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CORC

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Longitudinal Control for Balloon-Borne Launched Solar Powered UAVs in Near-Space 期刊论文
JOURNAL OF SYSTEMS SCIENCE & COMPLEXITY, 2022, 卷号: 35, 期号: 3, 页码: 802-819
作者:  Hu Yanpeng;  Guo Jin;  Meng Wenyue;  Liu Guanyu;  Xue Wenchao
收藏  |  浏览/下载：5/0  |  提交时间：2023/02/07
Optimal Elevator Group Control via Deep Asynchronous Actor-Critic Learning 期刊论文
IEEE TRANSACTIONS ON NEURAL NETWORKS AND LEARNING SYSTEMS, 2020, 卷号: 31, 期号: 12, 页码: 5245-5256
作者:  Wei, Qinglai;  Wang, Lingxiao;  Liu, Yu;  Polycarpou, Marios M.
收藏  |  浏览/下载：19/0  |  提交时间：2021/03/08
无人机飞行控制系统若干关键技术研究 学位论文
博士: 中国科学院大学, 2014
段镇
收藏  |  浏览/下载：267/0  |  提交时间：2014/08/21
Research of a Multi-UAV flight controller 其他
2014-01-01
Ding, Ji; Fan, Qiongjian; Luo, Delin; Shen, Xiqiang; 罗德林
收藏  |  浏览/下载：3/0  |  提交时间：2015/07/22
Direct adaptive type-2 fuzzy neural network control for a generic hypersonic flight vehicle 期刊论文
SOFT COMPUTING, 2013, 卷号: 17, 期号: 11, 页码: 2053-2064
作者:  Yang, Fang;  Yuan, Ruyi;  Yi, Jianqiang;  Fan, Guoliang;  Tan, Xiangmin
收藏  |  浏览/下载：20/0  |  提交时间：2015/08/12
New Energy-saving Elevator Energy Consumption Analysis and Simulation Based on MATLAB 会议论文
2nd International Conference on Energy and Environmental Protection (ICEEP 2013), Guilin, PEOPLES R CHINA, APR 19-21, 2013
作者:  Hao, Siyu;  Yang, Tingting*;  Wu, Lin
收藏  |  浏览/下载：2/0  |  提交时间：2019/12/04
A new tracking control approach of air-breathing hypersonic vehicles cruise 其他
2013-01-01
Sun, Hongfei; Yang, Zhiling; 孙洪飞
收藏  |  浏览/下载：3/0  |  提交时间：2015/07/22
Flexibility analysis of a tracking control method for air-breathing hypersonic vehicles 期刊论文
http://dx.doi.org/10.1007/s11768-013-2215-7, 2013
Yang, Zhiling; Meng, Bin; Zeng, Jianping; Sun, Hongfei; 孙洪飞
收藏  |  浏览/下载：5/0  |  提交时间：2015/07/22
基于网络通信与串口通信的电梯仿真软件的设计 学位论文
2013, 2013
张洪星
收藏  |  浏览/下载：3/0  |  提交时间：2016/01/13
Three-loop autopilot design and simulation (EI CONFERENCE) 会议论文
2012 9th IEEE International Conference on Mechatronics and Automation, ICMA 2012, August 5, 2012 - August 8, 2012, Chengdu, China
Chu H.-R.; Zhang Y.
收藏  |  浏览/下载：39/0  |  提交时间：2013/03/25
In order to realize missile real-time change flight trajectory  three-loop autopilot is setting up. The structure characteristics  autopilot model  and control parameters design method were researched. Firstly  this paper introduced the 11th order three-loop autopilot model. With the principle of systems reduce model order  the 5th order model was deduced. On that basis  open-loop frequency characteristic and closed-loop frequency characteristic were analyzed. The variables of velocity ratio  dynamic pressure ratio and elevator efficiency ratio were leading to correct system nonlinear. And then autopilot gains design method were induced. System flight simulations were done  and result shows that autopilot gains played a good job in the flight trajectory  autopilot satisfied the flight index. 2012 IEEE.  

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