Advanced guidance laws for acceleration-constrained missile, randomly maneuvering target and noisy measurements

1996 ◽  
Vol 32 (1) ◽  
pp. 456-464 ◽  
Author(s):  
I. Rusnak
Keyword(s):  
Maneuvering Target ◽  
Noisy Measurements ◽  
Guidance Laws

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.

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.

scholarly journals Cooperative guidance laws for maneuvering target interceptions

2013 ◽  
Vol 46 (19) ◽  
pp. 301-306
Author(s):  
H. Piet-Lahanier ◽  
A. Kahn ◽  
J. Marzat
Keyword(s):  
Maneuvering Target ◽  
Cooperative Guidance ◽  
Guidance Laws

End-game guidance laws for dual-control missiles

2005 ◽  
Vol 219 (2) ◽  
pp. 157-170 ◽  
Author(s):  
T Shima ◽  
O M Golan
Keyword(s):  
Flight Control ◽  
Performance Criterion ◽  
Guidance System ◽  
Single Shot ◽  
Dual Control ◽  
Monte Carlo Simulation Study ◽  
Guidance Law ◽  
Noisy Measurements ◽  
And Control ◽  
Guidance Laws

New guidance laws derived for a dual-control missile are studied. Their performance is compared with that of a conventional guidance system with flight control that distributes the commands among the two control channels. A Monte Carlo simulation study is performed where the target executes random evasive manoeuvres. The interceptor, represented by linear high-order manoeuvring dynamics with bounded forward and aft controls, acquires noisy measurements and uses a state estimator. Using the single-shot kill probability as a performance criterion, the superiority of the new guidance and control architecture is shown. It is also shown that the best performance is obtained by the bounded controls differential game guidance law. Sensitivity to the selection of the interceptor first-order time constant, a design parameter in the guidance law derivation, is also investigated.

Three-dimensional sliding mode guidance law for maneuvering target with prescribed performance and input saturation

2020 ◽  
pp. 014233122097202
Author(s):  
Meng-chen Ma ◽  
Li-Guo Tan ◽  
Shen-min Song
Keyword(s):  
Actuator Saturation ◽  
Sliding Mode ◽  
Error Function ◽  
Tracking Error ◽  
Input Saturation ◽  
Three Dimensional ◽  
Prescribed Performance ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Guidance Laws

The three-dimensional sliding mode guidance laws with prescribed performance and saturation actuator are proposed for maneuvering target. The proposed guidance laws can ensure the line of sight (LOS) angle converges according to the prescribed performance with actuator saturation and the convergence rate, the steady state error and the maximum overshoot can be preset in advance. A novel transformed error function is designed by combining the LOS tracking error with the performance constraint function. Then, to further solve the problem of input saturation, the saturation function and auxiliary system are introduced. Additionally, this paper discusses the problem whereby the upper bound of the aggregate uncertainty, including the target information, is unavailable. An adaptive sliding mode guidance law with prescribed performance is presented for this scenario. Experiments comparisons are conducted with other forms of guidance laws. Simulation results show that the guidance laws proposed in this paper achieve effective performance.

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.

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