复合柔性结构航天器动力学建模研究
中国空间技术研究院空间飞行器总体设计部,北京 100086
下一篇 上一篇
摘要
柔性航天器动力学建模的传统方法是采用混合坐标法,针对中心刚体带大型柔性附件类的航天器,这种方法在理论建模和工程应用方面都获得了极大的成功。在中心刚体加柔性附件类航天器柔性动力学研究成果基础上,通过计及柔性体与柔性体连接点间的复合位移变形,利用混合坐标法建立了复合柔性结构航天器动力学模型,其软件系统DASFA 2.0已初步用于工程分析设计。
参考文献
[ 1 ] Ho J Y L, Development of dynamic and control simulation of large flexble space systems [J] . J . Guidance 1985, 8 (3): 374一383
[ 2 ] Likins P W. Spacecraft attitude dynamic and control A personal perspective on early developments [J] . J . Guidance1986,9(2):129一134
[ 3 ] Qu Guangii. Dynamics analysis of flexible spacecraft [R]. IAF-90-321, The 41st Congress of IAF, 1990
[ 4 ] Qu Guangli. On the devedlopment of larges paceeraft dynamics in China [R]. ESASP-326, 1991
[ 5 ] 曲广青. 空间站动力学[A]. 范剑峰. 空间站工程概论[C]. 哈尔滨: 哈尔滨工业大学出版社, 1990.63一1101
[ 6 ] 曲广吉. 柔性航天器动力学分析研究 [A]. 王大钧,曲广吴. 工程力学进展 [C]. 北京: 北京大学出版社, 1998, 190一196
[ 7 ] Modi V J. Suleman A. System models and dynamics of the proposed space station type configuration [R]. A92-15376, 645一659
[ 8 ] Craig R R Jr. Su T J. A review of model reduction methods for structural control design [R]. A92一15383
[ 9 ] Hughes P C. Skelton R E. Modal truncation for flexible spacecraft [R]. AIAA79-1765R
[10] Likins P. Ohkami Yoshiaki. Appendage model coordinate trancation cnitera in hubrid coordinate dynamic analysis [J] Spacecraft, 1976, 13(10): 611一617
[11] Wiliams T. Mostarshedi M. Model reduction results for flexible space structures [R] , N93-18824
[12] Wiliams T. Closed-form grammians and model reduction for flexible spaces tructures [A]. IEEE Transactions on Automatic Control [C], 1990, 35(3) : 379一382