中国科学院机构知识库网格系统: 检索

浏览/检索结果: 共4条，第1-4条

帮助

条数/页：排序方式：
	Constraints on the Moment of Inertia of a Proto Neutron Star from the Hyperon Coupling Constants 期刊论文 OAI收割 JOURNAL OF ASTROPHYSICS AND ASTRONOMY, 2012, 卷号: 33, 页码: 303-310 作者: Zhao, Xian-Feng; Jia, Huan-Yu \| 收藏 \| 浏览/下载：22/0 \| 提交时间：2018/07/05 The Moment Of Inertia The Relativistic Mean Field Theory Proto Neutron Star
	Parameters estimation of BLDC motor for energy storage system (EI CONFERENCE) 会议论文 OAI收割 10th World Congress on Intelligent Control and Automation, WCICA 2012, July 6, 2012 - July 8, 2012, Beijing, China Wu J. 收藏 \| 浏览/下载：20/0 \| 提交时间：2013/03/25 This paper presents a statistical method to estimate the parameters of the brushless dc (BLDC) motor of a flywheel system for energy storage. The principle of the estimation is based on least square estimation under a reasonable constraint. Method is suitable to avoid using complicated test apparatus. Torque constant static friction coefficient vicious friction coefficient and inertia moment can be estimated. Furthermore copper loss iron loss mechanical loss and other loss can be computed from these estimation and measurement data. By the proposed method it is demonstrated experimentally that accuracy estimation can be achieved. 2012 IEEE.
	The reflector bracket mirror structure optimization and design of the IR warring system (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Advanced Engineering Materials and Technology, AEMT 2011, July 29, 2011 - July 31, 2011, Sanya, China 作者: Wang B.; Wang B. 收藏 \| 浏览/下载：21/0 \| 提交时间：2013/03/25 This paper introduced a kind of reflector mirror support structure of IRST system. Thescanning reflector mirror support frame material is Ly2 aluminum under the principle of the suited ofmaterial expanding quotient. The support form of the reflector was talked and the system bracketstructure was designed following the requests of the certain complex IRST. The bracket wasoptimized and analyzed under the best structure quality and the least moment of inertia and thebellowing of bracket plane thickness mode frequency restriction and deadweight restriction. Fromthe result we can see that the bracket mass can reduce from 0.73kg to 0.49kg and the moment ofinertia can reduce from 0.0109kg2 to 0.0056 kg2 under the first precondition of the structure modefrequency being low and the biggest transmogrification being teeny. The base frequency and intensionof the complex IRST system can be indicated well after the finite element analysis static checking. (2011) Trans Tech Publications Switzerland.
	Analysis of inertia dyadic uncertainty for small agile satellite with control moment gyros (EI CONFERENCE) 会议论文 OAI收割 2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China 作者: Zhang L.; Zhang L.; Sun Z. 收藏 \| 浏览/下载：20/0 \| 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.