Fixed-time Guidance Law for Intercepting Maneuvering Targets with 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.

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Adaptive Super-Twisting Algorithm-Based Nonsingular Terminal Sliding Mode Guidance Law

Journal of Control Science and Engineering ◽

10.1155/2020/1058347 ◽

2020 ◽

Vol 2020 ◽

pp. 1-11

Author(s):

Fang Yang ◽

Kuanqiao Zhang ◽

Lei Yu

Keyword(s):

Finite Time ◽

Sliding Mode ◽

Fixed Time ◽

Impact Angle ◽

Terminal Sliding Mode ◽

Finite Time Convergence ◽

Guidance Law ◽

Fast Terminal Sliding Mode ◽

The Impact ◽

Impact Angle Constraint

A nonsingular fast terminal sliding mode guidance law with an impact angle constraint is proposed to solve the problem of missile guidance accuracy and impact angle constraint for maneuvering targets. Aiming at the singularity problem of the terminal sliding mode, a fast terminal sliding mode surface with finite-time convergence and impact angle constraint is designed based on fixed-time convergence and piecewise sliding mode theory. To weaken chattering and suppress interference, a second-order sliding mode supertwisting algorithm is improved. By designing the parameter adaptive law, an adaptive smooth supertwisting algorithm is designed. This algorithm can effectively weaken chattering without knowing the upper bound information of interference, and it converges faster. Based on the proposed adaptive supertwisting algorithm and the sliding mode surface, a guidance law with the impact angle constraint is designed. The global finite-time convergence of the guidance law is proved by constructing the Lyapunov function. The simulation results verify the effectiveness of the proposed guidance law, and compared with the existing terminal sliding mode guidance laws, the proposed guidance law has higher guidance precision and angle constraint accuracy.

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An impact angle constraint integral sliding mode guidance law for maneuvering targets interception

Journal of Systems Engineering and Electronics ◽

10.21629/jsee.2020.01.17 ◽

2020 ◽

pp. 168-184

Author(s):

Wenjie ZHANG ◽

Keyword(s):

Sliding Mode ◽

Impact Angle ◽

Integral Sliding Mode ◽

Guidance Law ◽

Maneuvering Targets ◽

Impact Angle Constraint

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Fixed-Time Disturbance Observer-Based Adaptive Finite-Time Guidance Law Design considering Impact Angle Constraint and Autopilot Dynamics

Complexity ◽

10.1155/2021/8735625 ◽

2021 ◽

Vol 2021 ◽

pp. 1-18

Author(s):

Yunjie Wu ◽

Fei Ma ◽

Xiaofei Yang ◽

Siqi Wang ◽

Xiaodong Liu

Keyword(s):

Finite Time ◽

Disturbance Observer ◽

Sliding Mode ◽

Lyapunov Stability Theory ◽

Fixed Time ◽

Impact Angle ◽

Guidance Law ◽

Adaptive Laws ◽

Impact Angle Constraint ◽

Guidance Problem

This paper aims to establish an effective guidance law to accomplish the interception guidance mission for a missile intercepting a target with impact angle constraint and autopilot dynamics. To achieve this purpose, a fixed-time disturbance observer-based adaptive finite-time guidance law is presented. First, a fixed-time disturbance observer (FTDO) is designed to guarantee the fast estimation of the lumped disturbance caused by the target maneuver. Then, the FTDO-based adaptive integral sliding mode backstepping (AISMB) guidance law is constructed for the interception guidance problem. Besides, several adaptive laws are established to estimate the derivative of virtual control inputs, making the “differential explosion problem” of conventional backstepping get avoided. The finite-time convergence characteristic of the closed-loop system is analyzed by utilizing the Lyapunov stability theory. Finally, the simulation examples are conducted to demonstrate the effectiveness of the proposed composite guidance law.

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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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