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浏览/检索结果: 共7条，第1-7条 帮助 已选(0)清除 条数/页：5101520253035404550556065707580859095100   排序方式：请选择发表日期升序发表日期降序作者升序作者降序提交时间升序提交时间降序题名升序题名降序 基于红外光谱技术的混合气体检测系统概述 期刊论文 2016, 2016 党敬民; 付丽; 闫紫徽; 郑传涛; 常玉春; 陈晨; 王一丁; DANG Jing-min; FU Li; YAN Zi-hui; ZHENG Chuan-tao; CHANG Yu-chun; CHEN Chen; WANG Yi-ding 收藏  |  浏览/下载：13/0 基于相似反对称结构的大角度机动姿态控制器设计 期刊论文 2010, 2010 刘宜成; 张涛; 宋靖雁; 梁斌; LIU Yi-cheng; ZHANG Tao; SONG Jing-yan; LIANG Bin 收藏  |  浏览/下载：2/0 多体航天器大角度机动鲁棒控制 期刊论文 2010, 2010 袁长清; 李俊峰; 沈英; YUAN Changqing; LI Junfeng; SHEN Ying 收藏  |  浏览/下载：2/0 United steering of control moment gyros for small satellite with limited gimbal rate (EI CONFERENCE) 会议论文 2010 IEEE International Conference on Information and Automation, ICIA 2010, June 20, 2010 - June 23, 2010, Harbin, Heilongjiang, China Xu K.; Jin G.; Chen C. 收藏  |  浏览/下载：17/0  |  提交时间：2013/03/25 Single Gimbal Control Moment Gyroscopes (SGCMG) can could provide large control torque and quick attitude maneuver rate to small satellites without any increase in power  volume and mass  which will help small satellites become more powerful. Singularity avoidance and failure steering are two important problems to SGCMGs and also the main focus in this field. A new united steering law for SGCMGs with capabilities of singularity avoidance and quick transition of singularity surfaces is developed in this paper. To ensuring the existence of null motion  the commanded output of controller was changed real-timely as the variation of singularity measurement of SGCMGs  which can avoid the gimbal angle rate saturation. This developed steering law could help the SGCMGs provide real-time control toques in spite of limitation of gimbal angle rate. Simulation analysis is conducted for a certain 4-SGCMG system mounted on a small satellite. Simulation results indicate that the steering law is very effective in singularity avoidance. 2010 IEEE.   Analysis of inertia dyadic uncertainty for small agile satellite with control moment gyros (EI CONFERENCE) 会议论文 2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China Sun Z.; Zhang L.; Jin G.; Yang X. 收藏  |  浏览/下载：12/0  |  提交时间：2013/03/25 With the increasing demands for the agility of the next earth imaging satellite  control moment gyro (CMG) is considered to be the most suitable actuator because of its torque amplification capability. However  a CMG system may introduce uncertainty of inertia dyadic to a satellite's attitude control system. The uncertainty is negligible for large space vehicles  but it has not been tested whether it can be ignored for small agile satellites. How to model the CMG system inertia dyadic varying with gimbal angles  and what influence it will put on the performance of attitude control system haven't been test accurately as well. All of them are dealt with mathematically and accurately in this paper. This paper firstly gives mathematic descriptions of the inertia dyadic of the 4-CMG pyramid configuration system  varying with gimbal angles  and then designs a variable structure control law for small agile satellite using CMGs. Finally  numerical simulation suggests that the inertia dyadic variation of a 4-CMG pyramid configuration system is approximately centesimal of the total inertia dyadic of the satellite  and that the designed variable structure control law is of good robust performance for an example of large-angle attitude maneuver  despite of the variation of the inertia dyadic. 2010 IEEE.   挠性结构的Hœ鲁棒控制系统设计和实验研究 学位论文 1996, 1996 严洪 收藏  |  浏览/下载：3/0  |  提交时间：2016/02/14 Hœ  控制  物理仿真实验  挠性结构卫星  振动抑制  大角度机动  Hœ  control  physical simulation experiment  flexible space structure satellites  vibration suppression  large angle maneuver   CSVS method for spacecraft with two flexible appendages during attitude maneuver (CPCI-S收录) 会议论文 MODERN TECHNOLOGIES IN MATERIALS, MECHANICS AND INTELLIGENT SYSTEMS 作者:  Wang Guanyu[1];  Ge Weiping[2];  Yang Guangwei[1];  Wang Shengchao[1] 收藏  |  浏览/下载：2/0  |  提交时间：2019/04/12 component synthesis vibration suppression(CSVS) method  multi-deformable-body dynamics  large angle maneuver