摘要
针对控制系统,采用侧喷流发动机和栅格舵的新型小型多级固体运载火箭开展了起飞段姿态控制方法研究。给出了在低马赫数条件下侧喷流发动机的力放大因子和栅格舵的控制力矩,建立了运载器姿态控制模型。根据侧喷流和栅格舵的特点,设计了PID控制器与智能开关控制器相结合的新型控制器,运用神经网络算法实现了开关控制器参数的在线选择。仿真结果表明,所设计的控制器满足控制精度、稳定度和鲁棒性的要求,算法简便,具有工程可实现性,以侧喷流发动机和栅格舵为执行机构的控制系统能满足运载火箭起飞段姿态控制要求,为陆基或空射小型固体运载火箭姿态控制方法提供了一种新思路。
The attitude control problem for small-size multi-stage solid launch vehicles during ascending stage was investigated by using lateral jet thrusters and grid fins as its attitude control machanism. The jet force amplification factor and control torque of grid fins under low Mach numbers were presented, and the attitude control model of the launcher was established. A novel controller combining conventional PID controller and intelligent oft/off switching controller was designed based on characteristics of lateral jet thrusters and grid fins. The parameters of the switching controller were on-line selected by using neural network algorithm. The sim- ulation results show that the controller can meet accuracy, stability and robustness requirements, and the algorithm is simple and applicable. The control system taking lateral jet thrusters and grid fins as its executive mechanism can meet attitude control require- ments during take-off phase, which provide a new scheme for attitude control method of different kinds of solid launch vehicles.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第1期1-4,29,共5页
Journal of Solid Rocket Technology
关键词
侧喷流
栅格舵
姿态控制
神经网络
lateral jet
grid fin
attitude control
neural network
