Integrated guidance and control law for cooperative attack of multiple missiles

2015 ◽  
Vol 42 ◽  
pp. 1-11 ◽  
Author(s):  
Xiaofang Wang ◽  
Yiyu Zheng ◽  
Hai Lin
Keyword(s):  
Control Law ◽  
Guidance And Control ◽  
Multiple Missiles ◽  
Integrated Guidance And Control ◽  
And Control

Integrated Guidance and Control of Missile Using Subspace Stabilization Method

2012 ◽  
Vol 490-495 ◽  
pp. 1161-1165 ◽  
Author(s):  
Rui Sheng Sun ◽  
Peng Yun Liu ◽  
Jian Ping Shen
Keyword(s):  
Control Method ◽  
Integrated System ◽  
Control Law ◽  
Stabilization Method ◽  
Guidance And Control ◽  
Stabilization Control ◽  
Dynamic Tracking ◽  
Integrated Guidance And Control ◽  
And Control ◽  
Angle Tracking

Integrated guidance and control law is developed for high-maneuvering missile in order to minimize the uncertain dynamic couple between guidance loop and control loop. After building up the integrated model of guidance and control through combining guidance equations and autopilot equations, this paper puts forward a type of subspace control law with attack-angle tracking by using subspace stabilization control method. Finally, the simulation results by an example, which designs the integrated controller for a terminal guided missile, are presented to reveal that the integrated system has good dynamic-tracking performance.

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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