The Analysis of Contradiction and Solution for Stability of Launch Vehicle
The control parameter can not be traded off against the upper limit, the lower limit and normal states in the design of launch vehicle attitude control system. That is, the attitude control system can meet the demand in the states of upper limit and lower limit but can’t in the normal state and vice versa. The cause of the problem is presented in this paper that the parameter deviation of the launch vehicle is large and the frequency of rigid body in upper limit state is close to the first-order elastic vibration frequency. Therefore, the contradiction exists in the motion stability performance of the rigid body, sloshing and elastic vibration. Then the detailed solution to deal with this phenomenon is described and the feasibility of each solution is analyzed as well. With the design of the launch vehicles entire body and the control subsystem, the problem proposed in this paper provides an important reference for improving the control system performance of the launch vehicle.
YANG Yunfei ZHAO Yushan LI Guang CHEN Yu
School of Astronautics of Beihang University, Beijing 100083, P.R.China Beijing institute of Astrona School of Astronautics of Beihang University, Beijing 100083, P.R.China School of Automation Science and Electrical Engineering of Beihang University, Beijing 100083, P.R.C Beijing institute of Astronautical System Engineering, Beijing 100076, P.R.China
国际会议
The 30th Chinese Control Conference(第三十届中国控制会议)
烟台
英文
1-6
2011-07-01（万方平台首次上网日期，不代表论文的发表时间）