小型固体火箭控制系统设计与半实物仿真验证  

Small solid rocket control system design and hardware-in-the-loop simulation and validation

作　　者：张银辉[1] 程见童[1] 杨华波[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2012年第1期29-33,52,共6页Journal of Solid Rocket Technology

摘　　要：对小型固体火箭进行了滚转通道最优控制系统的设计,通过半实物仿真系统对其控制效果进行了验证。基于小扰动法与固化系数法,实现了对小火箭滚转通道最优控制律的设计;采用dSPACE实时仿真机,完成了小型固体火箭半实物仿真平台的搭建;在舵机无反馈装置的情况下,利用电台实现了舵机控制参数的传递,达到了控制系统闭环仿真的目的。设计的半实物仿真平台,不仅完成了对控制系统的验证,而且还具有小火箭发射过程的全程模拟能力。半实物仿真结果表明,设计的最优控制参数可满足小火箭滚转通道的稳定控制。The roll channel optimal control system of a small solid rocket was designed and validated in respect of control effect via hardware-in-the-loop simulation （HILS）. The roll channel optimal control state feedback matrix parameters were derived based on missile models linearization around several operating points in the flight envelope. The small rocket HILS platform was accom- plished by use of dSPACE, and the import of rudder control command was realized by use of radio device where there was no feed- back sensor for the rudder,attaining the aim of control system closed loop simulation. The HILS platform can not only validate the control effect of PID control system, but also possess the capability of entire simulation of the small rocket launch process. The HILS results indicate that optimal control system can satisfy the roll channel stability control of the small rocket.

关 键 词：最优控制系统 半实物仿真 DSPACE 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]