Finite-time integrated guidance and control system for hypersonic vehicles

2020 ◽  
pp. 014233122094193
Author(s):  
Chong Zhenyu ◽  
Guo Jianguo ◽  
Zhao Bin ◽  
Guo Zongyi ◽  
Lu Xiaodong
Keyword(s):  
Control System ◽  
Finite Time ◽  
Lyapunov Stability Theory ◽  
Hypersonic Vehicles ◽  
Nonlinear Simulation ◽  
Loop Control ◽  
Finite Time Stability ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control

A finite-time integrated guidance and control (IGC) method is proposed in this study for hypersonic vehicles. The IGC dynamic model is initially built by combining the 3D relative kinematics and dynamics equations. Then, by introducing the adaptive control technology and the backstepping approach, an IGC scheme with adaptive parameters is presented to guarantee the finite-time stability of a closed-loop control system on the basis of Lyapunov stability theory. Nonlinear simulation results demonstrate the effectiveness and robustness of the proposed IGC method for hypersonic vehicles compared with other robust IGC methods.

Finite-time convergence of an nth nonlinear system with unmatched disturbance and its application in integrated guidance and control system

2018 ◽  
Vol 09 (05) ◽  
pp. 1850039 ◽  
Author(s):  
Cong Zhang
Keyword(s):  
Control System ◽  
Nonlinear System ◽  
Finite Time ◽  
Recursive Procedure ◽  
Sign Function ◽  
Guidance And Control ◽  
Finite Time Convergence ◽  
Integrated Guidance And Control ◽  
Power Integrator ◽  
And Control

The finite-time convergence problem of an [Formula: see text]th nonlinear system with unmatched disturbance is primarily studied in this paper. During the recursive procedure, a new finite-time controller is designed and proven by adding a sign function and a power integrator. Meanwhile, a [Formula: see text] positive definite and proper Lyapunov function, which satisfies the finite-time Lyapunov stability law, is designed. Finally, the designed finite-time controller is applied to some examples and an application of integrated guidance and control system to test and verify its advantage and practicability.

scholarly journals New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

2018 ◽  
Vol 2018 ◽  
pp. 1-10 ◽  
Author(s):  
Shengjiang Yang ◽  
Jianguo Guo ◽  
Jun Zhou
Keyword(s):  
Control System ◽  
Control Method ◽  
Sliding Mode ◽  
Lyapunov Stability Theory ◽  
Impact Angle ◽  
Guidance And Control ◽  
Ground Target ◽  
Integrated Guidance And Control ◽  
And Control ◽  
The Impact

A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.

Low-order diving integrated guidance and control for hypersonic vehicles

2019 ◽  
Vol 91 ◽  
pp. 96-109 ◽  
Author(s):  
JianHua Wang ◽  
Long Cheng ◽  
YuanWen Cai ◽  
GuoJian Tang
Keyword(s):  
Hypersonic Vehicles ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Low Order

Integrated guidance and control of interceptors with impact angle constraint against a high-speed maneuvering target

2019 ◽  
Vol 233 (14) ◽  
pp. 5192-5204
Author(s):  
Guanjie Hu ◽  
Jianguo Guo ◽  
Jun Zhou
Keyword(s):  
Control System ◽  
High Speed ◽  
Control Method ◽  
Impact Angle ◽  
Adaptive Sliding Mode Control ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Impact Angle Constraint

An integrated guidance and control method is investigated for interceptors with impact angle constraint against a high-speed maneuvering target. Firstly, a new control-oriented model with impact angle constraint of the integrated guidance and control system is built in the pitch plane by combining the engagement kinematics and missile dynamics model between the interceptor and target. Secondly, the flight path angle of the target is estimated by extended Kalman filter in order to transform the terminal impact angle constraint into the terminal line-of-sight angle constraint. Thirdly, a nonlinear adaptive sliding mode control law of the integrated guidance and control system is designed in order to directly obtain the rudder deflection command, which eliminates time delay caused by the traditional backstepping control method. Then the Lyapunov stability theory is used to prove the stability of the whole closed-loop integrated guidance and control system. Finally, the simulation results confirm that the integrated guidance and control method proposed in this paper can effectively improve the interception performance of the interceptor to a high-speed maneuvering target.

scholarly journals A Low-Order Partial Integrated Guidance and Control Scheme for Diving Hypersonic Vehicles to Impact Ground Maneuver Target

2021 ◽  
Vol 2021 ◽  
pp. 1-12
Author(s):  
Tong An ◽  
JianHua Wang ◽  
YuLong Pan ◽  
HaiShan Chen
Keyword(s):  
Analytical Model ◽  
Sliding Mode ◽  
Design Method ◽  
Hypersonic Vehicle ◽  
Hypersonic Vehicles ◽  
Dynamic Surface ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Low Order

In this article, a low-order partial integrated guidance and control (PIGC) design method is proposed for diving hypersonic vehicles to impact ground maneuver target. A three-channel analytical model of body rates is deduced based on acceleration components of the hypersonic vehicle. By combining the analytical model of body rates and relative dynamic model between the hypersonic vehicle and target, three-channel commands of body rates are directly generated based on the extended state observer (ESO) technique, sliding mode control approach, and dynamic surface control theory in the guidance subsystem. In the attitude control subsystem, a sliding mode controller is designed to track the commands of body rates and generate commands of control surface fin deflections. By making full use of acceleration information of the hypersonic vehicle measured by the mounted accelerometer, the proposed PIGC design method provides a novel solution to compensate the unknown acceleration of the ground maneuver target. Besides, the order of design model is also reduced, and the design process is simplified. The effectiveness and robustness of the PIGC design method are verified and discussed by 6DOF simulation studies.

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