scholarly journals Profile-Tracking-Based Adaptive Guidance Law against Maneuvering Targets

2019 ◽  
Vol 2019 ◽  
pp. 1-17
Author(s):  
Jingshuai Huang ◽  
Hongbo Zhang ◽  
Guojian Tang ◽  
Weimin Bao
Keyword(s):  
Convergence Rate ◽  
Sliding Mode ◽  
Tracking Error ◽  
Small Neighborhood ◽  
Terminal Sliding Mode ◽  
Control Approach ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Adaptive Guidance ◽  
The One

For the terminal guidance problem of a missile intercepting a maneuvering target, a profile-tracking-based adaptive guidance law is proposed with inherent continuity in this paper. To flexibly and quantitatively control the convergence rate of the line-of-sight rate, a standard tracking profile is designed where the convergence rate is analytically given. Then, a nonsingular fast terminal sliding-mode control approach is used to track the profile. By estimating the square of the upper bound of target maneuver, an adaptive term is constructed to compensate the maneuver. Therefore, no information of target acceleration is required in the derived law. Stability analysis shows that the tracking error can converge to a small neighborhood of zero in finite time. Furthermore, a guidance-command-conversion scheme is presented to convert the law into the one appropriate for endoatmospheric interceptions. Simulation results indicate that the proposed law is effective and outperforms existing guidance laws.

A novel adaptive second-order nonsingular terminal sliding mode guidance law design

2020 ◽  
Vol 234 (16) ◽  
pp. 2263-2273
Author(s):  
Shuai Xu ◽  
Min Gao ◽  
Dan Fang ◽  
Yi Wang ◽  
Baochen Li
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Initial Conditions ◽  
Dynamic Control ◽  
Small Neighborhood ◽  
Lyapunov Stability Theory ◽  
Second Order ◽  
Terminal Sliding Mode ◽  
Guidance Law ◽  
Nonsingular Terminal Sliding Mode

Aiming at the problem of missile attacking ground target in pitch plane, combined with a composite fast nonsingular terminal sliding mode, a new adaptive finite-time stable guidance law with attack angle constraint is designed based on the second-order sliding mode control. The improved extended state observer is used to estimate the uncertainties and compensate the control quantity, and the dynamic control gains are designed to avoid the problem about “excessive estimation” of the parameter upper limit. According to the Lyapunov stability theory, it is proved that the system states can converge into a small neighborhood near the equilibrium point in a finite time. Monte Carlo simulation is carried out by randomly generating initial conditions, which proves that the guidance law has strong adaptability to different initial conditions and has good guidance precision.

A novel nonsingular integral terminal sliding mode control scheme in epilepsy treatment

2021 ◽  
pp. 014233122110507
Author(s):  
Moshu Qian ◽  
Zhen Zhang ◽  
Guanghua Zhong ◽  
Cuimei Bo
Keyword(s):  
Closed Loop ◽  
Controller Design ◽  
Sliding Mode ◽  
Tracking Error ◽  
Lyapunov Theory ◽  
Terminal Sliding Mode ◽  
Loop Control ◽  
Control Approach ◽  
Control Scheme ◽  
Loop Control System

In this paper, a closed-loop brain stimulation control problem is investigated using the nonsingular integral terminal sliding mode (NITSM) control approach. First, the thalamocortical model of epilepsy seizure is given, which is composed of the cortical PY-IN subnetwork and the subcortical RE-TC subsystem. Then, a nonsingular integral terminal sliding mode surface is designed utilizing the derived output tracking error, and the stability of the sliding mode dynamics is proved by Lyapunov approach. Furthermore, a disturbance observer (DOB) based NITSM controller design approach is proposed for the established thalamocortical model, and the reachability of the closed-loop control system under the designed controller is analyzed using Lyapunov theory. Finally, simulation results are given to illustrate the effectiveness and superiority of the designed control scheme.

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.

Cooperative guidance laws against highly maneuvering target with impact time and angle

2021 ◽  
pp. 095441002110260
Author(s):  
Zhikai Wang ◽  
Yangwang Fang ◽  
Wenxing Fu ◽  
Zihao Wu ◽  
Mingang Wang
Keyword(s):  
Sliding Mode Control ◽  
Sliding Mode ◽  
Terminal Sliding Mode ◽  
Maneuvering Target ◽  
Mode Control ◽  
Guidance Law ◽  
Cooperative Guidance ◽  
Multi Agent ◽  
Fast Power ◽  
Guidance Model

To address the issue that multiple missiles intercepting a highly maneuvering target simultaneously with desired angles, a novel cooperative guidance law based on the decoupled model in the line-of-sight (LOS) and normal LOS direction is proposed in LOS frame. However, there is control coupling in the two directions of the cooperative guidance model. In this article, we first decouple the guidance model and then separately design estimation decouple cooperative guidance law in two directions based on the decoupled model. The guidance law component in the LOS direction is designed with the integral sliding mode control and multi-agent consensus theory, where the combining disturbance is compensated by an adaptively estimated term. The guidance law component in the normal LOS direction is designed based on nonsingular terminal sliding mode control with fast power reaching law, and a nonlinear disturbance observer is introduced to estimate the combining disturbance. Then, the finite time convergence of time-to-go and LOS angle is proved. Finally, numerical simulation results demonstrate the effectiveness and superiority of the proposed cooperative guidance law.

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 Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

2020 ◽  
Vol 38 (6) ◽  
pp. 1257-1265
Author(s):  
Zhengyu Guo ◽  
Chaolei Wang ◽  
Hang Qian ◽  
Zhiguo Han ◽  
Jingxian Zhang
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Impact Angle ◽  
Attack Angle ◽  
Lateral Acceleration ◽  
Terminal Sliding Mode ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Guidance

A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.

scholarly journals Adaptive compound second-order terminal sliding mode control for the longitudinal attitude control of the fully submerged hydrofoil vessel

2019 ◽  
Vol 11 (12) ◽  
pp. 168781401989563 ◽  
Author(s):  
Sheng Liu ◽  
Hongmin Niu ◽  
Lanyong Zhang ◽  
Xiaojie Guo
Keyword(s):  
Sliding Mode Control ◽  
Sliding Mode ◽  
Tracking Error ◽  
Small Neighborhood ◽  
Second Order ◽  
Terminal Sliding Mode Control ◽  
Terminal Sliding Mode ◽  
Fast Tracking ◽  
Mode Control ◽  
The Stability

Due to the ever-existing environmental disturbance of ocean wave and nonlinear of the system, it is difficult to obtain a satisfying control performance for the longitudinal attitude and desired height tracking of the fully submerged hydrofoil vessel. To solve such problems, an adaptive compound second-order terminal sliding mode controller is proposed. First, a combination of the complementary sliding mode surface and second-order terminal sliding mode control is introduced. Therefore, the closed system is uniformly ultimately bounded, and the steady-state errors converge to a small neighborhood of equilibrium point. Second, the chattering problem in an actual controller is solved by eliminating the sign function contained in the controller after integration without influencing the stability of the closed-loop system. Besides, a revised adaptive radial basis function neural network is introduced to estimate the derivative of the unknown environmental disturbances without the prior information of the disturbance. Finally, the stability of the system is proved by the Lyapunov stability theory. Numerical experimental results demonstrate that the proposed method possesses fast tracking ability and can decrease the stabilization error and the tracking error simultaneously.

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