大型液体火箭姿控与跷振大回路耦合动力学建模与分析

王庆伟; 谭述君; 吴志刚; 杨云飞; 陈宇

doi:10.6052/0459-1879-15-137

大型液体火箭姿控与跷振大回路耦合动力学建模与分析

doi: 10.6052/0459-1879-15-137

1.
工业装备结构分析国家重点实验室, 大连理工大学工程力学系, 大连116024
2. 大连理工大学航空航天学院, 大连116024
3. 北京宇航系统工程研究所, 北京100076

基金项目: 国家自然科学基金(11072044,11372056)、高等学校博士点基金资助项目(20110041130001)和基本科研业务费(DUT15LK23)资助项目

详细信息

通讯作者:
谭述君,讲师,主要研究方向:飞行器动力学与控制.E-mail:tansj@dlut.edu.cn

中图分类号: V448.2;V434.1
计量
- 文章访问数: 1204
- HTML全文浏览量: 67
- PDF下载量: 887
- 被引次数: 0
出版历程
- 收稿日期: 2015-04-20
- 修回日期: 2015-06-15
- 刊出日期: 2015-09-18

DYNAMIC MODELING AND ANALYSIS OF LARGE-LOOP COUPLED BY ATTITUDE CONTROL AND POGO FOR LARGE LIQUID ROCKETS

1.
State Key Laroratory of Structural Analysis for Industrial Equipment, Department of Engineering Mechanics, Dalian University of Technology, Dalian 116024, China
2. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China
3. Beijing Aerospace System Engineering Institute, Beijing 100076, China

Funds: The project was supported by the General Program of the National Natural Science Foundation of China (11072044, 11372056), Doctoral Fund of Ministry of Education of China (20110041130001) and Funds of Central Universities (DUT15LK23).

摘要

摘要: 大型液体火箭结构模态的空间化分布特征导致结构振动、姿态运动和推进系统液路脉动存在相互耦合,进而影响传统姿控回路的稳定性. 针对大型液体火箭, 充分考虑姿态控制系统对箭体姿态动力学和弹性振动的影响, 以及箭体结构弹性振动与推进系统的耦合作用(跷振(POGO)), 建立了姿控与跷振大回路耦合模型. 该模型包含了推进系统、结构系统与姿控系统之间的耦合因素, 可进行姿控-结构-推进大回路耦合机理研究. 该模型具有非奇异的优点, 可以直接用于频域分析和时域仿真. 基于该模型研究了我国某型号液体捆绑火箭推进系统参数——泵增益和蓄压器能量值对姿态运动与结构振动稳定性的影响. 研究得出, 泵增益和蓄压器能量值的变化不仅导致了结构振动的不稳定, 而且也导致了姿态运动的发散. 因此, 对于大型液体捆绑火箭, 推进系统与姿控系统之间存在不可忽略的耦合作用, 在设计姿控系统时, 有必要考虑推进系统对姿控系统稳定性的影响.
- 姿控回路 /
- 跷振回路 /
- 大回路耦合模型 /
- 建模 /
- 稳定性分析
Abstract: Coupling effect always exists between structural vibration, attitude and propulsion system because of the spatial distribution characteristics of the structural vibration mode of large liquid rockets. The coupling model of attitude control-structure-propulsion system is derived to investigate the effects of the propulsion system on the stability of attitude control system. The coupling is based on mechanism that the effects of attitude control system on the attitude motion and structural vibration as well as the interaction of propulsion system and structural vibration. By including the coupling factors between the propulsion system, structural system and attitude control system, the large-loop coupling model can be used to investigate the coupling stability of the large-loop coupling system. Besides, the coupling model can be directly used for frequency-domain analysis and time-domain simulation for the non-singularity. Based on this model, the effects of the propulsion system parameters-pump gain and accumulator energy value to the stability of attitude control system are analyzed by frequency domain analysis and time domain simulation. The results show that the variations of parameters-pump gain and accumulator energy value not only result in the instability of structural vibration but also lead to the instability of attitude motion. It is concluded that it is necessary to take the effect of POGO loop into count in the design of attitude control system.
- attitude control loop /
- POGO loop /
- large-loop coupling model /
- modeling /
- stability analysis

HTML全文

参考文献(16)

杨云飞, 李家文, 陈宇, 等. 大型捆绑火箭姿态动力学模型研究. 中国科学(E辑:技术科学), 2009, 39(3): 490-499 (Yang Yunfei, Li Jiawen, Chen Yu, et al. Study on attitude dynamics modeling for large bundled rockets. Science in China E Series: Technical Science, 2009, 39(3): 490-499 (in Chinese))

