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浏览/检索结果: 共4条，第1-4条 帮助 限定条件 发表日期：2010     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 Parameter tuning for nonlinear robust controller with high gain observer 期刊论文 2010, 2010 Liu Song; Li Donghai; Xue Yali; Tian Lingling; Wang Chuanfeng 收藏  |  浏览/下载：5/0 Controller design and simulation of aircraft's automatic landing under complex atmospheric conditions 期刊论文 2010, 2010 Zou Xin-sheng; Li Chun-wen 收藏  |  浏览/下载：2/0 Speech signal enhancement through wavelet domain MMSE filtering (EI CONFERENCE) 会议论文 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010, August 24, 2010 - August 26, 2010, Changchun, China Fenghua Z.; Le Y.; Jian W.; Qiang S. 收藏  |  浏览/下载：17/0  |  提交时间：2013/03/25 A new speech enhancement system that combine robust signal enhancement and minimum signal distortion is proposed in this paper. The proposed method introduces frequency depended  parametric  MMSE filtering techniques that involve wavelet packets. Voice activity detection (VAD) is used to further distinguish speech from noise and help to adaptively remove noise components from color noise eruptive noisy speech  while perceptual criteria is also taken into account. Experimental results and objective quality measurement test results validate the proposed speech enhancement system and illustrate the benefit of the proposed wavelet domain MMSE filtering as an excellent speech enhancement method to provide sufficient noise reduction and good intelligibility and perceptual quality  without causing considerable signal distortion and musical background noise method. 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.