摘要
针对导弹在三维场景中以期望角度拦截加速度未知的机动目标问题,提出了一种考虑角度约束的三维拦截制导律。首先,建立了三维弹目非线性拦截制导模型;其次,设计了一种全滑动模态的积分滑模面,省去了传统滑模制导律中的滑模趋近阶段,有效地降低了拦截制导过程中的能量消耗;而后,基于设计的积分滑模面和二阶滑模控制理论,在弹目视线法向和侧向上分别设计了一种带角度约束的三维积分二阶滑模拦截制导律,有效地抑制了抖振现象,同时对目标机动造成的未知干扰进行了在线补偿;此外,对所设计算法进行了严格的Lyapunov稳定性数学证明;最后,数值仿真结果验证了本文所提三维拦截制导律的有效性、优越性以及抗干扰的鲁棒性。
Aiming at the problem that missiles intercept a maneuvering target with unknown acceleration information,a three-dimensional interception guidance law with impact angle constraints is proposed.Firstly,a three-dimensional nonlinear interception guidance model is investigated.Second,a global integral sliding mode surface is designed,which omits the reaching phase in the traditional sliding mode guidance laws and effectively reduces energy consumption in the interception guidance process.Then,based on the designed integral sliding mode surface and second-order sliding mode control theory,a three-dimensional integral second-order sliding mode interception guidance law with impact angle constraints is designed in the normal and lateral directions to the line of sight(LOS),effectively suppressing the chattering phenomenon and compensating for unknown disturbances caused by target maneuvering online.In addition,the strict mathematical proof of Lyapunov stability is made for the designed guidance law.Finally,the numerical simulation results validate the effectiveness,superiority,and anti-interference robustness of the proposed three-dimensional interception guidance law.
作者
尤浩
常新龙
赵久奋
石学乾
YOU Hao;CHANG Xinlong;ZHAO Jiufen;SHI Xueqian(College of Missile Engineering,Rocket Force University of Engineering,Xi'an 710025,China)
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2024年第4期590-602,共13页
Journal of Astronautics
关键词
导弹
角度约束
三维拦截制导
积分滑模面
机动目标
Missiles
Impact angle constraints
Three-dimensional interception guidance
Integral sliding mode surface
Maneuvering target
