Three-dimensional cooperative guidance and control law for multiple reentry missiles with time-varying velocities

Wang, Xiaofang; Zhang, Yiwei; Liu, Dong‐Ze; He, Ming

doi:10.1016/j.ast.2018.07.011

Cited by 25 publications

(15 citation statements)

References 18 publications

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“…To deal with it, the effect of engine dynamics modeling error can be incorporated into the expression of d x . Although acceleration tracking controller design for multiple missiles is presented in [24], [25], the proposed cooperative controller is not applicable in that the explicit knowledge of the drag coefficient and the consideration of turbojet engine thrust were absent.…”

Section: Remarkmentioning

confidence: 99%

“…Only 3 DOF cooperative problems were considered in [22]. Although 6 DOF cooperative problems were investigated in [24], [25], explicit knowledge of the drag coefficient was required in [24], while controller involving turbojet engine thrust was not considered in [25] with respect to axial overload control. It should be noted that [26] only focused on the mid-course guidance of cooperative attack of multiple missiles formation, and cooperative engagement process involving dynamic characteristics was ignored.…”

Section: Introductionmentioning

confidence: 99%

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Multiple Tactical Missiles Cooperative Attack With Formation-Containment Tracking Requirement Along the Planned Trajectory

Chen

Zhang

et al. 2020

IEEE Access

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This paper studies the cooperative guidance and control problems with formation-containment tracking requirement under directed topologies for multiple tactical missiles. The states of the formationleaders can not only keep a parallel triangle formation but also make tracks for the state trajectory generated by the tracking-leader, while the states of followers converge to the convex hull formed by those of the formation-leaders. Firstly, an integrated cooperative guidance and control framework is proposed, and combat missions are distinguished in line with tactical missiles rewarded different functions in practical applications. Then, a terminal slide mode guidance law with impact angle is presented in three-dimensional space, which ensures attack missile to attack the target in finite time. Sufficient conditions for multiple tactical missiles to achieve formation-containment tracking are derived. On the basis of Lyapunov theory, it is shown that the expected formation-containment tracking can be realized by reconnaissance and decoy missiles in the presence of the tracking-leaders' unknown control input. In addition, in the case of unknown drag force, the six degrees of freedom missile controller is designed by combining genetic algorithm and disturbance observer to dynamically adjust the rudder deflection and thrust, ensuring stable tracking of overload command during cooperative attack. Finally, numerical simulations validate the feasibility and effectiveness of the proposed results. INDEX TERMS Cooperative guidance and control framework, formation-containment tracking, terminal slide mode guidance law, genetic algorithm, disturbance observer.

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Section: Remarkmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multiple Tactical Missiles Cooperative Attack With Formation-Containment Tracking Requirement Along the Planned Trajectory

Chen

Zhang

et al. 2020

IEEE Access

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“…An outer loop re-entry guidance law with online trajectory reshaping capability is designed and a novel re-entry attitude control strategy is proposed based on a sliding mode controller (SMC) and disturbance observer. A three-dimensional partial IGC law is proposed in [12] for cooperative flight of multiple hypersonic re-entry missiles. An IGC scheme combining with the virtual target and the filter for fixed-trim RHV is proposed in [13].…”

Section: Introductionmentioning

confidence: 99%

A Novel IGC Scheme for RHV with the Capabilities of Online Aerodynamic Coefficient Estimation and Trajectory Generation

Wang

Zhang

2021

Mathematics

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A novel integrated guidance and control (IGC) scheme for a Re-entry Hypersonic Vehicle (RHV) is proposed with the capabilities of online aerodynamic coefficient estimation based on an Unscented Kalman Filter and online trajectory generation based on the Gaussian pseudospectral method. A linear quadratic regulator is adopted for trajectory tracking guidance and a second-layer sliding mode controller is designed for attitude control. The variation of lift and drag coefficients are modeled and estimated online, based on which a new trajectory can be generated. The commands of trajectory generation are set as moments of actuators and their extremums pose more constraints on the rate and acceleration of flow angles. Comprehensive simulations are conducted and comparable IGC performances with normal conditions are obtained under large aerodynamic coefficient errors according to online generated trajectory, which proves the effectiveness and advantages of the proposed IGC scheme.

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“…In centralized cooperative guidance, there is one central node in the entire cluster that can interact with all vehicles, while in distributed cooperative guidance the vehicles in the cluster only need to exchange information with several neighbors. Centralized cooperative guidance usually designs a two-layer centralized cooperative guidance architecture based on coordination variables [23,24]. And distributed cooperative guidance usually adopts a multiagent consensus control algorithm to deal with coordination variables [25][26][27][28].…”

Section: Introductionmentioning

confidence: 99%

Distributed Analytical Formation Control and Cooperative Guidance for Gliding Vehicles

Jia

Wang

et al. 2020

International Journal of Aerospace Engineering

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This paper addresses the analytical formation control and cooperative guidance problem for multiple hypersonic gliding vehicles under distributed communication. The gliding flight of the hypersonic gliding vehicle is divided into formation control phase and time coordination phase. In formation control phase, based on the idea of path tracking, the formation controller is designed using the second-order consensus protocol with normal positions as the coordination variables. In time coordination phase, based on the quasi-equilibrium gliding condition and the assumption of uniform deceleration motion, the analytical expression of time to go is derived. Then, the cooperative guidance method is developed using the first-order consensus protocol with time to go as the coordination variable. The proposed method takes full consideration of the characteristics of hypersonic gliding vehicle, such as complex nonlinear dynamics, no thrust, and quasi-equilibrium gliding condition, and no online numerical iteration is needed, which is well applicable for hypersonic gliding vehicles. Simulation results demonstrate the effectiveness of the formation control and cooperative guidance method.

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Three-dimensional cooperative guidance and control law for multiple reentry missiles with time-varying velocities

Cited by 25 publications

References 18 publications

Multiple Tactical Missiles Cooperative Attack With Formation-Containment Tracking Requirement Along the Planned Trajectory

Multiple Tactical Missiles Cooperative Attack With Formation-Containment Tracking Requirement Along the Planned Trajectory

A Novel IGC Scheme for RHV with the Capabilities of Online Aerodynamic Coefficient Estimation and Trajectory Generation

Distributed Analytical Formation Control and Cooperative Guidance for Gliding Vehicles

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