摘要
针对大气层内姿控式直接力/气动力复合控制导弹,提出了一种基于模糊控制理论的复合控制算法,并为不同配置的姿控发动机设计了相应的点火实现方案。首先建立了复合控制导弹的数学模型;然后以俯仰通道为例设计了模糊控制器跟踪该通道的过载指令,选择合适的论域变换因子使输入输出量的论域自适应调节,并且设计了复合控制分配算法,实时分配2个子系统的控制权限;最后为增强算法的实用性,分别设计了有限时间收敛二阶微分器、滚转稳定导弹的PWPF调制器及改进的旋转弹叠加点火算法。仿真实验证明了复合控制器的有效性。
Concerning the attitude control type of lateral thrust/aerodynamic control missile inside the atmosphere, a compound control algorithm based on the fuzzy control theory is proposed and the corresponding ignition schemes are designed for the attitude control engines with different configurations. Initially, a mathematical model is estab-lished for the compound control missile;secondly, a fuzzy controller is designed to track the overload command in the pitch channel. Proper extension-contraction factors are chosen to realize the adaptive regulation of the universes of inputs and outputs;a compound control allocation algorithm is designed to allocate the control authority between two subsystems in real time. Finally, in order to improve the practicality of the algorithm, the finite-time-convergent differentiator （ FTCD） , the PWPF modulator for the rolling-stable missile and an improved stack ignition algorithm for the rolling missile are designed respectively. The simulation experiment verifies the effectiveness of the com-pound controller.
出处
《哈尔滨工程大学学报》
EI
CAS
CSCD
北大核心
2014年第2期195-201,共7页
Journal of Harbin Engineering University
基金
国家自然科学基金资助项目(61174047)
国防预研资助项目(103020101)
关键词
复合控制
直接力
模糊控制
变论域
点火算法
分配算法
compound control
lateral thrust
fuzzy control
variable universe
ignition algorithm
allocation algorithm
