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	Practical method for the definition of chromatographic peak parameters in preparative liquid chromatography 期刊论文 OAI收割 JOURNAL OF SEPARATION SCIENCE, 2016, 卷号: 39, 期号: 20, 页码: 3917-3926 作者: Shen, Aijin; Jin, Gaowa; Guo, Zhimou; Xiao, Yuansheng; Yan, Jingyu 收藏 \| 浏览/下载：52/0 \| 提交时间：2017/10/29 Basic compounds Chromatographic parameters Concentration distribution Peak broadening Preparative liquid chromatography
	Mythen detector for X-ray diffraction at the Beijing synchrotron radiation facility 期刊论文 OAI收割 INSTRUMENTATION SCIENCE AND TECHNOLOGY, 2015, 卷号: 44, 期号: 1, 页码: 1-11 作者: Du R(杜蓉); Cai Q(蔡泉); Chen ZJ(陈中军); Gong Y(宫宇); Wu ZH(吴忠华) 收藏 \| 浏览/下载：44/0 \| 提交时间：2016/04/18 Basic parameters Data treatment Fast response Flat field correction Polycrystalline Synchrotron radiation facility Time-resolved X-ray diffraction measurements
	Structure buckling load interval analysis of supercavitating projectile (EI CONFERENCE) 会议论文 OAI收割 2011 9th International Conference on Reliability, Maintainability and Safety: Safety First, Reliability Primary, ICRMS'2011, June 12, 2011 - June 15, 2011, Guiyang, China 作者: Zhou L. 收藏 \| 浏览/下载：48/0 \| 提交时间：2013/03/25 As a result of supercavitating projectiles with high underwater velocity their structures undergo high longitudinal force. It is necessary to perform structure buckling load interval analysis because the uncertainty of structural own parameters should be considered. Critical buckling load of supercavitating projectiles is calculated by Galerkin method. The partial matrixes of critical buckling load implicit function to each uncertainty variable are deduced and the interval of structure critical buckling load is calculated by interval analysis and convex model methods. Numerical results show that the nominal value lower and upper bounds of critical buckling load increase with the increment of the ratio of base diameter to cavitator diameter. And the uncertainty degree of basic variables should be controlled as far as possible in the project for high reliability. 2011 IEEE.
	The aircraft autopilot design of parameters changing in a wide range (EI CONFERENCE) 会议论文 OAI收割 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：43/0 \| 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 OAI收割 2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China 作者: Duan Z. 收藏 \| 浏览/下载：52/0 \| 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.
	电子束蒸发镀膜速率控制期刊论文 OAI收割中国激光, 2008, 卷号: 35, 期号: 10, 页码: 1591, 1594 王善成; 方明; 易葵; 邵淑英; 范正修收藏 \| 浏览/下载：1605/209 \| 提交时间：2009/09/22 薄膜薄膜工艺速率控制比列积分微分控制 Basic principles Closed-loop controls Control parameters Evaporation characteristics Film process Improved processes Proportion integral differential Rate control Rate controls
	The basic parameters of static pointing model of telescope 期刊论文 OAI收割 CHINESE ASTRONOMY AND ASTROPHYSICS, 2001, 卷号: 25, 期号: 4, 页码: 499-505 作者: Zhang, XX; Wu, LD 收藏 \| 浏览/下载：37/0 \| 提交时间：2013/01/31 telescope static pointing model basic parameters
	SOLUTIONS OF YANG-BAXTER EQUATION WITH COLOR PARAMETERS 期刊论文 OAI收割 SCIENCE IN CHINA SERIES A-MATHEMATICS PHYSICS ASTRONOMY & TECHNOLOGICAL SCIENCES, 1995, 卷号: 38, 期号: 9, 页码: 1105-1116 作者: SUN, XD; WANG, SK \| 收藏 \| 浏览/下载：36/0 \| 提交时间：2018/07/30 YANG-BAXTER EQUATION SOLUTIONS WITH COLOR PARAMETERS OF 6-VERTEX TYPE SOLUTION TRANSFORMATIONS AND BASIC SOLUTIONS