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terminal angular constraint Integrated Guidance and Control for Flexible Hypersonic Vehicle with Dead-Zone Input Nonlinearity

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Journal of Beijing Institute of Technology 2020年第4期29卷 489-503页

作者： Hewei Zhao Detection Guidance and Control Teaching Research Section Naval Aviation UniversityYantai 264001ShandongChina

This paper presents an integrated guidance and control model for a flexible hypersonic vehicle with terminal angular *** integrated guidance and control model is bounded and the dead-zone input nonlinearity is considered in the system *** line of sight angle,line of sight angle rate,attack angle and pitch rate are involved in the integrated guidance and control *** controller is designed with a backstepping method,in which a first order filter is employed to avoid the differential *** full tuned radial basis function(RBF)neural network(NN)is used to approximate the system dynamics with robust item coping with the reconstruction errors,the exactitude model requirement is reduced in the controller *** the last step of backstepping method design,the adaptive control with Nussbaum function is used for the unknown dynamics with a time-varying control gain *** uniform ultimate boundedness stability of the control system is *** simulation results validate the effectiveness of the controller design.

关键词： hypersonic vehicle terminal angular constraint dead-zone input nonlinearity full tuned radial basis function(RBF)neural network(NN) integrated guidance and control

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Adaptive Multiple Sliding Surface Control for Integrated Missile Guidance and Autopilot with terminal angular constraint

Adaptive Multiple Sliding Surface Control for Integrated Mis...

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第二十九届中国控制会议

作者： WEI Yiyin,HOU Mingzhe,DUAN Guang-Ren Harbin Institute of Technology,Harbin 150001,P.R.China

Integrated guidance and control for homing missiles with terminal angular constraint is considered.A time-varying integrated guidance and control model with unmatched uncertainties is *** order to solve the multiple states regulation problem of such a system,an adaptive multiple sliding surface control algorithm is *** is proved that the proposed feedback controller can drive the missile to intercept the target accurately with a desired terminal attitude angle,and ensure the stability of the missile dynamics *** 6DOF nonlinear missile simulation results demonstrate the feasibility of the proposed integrated guidance and control design scheme.

关键词： Integrated Guidance and Control terminal angular constraint Unmatched Uncertainty Adaptive Control Multiple Sliding Surface Control

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