasish Ghose
Keyword(s):  
Constant Velocity ◽  
Sliding Mode ◽  
Impact Angle ◽  
Time Error ◽  
Impact Time ◽  
Guidance Law ◽  
Terminal Constraints ◽  
Noisy Measurements ◽  
The Impact ◽  
Guidance Laws

This paper proposes a guidance strategy, which caters to both impact angle and impact time terminal constraints. This guidance scheme is based on switching between impact time and impact angle guidance laws. Unlike the existing impact time guidance laws, the proposed guidance strategy takes into account the curvature of the trajectory due to requirement of impact angle. The guidance law is derived using sliding mode control theory with the switching surface based on impact time error. The interceptor first corrects its course to nullify the impact time error and then aims to achieve interception with desired impact angle. In order to reduce transitions between the two guidance laws, a novel hysteresis loop is introduced in the switching conditions. The guidance law is initially designed for stationary targets, and later it is extended to constant velocity targets using the notion of predicted interception point. In order to validate the efficacy of the proposed guidance strategy, simulation results are presented with constant as well as realistic time-varying speed interceptor models for different engagement scenarios against stationary and constant velocity targets. The performance of the guidance law is evaluated under noisy measurements and the presence of system lag and its performance is compared with other existing guidance laws.

Fixed-Time Convergence Cooperative Guidance Law Against Maneuvering Target

2021 ◽  
pp. 3975-3986
Author(s):  
Mingjie Zhang ◽  
Jianjun Ma ◽  
Rong Che ◽  
Yalei He
Keyword(s):  
Fixed Time ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Cooperative Guidance

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.

scholarly journals Cooperative Guidance Law against Highly Maneuvering Target with Dynamic Surrounding Attack

2021 ◽  
Vol 2021 ◽  
pp. 1-16
Author(s):  
Zhikai Wang ◽  
Wenxing Fu ◽  
Yangwang Fang ◽  
Zihao Wu ◽  
Mingang Wang
Keyword(s):  
Inverse Method ◽  
Extended State ◽  
Stable Method ◽  
Maneuvering Target ◽  
Guidance Law ◽  
State Observers ◽  
Cooperative Guidance ◽  
Dynamic Inverse ◽  
The Impact ◽  
Guidance Model

In this paper, a new dynamic surrounding attack cooperative guidance law against highly maneuvering target based on decoupled model is proposed. First, a new dynamic surrounding guidance strategy is proposed, and virtual targets are introduced to establish the cooperative guidance model for dynamic surrounding attack. Second, a dynamic inverse method is used to decouple the cooperative guidance model, and extended state observers (ESOs) are introduced to estimate the disturbances caused by target maneuver. Then, the impact time and dynamic surrounding guidance (ITDSG) law against highly maneuvering target is designed based on a prescribed-time stable method and the decoupled model. Finally, numerical simulations are performed to illustrate the superiority and effectiveness of the proposed ITDSG.

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