Integrated guidance and control for hypersonic vehicles in dive phase with multiple constraints

2016 ◽  
Vol 53 ◽  
pp. 103-115 ◽  
Author(s):  
JianHua Wang ◽  
LuHua Liu ◽  
Tun Zhao ◽  
GuoJian Tang
Keyword(s):  
Hypersonic Vehicles ◽  
Multiple Constraints ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
And Control

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

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.

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.

Integral barrier Lyapunov functions-based integrated guidance and control design for strap-down missile with field-of-view constraint

2021 ◽  
pp. 014233122098132
Author(s):  
Bin Zhao ◽  
Zhenxin Feng ◽  
Jianguo Guo
Keyword(s):  
Sliding Mode ◽  
State Equation ◽  
Field Of View ◽  
Feedback Form ◽  
Theoretical Derivation ◽  
Guidance And Control ◽  
Integrated Guidance And Control ◽  
Twisting Algorithm ◽  
And Control ◽  
Special Time

The problem of the integrated guidance and control (IGC) design for strap-down missile with the field-of-view (FOV) constraint is solved by using the integral barrier Lyapunov function (iBLF) and the sliding mode control theory. Firstly, the nonlinear and uncertainty state equation with non-strict feedback form for IGC design is derived by using the strap-down decoupling strategy. Secondly, a novel adaptive finite time disturbance observer is proposed to estimate the uncertainties based on an improved adaptive gain super twisting algorithm. Thirdly, the special time-varying sliding variable is designed and the iBLF is employed to handle the problem of FOV constraint. Theoretical derivation and simulation show that the IGC system is globally uniformly ultimately bounded and the FOV angle constraint is also guaranteed not only during the reaching phase but also during the sliding mode phase.

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