Design of integrated smooth sliding mode of guidance and control for intercepting the hypersonic aircraft

2020 ◽  
pp. 002072092094444
Author(s):  
Qin Zhong ◽  
Yonghua Fan ◽  
Jie Yan ◽  
Xiaofeng Zhang
Keyword(s):  
Sliding Mode ◽  
Variable Structure ◽  
Side Window ◽  
Guidance And Control ◽  
Near Space ◽  
Guidance Law ◽  
Hypersonic Aircraft ◽  
Aerodynamic Control ◽  
Sliding Mode Variable Structure ◽  
And Control

A strategy of intercepting the near-space hypersonic aircraft is proposed, which is based on infrared window guidance, change the guidance law from side window constraint to the fixed lead angle, the sliding mode variable structure guidance law with prefix angle constraint is designed. First, setting up the dynamic model for the end of interceptor with direct force/aerodynamic control, deriving the integrated mathematical model of interceptor’s longitudinal guidance and control. Then, by using smooth sliding mode control, the interceptor’s variable structure guidance law with prefix angle constraint is designed. Last, the simulation results show that the designed guidance law can achieve high precision interception for hypersonic vehicle.

scholarly journals Guidance Law and Neural Control for Hypersonic Missile to Track Targets

2016 ◽  
Vol 2016 ◽  
pp. 1-10 ◽  
Author(s):  
Wenxing Fu ◽  
Binbin Yan ◽  
Xiaofei Chang ◽  
Jie Yan
Keyword(s):  
Neural Control ◽  
Controller Design ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Laws ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Control Command ◽  
And Control

Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC) method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

scholarly journals Integrated Guidance and Control Method for the Interception of Maneuvering Hypersonic Vehicle Based on High Order Sliding Mode Approach

2015 ◽  
Vol 2015 ◽  
pp. 1-19 ◽  
Author(s):  
Kang Chen ◽  
Bin Fu ◽  
Yuening Ding ◽  
Jie Yan
Keyword(s):  
Fourth Order ◽  
Control Method ◽  
Sliding Mode ◽  
High Order ◽  
Control Input ◽  
Guidance And Control ◽  
Near Space ◽  
Sliding Manifold ◽  
Integrated Guidance And Control ◽  
And Control

This paper focuses on the integrated guidance and control (IGC) method applied in the interception of maneuvering near space hypersonic vehicles using the homogeneous high order sliding mode (HOSM) approach. The IGC model is derived by combining the target-missile relative motion and dynamic equations. Then, a fourth-order sliding mode controller is implemented in the augmented IGC model. To estimate the high order derivatives of the sliding manifold which is required in the HOSM method, an Arbitrary Order Robust Exact Differentiator is presented. At last, the idea of virtual control is introduced to alleviate the chattering of the control input without using any saturation functions which may lead to a loss of the robustness. And the stability of the closed-loop system with presented fourth-order homogeneous HOSM controller is also proved theoretically. Finally, simulation results are provided and analyzed to demonstrate the effectiveness of the proposed method in three typical engagement scenarios.

Duffing Chaotic System Stability Control Based on Sliding Mode Control

2012 ◽  
Vol 605-607 ◽  
pp. 1639-1642
Author(s):  
Ding Ma
Keyword(s):  
Chaotic System ◽  
Control Method ◽  
Sliding Mode ◽  
Variable Structure ◽  
Stability Control ◽  
System Stability ◽  
Terminal Sliding Mode ◽  
Sliding Mode Variable Structure ◽  
The Stability ◽  
And Control

Considering the Duffing chaotic system, the problem of stability control based on the terminal sliding mode variable structure is studied. A new terminal sliding mode surface and control law are designed. On this basis, the stability of closed-loop system is analyzed. Simulation results show the effectiveness of the control method.

Control Strategy Used on UAV Motion System

2014 ◽  
Vol 1028 ◽  
pp. 186-190
Author(s):  
Hong Cheng Zhou ◽  
Zhi Peng Jiang
Keyword(s):  
Control Strategy ◽  
Control Method ◽  
Sliding Mode ◽  
Variable Structure ◽  
Control Law ◽  
Low Velocity ◽  
Structure Control ◽  
Motion System ◽  
Sliding Mode Variable Structure ◽  
And Control

The servo control methods of 6-DOF motion configuration are researched. Based on analysis for characteristic of the motion configuration, the control strategy and control law used on the motion control system are presented. The controller in velocity tracking loop and location loop are respectively designed by frequency correcting method and normal control method which belongs to classical control theory. Sliding mode variable structure control method is presented for location control law designing, against the super low velocity creep caused by friction disturbance, so that the problem of location control loop low velocity creeping is solved, and a simulating experimentation demonstrate the effectiveness of the proposed approach.

Integrated Guidance, Control and Maneuver for Anti-Vessel Missiles Based on Backstepping Method

2011 ◽  
Vol 69 ◽  
pp. 126-131
Author(s):  
Cong Ying Li ◽  
Jin Yong Yu ◽  
Lei Han ◽  
Wen Guang Zhang
Keyword(s):  
Sliding Mode ◽  
Integrated Design ◽  
Control Law ◽  
Backstepping Method ◽  
Guidance Control ◽  
Guidance And Control ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
And Control ◽  
Accuracy Performance

Integrated guidance, control and maneuver for anti-vessel missiles against vessel targets was studied. Firstly, the integrated guidance and autopilot model of the yaw plane was formulated, the guidance and control law was designed based on the backstepping method and sliding mode control theory. For the unavailable information of the vessel target, an estimating method was given. Integration of guidance and maneuver was realized based on a new guidance law. Finally, to verify the effectiveness and rightness of the integrated design scheme, the simulation of some anti-vessel missile against maneuvering targets had been made, the simulation results showed that high accuracy performance of guidance and control system can be got.

scholarly journals Design of Stochastic Sliding Mode Variable Structure Guidance Law based on Adaptive EKF

2011 ◽  
Vol 23 ◽  
pp. 276-283 ◽  
Author(s):  
Zhao Hui ◽  
Liu Wan Jun ◽  
Yang Jin Hui ◽  
Xuan Yong Bo
Keyword(s):  
Sliding Mode ◽  
Variable Structure ◽  
Guidance Law ◽  
Sliding Mode Variable Structure
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