摘要
针对高超声速空地导弹多约束高精度末制导的基本需求,在三维解耦的俯仰平面和转弯平面上分别设计制导律。在综合考虑脱靶量、落角、入射角等多种约束条件后,运用最优控制构造的最优制导律设计了一种三维最优变结构制导律,接着利用梯度自适应下降法和T-S模型改进了速度约束控制。最后通过典型弹道的结果显示该制导律能够满足多约束高精度制导的需要,具有良好的弹道性能。
In order to study the terminal precision guidance of the hypersonic air-to-surface missile with constraints, the guidance law was designed respectively in the pitching plane and swerve plane. After the constraints of miss-distance, impact angular and orientation angular were considered synthetically, and the three-dimensional optimal variable structure guidance law was derived from the optimal control. Moreover, the traditional algorithm of max-velocity control was also mended by the adaptive gradient method and Takagi-Sugeno fuzzy system. Through the simulation test of the characteristic trajectory, the optimal variable structure guidance law with constraints is not only satisfied with the precision guidance in the multi-constraint conditions, but also has excellent trajectory in terminal guidance.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2007年第3期126-130,共5页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(60374006)
关键词
高超声速空地导弹
制导律
多约束
最优控制
变结构控制
模糊控制
hypersonic Mr-to-surface missile
guidance law
constraints
optimal control
variable structure control
fuzzy control
