固体火箭技术2011，Vol.34Issue(6)：687-692,6.
带落角约束的自适应比例制导律
Adaptive proportional navigation with terminal angular constraint
摘要
Abstract
A missile motion equation with terminal angular constraint was derived and then adaptive proportional guidance laws adopting adaptive navigation constant were designed to realize effective interception of maneuvering target with certain terminal angular constraint. That is through particular derivation of missile-target motion model and the geometry relationships of angular constraint , an adaptive adjustable function was derived and then the adaptive proportional guidance law based on missile kinematics was formed with feedback form. It is proven that the proposed guidance law could meet the requirements of successful interception with arbitrary attack angle. Another adaptive proportional guidance law based on realistic model was derived after revising the previous law. Simulations were made for air-to-ground and ground-to-ground missiles in order to display the fundamental advantages and practical values. Simulation results show that the proposed guidance laws have better guidance effect and could offer some references for engineering application.关键词
导弹/落角约束/机动目标/自适应比例导引Key words
missile/terminal angular constraint/maneuvering target/adaptive proportional navigation分类
航空航天引用本文复制引用
张旭,雷虎民,曾华,肖增博,叶继坤..带落角约束的自适应比例制导律[J].固体火箭技术,2011,34(6):687-692,6.基金项目
航空科学基金(20090196005,20100196002). （20090196005,20100196002）
