Adaptive terminal guidance law with impact-angle constraint

ABSTRACTThis paper proposes an adaptive guidance law for attacking a ground target based on motion camouflage strategy. The coefficients of normal and bi-normal feedback guidance law are given according to the relative motion relationship under Frenet frame. Utilizing the coefficients, the motion camouflage proportional guidance law is derived. In order to improve the initial overload characteristic of the missile, an adaptive feedback coefficient is introduced. Then, the adaptive guidance law is applied to a longitudinal plane interception problem with impact-angle constraint. Finally, the validity of this guidance law for air-to-ground missiles is proved by simulations.

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Impact Angle Constraint Dual-Layer Adaptive Guidance Law With Actuator Faults

IEEE Access ◽

10.1109/access.2020.3003915 ◽

2020 ◽

Vol 8 ◽

pp. 115823-115836

Author(s):

Qiancai Ma ◽

Yi Ji ◽

Zhiqi Niu ◽

Qiuxiong Gou ◽

Liangyu Zhao

Keyword(s):

Impact Angle ◽

Actuator Faults ◽

Guidance Law ◽

Adaptive Guidance ◽

Impact Angle Constraint

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Studies on Multi-Constraints Cooperative Guidance Method Based on Distributed MPC for Multi-Missiles

Applied Sciences ◽

10.3390/app112210857 ◽

2021 ◽

Vol 11 (22) ◽

pp. 10857

Author(s):

Mingyu Cong ◽

Xianghong Cheng ◽

Zhiquan Zhao ◽

Zhijun Li

Keyword(s):

Three Dimensional ◽

Impact Angle ◽

Distributed Model ◽

Guidance Law ◽

Multiple Missiles ◽

Virtual Leader ◽

Prediction Control ◽

The Impact ◽

Terminal Guidance ◽

Impact Angle Constraint

Cooperative terminal guidance with impact angle constraint is a key technology to achieve a saturation attack and improve combat effectiveness. The present study envisaged cooperative terminal guidance with impact angle constraint for multiple missiles. In this pursuit, initially, the three-dimensional cooperative terminal guidance law with multiple constraints was studied. The impact time cooperative strategy of virtual leader missile and follower missiles was designed by introducing virtual leader missiles. Subsequently, based on the distributed model prediction control combined with the particle swarm optimization algorithm, a cooperative terminal guidance algorithm was designed for multiple missiles with impact angle constraint that met the guidance accuracy. Finally, the effectiveness of the algorithm was verified using simulation experiments.

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Novel guidance model and its application for optimal re-entry guidance

The Aeronautical Journal ◽

10.1017/aer.2018.94 ◽

2018 ◽

Vol 122 (1257) ◽

pp. 1811-1825

Author(s):

C.W. Jiang ◽

G.F. Zhou ◽

B. Yang ◽

C.S. Gao ◽

W.X. Jing

Keyword(s):

Three Dimensional ◽

Impact Angle ◽

Guidance Law ◽

Optimal Guidance ◽

Entry Guidance ◽

Independent Variable ◽

Guidance Laws ◽

Terminal Guidance ◽

Impact Angle Constraint ◽

Guidance Model

ABSTRACTAiming at three-dimensional (3D) terminal guidance problem, a novel guidance model is established in this paper, in which line-of-sight (LOS) range is treated as an independent variable, describing the relative motion between the vehicle and the target. The guidance model includes two differential equations that describe LOS’s pitch and yaw motions in which the pitch motion is separately decoupled. This model avoids the inaccuracy of simplified two-dimensional (2D) guidance model and the complexity of 3D coupled guidance model, which not only maintains the accuracy but also simplifies the guidance law design. The application of this guidance model is studied for optimal re-entry guidance law with impact angle constraint, which is presented in the form of normal overload. Compared with optimal guidance laws based on traditional guidance model, the proposed one based on novel guidance model is implemented with the LOS range instead of time-to-go, which avoids the problem of the time-to-go estimation of traditional optimal guidance laws. Finally, the correctness and validity of the guidance model and guidance law are verified by numerical simulation. The guidance model and guidance law proposed in this paper provide a new way for the design of terminal guidance.

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A Terminal Guidance Law Based on Motion Camouflage Strategy of Air-to-Ground Missiles

International Journal of Aerospace Engineering ◽

10.1155/2016/9218754 ◽

2016 ◽

Vol 2016 ◽

pp. 1-7 ◽

Cited By ~ 2

Author(s):

Chang-sheng Gao ◽

Jian-qing Li ◽

Wu-xing Jing

Keyword(s):

Dimensional Space ◽

Three Dimensional ◽

Two Dimensional ◽

Dynamics Model ◽

Proportional Navigation ◽

Guidance Law ◽

Motion Camouflage ◽

Ground Target ◽

Terminal Guidance ◽

Three Dimensional Space

A guidance law for attacking ground target based on motion camouflage strategy is proposed in this paper. According to the relative position between missile and target, the dual second-order dynamics model is derived. The missile guidance condition is given by analyzing the characteristic of motion camouflage strategy. Then, the terminal guidance law is derived by using the relative motion of missile and target and the guidance condition. In the process of derivation, the three-dimensional guidance law could be designed in a two-dimensional plane and the difficulty of guidance law design is reduced. A two-dimensional guidance law for three-dimensional space is derived by bringing the estimation for target maneuver. Finally, simulation for the proposed guidance law is taken and compared with pure proportional navigation. The simulation results demonstrate that the proposed guidance law can be applied to air-to-ground missiles.

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Trajectory shaping guidance law design using constraint-combining multiplier

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410020986371 ◽

2021 ◽

pp. 095441002098637

Author(s):

Min-Guk Seo ◽

Chang-Hun Lee ◽

Tae-Hun Kim

Keyword(s):

Design Method ◽

Impact Angle ◽

State Variables ◽

Flight Trajectory ◽

Potential Significance ◽

Guidance Law ◽

Terminal Constraints ◽

The Impact ◽

Guidance Laws ◽

Impact Angle Constraint

A new design method for trajectory shaping guidance laws with the impact angle constraint is proposed in this study. The basic idea is that the multiplier introduced to combine the equations for the terminal constraints is used to shape a flight trajectory as desired. To this end, the general form of impact angle control guidance (IACG) is first derived as a function of an arbitrary constraint-combining multiplier using the optimal control. We reveal that the constraint-combining multiplier satisfying the kinematics can be expressed as a function of state variables. From this result, the constraint-combining multiplier to achieve a desired trajectory can be obtained. Accordingly, when the desired trajectory is designed to satisfy the terminal constraints, the proposed method directly can provide a closed form of IACG laws that can achieve the desired trajectory. The potential significance of the proposed result is that various trajectory shaping IACG laws that can cope with various guidance goals can be readily determined compared to existing approaches. In this study, several examples are shown to validate the proposed method. The results also indicate that previous IACG laws belong to the subset of the proposed result. Finally, the characteristics of the proposed guidance laws are analyzed through numerical simulations.

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