固体火箭技术Issue(3)：285-290,6.DOI:10.7673/j.issn.1006-2793.2014.03.001
带落角约束与控制约束的纵向制导律
Longitudinal guidance law with constraints on impact angle and control
摘要
Abstract
A certain impact angle and the observation of the control constraint are desired when a land-attack-missile attacks a stationary ground target.To address this problem,a longitudinal guidance law with constraints on the impact angle and the control was presented.Based on nonlinear center of mass motion equations of the missile,a linear model for guidance law design was derived by coordinate transformation.The guidance problem was converted to a stabilization problem of a linear time-invariance(LTI)system with control saturation.To stabilize the LTI system,a low gain state feedback law was designed utilizing the parametric Lyapunov e-quation approach.And a longitudinal guidance law with a design parameter was derived.A method tuning the design parameter of the guidance law was proposed.By tuning the parameter online,sight angle converged to the desired impact angle in finite time.And the control constraint was observed during flight.Simulation results show that the guidance law is adaptive to various missions and has a potential for engineering applications.关键词
制导律/落角约束/控制饱和/参量李雅普诺夫方程Key words
guidance law/impact angle constraint/control saturation/parametric Lyapunov equation分类
航空航天引用本文复制引用
董晨,晁涛,王松艳,杨明..带落角约束与控制约束的纵向制导律[J].固体火箭技术,2014,(3):285-290,6.基金项目
国家自然科学基金创新研究群体（61021002）；中央高校基本科研业务费专项资金（HIT．NSRIF．2014036）；重点实验室开放基金（HIT．KLOF．2013081）。 （）