李家文. 大型捆绑火箭姿态控制系统的建模、设计与分析. [博士论文]. 长沙: 国防科学技术大学, 2011 (Li Jiawen. Modeling, design and analysis of large strap-on launch vehicle's attitude control system.[PhD Thesis].Changsha: National University of Defense Technology, 2011 (in Chinese))

Rtan RS, Papadopoulos JG, Kiefling LA, et al. A study of saturn As-502 coupling longitidinal structural vibration and lateral bending respnse during boost. Journal of Spacecraft and Rockets, 1970,7(2): 113-118

肖利红. 捆绑火箭助推段扭转与纵向振动耦合分析. 航天控制, 2001, 19(2): 14-19 (Xiao Lihong. Coupling analysis of tortional and longitudinal vibration of bundled rocket during boost. Aerospace Control, 2001, 19(2): 14-19 (in Chinese))

王建民, 荣克林, 冯颖川等. 捆绑火箭全箭动力学特性研究. 宇航学报, 2009, 30(3): 821-826 (Wang Jianmin, Rong Kelin, Feng Yingchuan, et al. The research of dynamic characteristics for the strap-on launch vehicle. Journal of Astronautics, 2009, 30(3): 821-826 (in Chinese))

王建民, 吴艳红, 张忠等. 运载火箭全箭动特性三维建模技术. 中国科学:技术科学, 2014, 44(1): 50-61 (Wang Jianmin, Wu Yanhong, Zhang Zhong, et al. Three-dimensional modeling technology for dynamic characteristics of the launch vehicle. Science in China: Technology Science, 2014, 44(1): 50-61 (in Chinese))

徐延万. 液体弹道导弹与运载火箭系列---控制系统(上册). 北京: 宇航出版社, 1989 (Xu Yanwan. Liquid Ballistic Missile and Lanuch Vehicle Series-Control System. Beijing: Aerospace Press, 1989 (in Chinese))

Rubin S. Longitudinal instability of liquid rockets due to propulsion feedback. Journal of Spacecraft and Rockets, 1966, 3(8): 1188-1195

Oppenheim BW, Rubin S. Advanced POGO stability analysis for liquid rockets. Journal of Spacecraft and Rockets, 1993, 30(3): 360-373

Zhao ZH, Ren GX, Yu ZW, et al. Parameter study on pogo stability of liquid rockets. Journal of Spacecraft and Rockets, 2011, 48(3): 537-541

荣克林, 张建华, 马道远等. CZ-2F火箭POGO问题研究. 载人航天, 2011, (4): 8-18 (Rong Kelin, Zhang Jianhua, Ma Daoyuan, et al. Research on POGO problem for CZ-2F rocket. Manned Spaceflight, 2011, (4): 8-18 (in Chinese))

唐冶, 方勃, 李明明等. 液体火箭推进系统频率特性的灵敏度分析. 宇航学报, 2014, 35(8): 878-883 (Tang Ye, Fang Bo, LI Mingming, et al. Sensitivity analysis of frequency characteristic for propulsion system in liquid rocket. Journal of Astronautics, 2014, 35(8) :878-883 (in Chinese))

徐得元, 郝雨, 杨琼梁等. 液体火箭纵向耦合振动特性的快速求解方法. 宇航学报, 2014, 35(1): 21-27 (Xu Deyuan, Hao Yu, Yang Qiongliang, et al. Fast matrix algorithm for POGO instability prediction in liquid rocket. Journal of Astronautics, 2014, 35(1): 21-27 (in Chinese))

Wang QW, Tan SJ, Wu ZG, et al. Improved modelling method of POGO analysis and simulation for liquid rockets. Acta Astronautica, 2015, 107: 262-273

胡鹏翔. 液体火箭的多体动力学建模与仿真研究.[博士论文]. 北京: 清华大学, 2012 (Hu Pengxiang. Multibody dynamic modeling and simulation of liquid-propellant launch vehicles.[PhD thesis]. Beijing, Tsinghua University, 2012 (in Chinese))

Cui DL, Yan SZ, Guo XS, et al. Parametric resonance of liquid sloshing in partially filled spacecraft tanks during the powered-flight phase of rocket. Aerospace Science and Technology, 2014, 35: 93-105

施引文献

资源附件(0)

访问统计