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浏览/检索结果: 共5条，第1-5条 帮助 已选(0)清除 条数/页：5101520253035404550556065707580859095100   排序方式：请选择作者升序作者降序题名升序题名降序发表日期升序发表日期降序提交时间升序提交时间降序 Research on optimal control strategy for velocity stability of space two-dimensional tracking turntable 会议论文 Chongqing, China, 2022-03-04 作者:  Xie, Meilin;  DIng, Lu;  Cao, Yu;  Lian, Xuezheng;  Liu, Peng 收藏  |  浏览/下载：37/0  |  提交时间：2022/04/27 Space  High dynamic  Speed stability  Optimal control  Strong coupling   Development and experimental evaluation of multi-fingered robot hand with adaptive impedance control for unknown environment grasping 期刊论文 ROBOTICA, 2016 作者:  Zhang, Ting;  Jiang, Li;  Fan, Shaowei;  Wu, Xinyu;  Feng, Wei 收藏  |  浏览/下载：18/0  |  提交时间：2017/01/13 4m级望远镜主轴交流伺服控制系统研究 学位论文 博士: 中国科学院大学, 2015 作者:  邓永停 收藏  |  浏览/下载：223/0  |  提交时间：2015/11/30 大型望远镜  永磁同步力矩电机  空间矢量控制   The aircraft autopilot design of parameters changing in a wide range (EI CONFERENCE) 会议论文 2011 International Conference on Electric Information and Control Engineering, ICEICE 2011, April 15, 2011 - April 17, 2011, Wuhan, China Zhen D.; Yue Z. 收藏  |  浏览/下载：20/0  |  提交时间：2013/03/25 Autopilot is an important part of aircraft  Under the action of the disturbance torque  for the flight parameters of aircraft Changing in a wide range  the range was about 16km  on the basic of analyzing the typical trajectory  the max height was about 5100m  the trajectory of feature points were selected  the deviation of lateral was about 12m  taking pitch control loop for example  the maximum angle of attack was about 3.6  a sub- PID autopilot was designed using classical control theory  the maximum elevator deflection was less than 5  using single-mode Transient suppression method  the maximum aileron deflection was less than 2  the overload due to control surface transition deflection was avoided when control parameters changing  the maximum roll was less than 5  the verification was done by non-linear simulation. The result showed that: the phase margin of autopilot was greater than 30  the response of overload can accurately track the given overload instruction. An autopilot design method of aircraft of parameter changes in a wide range was provided. 2011 IEEE.  the bandwidth was more than 14rad / s  the settling time was less than 0.7s  the maximum overshoot was 23.3%   Control method research on wide flight envelope aerocraft (EI CONFERENCE) 会议论文 2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China Duan Z. 收藏  |  浏览/下载：19/0  |  提交时间：2013/03/25 The flying qualities of aerocraft was directly effected by the autopilot  for the wide flight envelope aerocraft  on the basic of analyzing the typical trajectory  the three loop autopilots of roll stability  pitch and yaw were designed  using single-mode Transient suppression method  the overload due to control surface transition deflection was avoided when control parameters changing  the verification was done by non-linear simulation. The result showed that: Under the action of the disturbance torque  the maximum roll was less than 5  the range of the aerocraft was from 13.5km to 22.4km  the max height was about 5100m  the max deviation of lateral was about 42m  the maximum elevator deflection was less than 6.5 the control law was applicable within the effective range. An autopilot design method of wide flight envelope aerocraft was provided. 2011 IEEE.