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浏览/检索结果: 共3条，第1-3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 Design and optimisation of a novel asymmetric rotor structure for a PM-assisted synchronous reluctance machine 期刊论文 IET ELECTRIC POWER APPLICATIONS, 2019, 卷号: 13, 期号: 5, 页码: 573-580 作者:  Xing, Fuzhen;  Zhao, Wenliang;  Kwon, Byung-Il 收藏  |  浏览/下载：15/0  |  提交时间：2019/12/11 finite element analysis  torque  permanent magnet motors  magnetic flux  reluctance motors  permanent magnet machines  genetic algorithms  reluctance machines  rotors  machine models  symmetric rotor structure  optimised model  optimal torque characteristics  JMAG-Designer  finite-element method  total torque  frozen permeability method  current  phase angle  reluctance torque  magnetic torque  flux leakage  asymmetrical rotor structure  permanent magnet  tuning-fork flux  barriers  synchronous reluctance machine  novel asymmetric rotor  structure  optimisation   Nonlinear fitting method for torque-angle characteristic model of switched reluctance motor [开关磁阻电机矩角特性模型非线性拟合方法] 期刊论文 Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics, 2019, 卷号: 45, 页码: 83-92 作者:  Ye, W.;  Ma, Q.;  Xu, P.;  Zhang, P. 收藏  |  浏览/下载：9/0  |  提交时间：2019/12/30 Curve fitting  Digital storage  Inductance  Models  Reluctance motors  Torque  Constraint conditions  Electromagnetic torques  Magnetization curves  Nonlinear  Nonlinear fitting method  Saturation conditions  Switched Reluctance Motor  Torque-angle characteristics  Electric machine theory   Adaptive control at launching using three loop autopilot (EI CONFERENCE) 会议论文 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China Zhang Y. 收藏  |  浏览/下载：17/0  |  提交时间：2013/03/25 In order to guarantee the precise initial flight trajectory  control the missile disturbance of large disturbance torque  three loop adaptive autopilot was researched. The characteristics of the projectile and three loop autopilot instruction formation characteristics were analysed. From equivalent pitching angle of lateral acceleration feedback loop  combined with the instruction of generalized error  autopilot structure was simplified  and three loop autopilot adaptive control law and stability were designed. The test data show that when disturbance torque was 600Nm  the attitude angle generalized error was -4.4. In the time lasted about 15s  late trajectory accuracy was within 1.0.Three loop autopilot adaptive control law was able to control the disturbance of initial trajectory and adapt to dynamic characteristics changes  control system stability. It was the initial trajectory accurate solution method of flight. 2011 IEEE.