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浏览/检索结果: 共19条，第1-10条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 Self-Propelled Swimming of a Flexible Propulsor Actuated by a Distributed Active Moment 期刊论文  OAI收割 Fluids, 2023, 卷号: 8, 期号: 1, 页码: 29 作者:  Han ZH(韩长鸿);  Zhang ZY(张治愚);  Zhang X(张星)   |  收藏  |  浏览/下载：34/0  |  提交时间：2023/01/17 self-propulsion  ground effect  turning maneuver  flexible propulsor  fluid-structure interaction  active moment  traveling wave  cruising speed  cost of transport   An orbit maneuver detection method based on orbital elements for BeiDou GEO and IGSO satellites 期刊论文  OAI收割 ADVANCES IN SPACE RESEARCH, 2022, 卷号: 69, 期号: 10, 页码: 3644-3654 作者:  Fan, Lihong;  Tu, Rui;  Zhang, Rui;  Han, Junqiang;  Zhang, Pengfei   |  收藏  |  浏览/下载：43/0  |  提交时间：2022/08/15 Orbital maneuver detection  Control interval of orbit maneuver  Control duration of orbital maneuver  Per-satellite Availability  Continuity   Autonomous Maneuver Decisions via Transfer Learning Pigeon-Inspired Optimization for UCAVs in Dogfight Engagements 期刊论文  OAI收割 IEEE/CAA Journal of Automatica Sinica, 2022, 卷号: 9, 期号: 9, 页码: 1639-1657 作者:  Wanying Ruan;  Haibin Duan;  Yimin Deng   |  收藏  |  浏览/下载：26/0  |  提交时间：2022/08/19 Autonomous maneuver decisions  dogfight engagement  game mixed strategy  transfer learning pigeon-inspired optimization (TLPIO)  unmanned combat aerial vehicle (UCAV)   Real-time monitoring of the dynamic variation of satellite orbital maneuvers based on BDS observations 期刊论文  OAI收割 MEASUREMENT, 2021, 卷号: 168, 页码: 9 作者:  Tu, Rui;  Zhang, Rui;  Fan, Lihong;  Han, Junqiang;  Zhang, Pengfei   |  收藏  |  浏览/下载：23/0  |  提交时间：2021/11/29 Orbital maneuver  BeiDou Navigation Satellite System  Velocity estimation  Dynamic monitoring  Epoch-differenced observation  Positioning navigation and timing service   风云四号卫星双程测距系统精密轨道确定 期刊论文  OAI收割 宇航学报, 2020, 卷号: 41, 期号: 3, 页码: 270 作者:  宋叶志;  黄勇;  杨建华;  胡小工;  杨旭海   |  收藏  |  浏览/下载：31/0  |  提交时间：2020/09/02 FY-4  Orbit determination  Orbit maneuver  风云四号  轨道确定  轨道机动   Tracking an Underwater Maneuvering Target Using an Adaptive Kalman Filter 会议论文  OAI收割 2013 IEEE TENCON, Xi'an, China, October 22-25, 2013 作者:  Li W(李为);  Li YP(李一平);  Ren SZ(任申真);  Feng XS(封锡盛) 收藏  |  浏览/下载：24/0  |  提交时间：2013/12/26 underwater target  maneuver  tracking  adaptive Kalman filter  active sonar   On optimal guidance arithmetic of Super-maneuverable aircraft (EI CONFERENCE) 会议论文  OAI收割 30th Chinese Control Conference, CCC 2011, July 22, 2011 - July 24, 2011, Yantai, China 作者:  Liu Y.;  Gong Y.;  Wang Z.;  Wang Z.;  Liu Y. 收藏  |  浏览/下载：23/0  |  提交时间：2013/03/25 Due to the complexity of maneuverability  Super-maneuver attack guidance of modern aircraft has become the most important function to be immediately solved and perfectly completed. Proceed from the maneuvering optimization position and based on the optimal control theory  the optimal angle maneuver guidance arithmatic is proposed. On the basis of aircraft maneuver guidance algorithm  we come up with a variety of constraint condition  optimized index and optimization rule and present a set of steepest optimal angle maneuver guidance algorithm  and the validity and feasibility of the steepest optimal angle maneuver guidance algorithm has been comfirmed by the super-maneuver guidance simulation. 2011 Chinese Assoc of Automati.   United steering of control moment gyros for small satellite with limited gimbal rate (EI CONFERENCE) 会议论文  OAI收割 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：18/0  |  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  OAI收割 2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China 作者:  Zhang L.;  Zhang L.;  Sun Z. 收藏  |  浏览/下载：19/0  |  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.   The application of the instantaneous states reduction to the orbital monitoring of pivotal arcs of the Chang'E-1 satellite 期刊论文  OAI收割 SCIENCE IN CHINA SERIES G-PHYSICS MECHANICS & ASTRONOMY, 2009, 卷号: 52, 期号: 12, 页码: 1833-1841 作者:  Li JinLing;  Guo Li;  Qian ZhiHan;  Ping JinSong 收藏  |  浏览/下载：29/0  |  提交时间：2015/08/18 lunar exploration  orbital maneuver  trace monitoring  instantaneous states  CE-1 satellite