机构

• 近代物理研究所 [14]
• 长春光学精密机械与物... [3]
• 沈阳自动化研究所 [3]

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• OAI收割 [20]

内容类型

• 期刊论文 [15]
• 会议论文 [5]

发表日期

• 2017 [2]
• 2015 [1]
• 2014 [1]
• 2012 [2]
• 2011 [1]
• 2010 [2]
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浏览/检索结果: 共20条，第1-10条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 On-orbit identification of time-varying moment of inertia for spacecraft based on a recursive subspace method 会议论文  OAI收割 36th Chinese Control Conference, CCC 2017, Dalian, China, July 26-28, 2017 作者:  Ni ZY(倪智宇);  Shen XH(沈昕慧);  Liu JG(刘金国);  Wu ZG(吴志刚)   |  收藏  |  浏览/下载：31/0  |  提交时间：2017/11/15 Recursive subspace method  time-varying system  moment of inertia  on-orbit identification  state space model   On-orbit identification of time-varying moment of inertia for spacecraft using an improved recursive subspace method 会议论文  OAI收割 2017 IEEE International Conference on Cybernetics and Intelligent Systems (CIS) and IEEE Conference on Robotics, Automation and Mechatronics (RAM), Ningbo, China, November 19-21, 2017 作者:  Ni ZY(倪智宇);  Shen XH(沈昕慧);  Liu JG(刘金国);  Chang CG(畅晨光)   |  收藏  |  浏览/下载：20/0  |  提交时间：2017/12/21 moment of inertia  recursive subspace method  time-varying system  state-space model  on-orbit identification   Load equivalent simulation method of ultra-large moment of inertia of space station redocking manipulator 期刊论文  OAI收割 Journal of Information and Computational Science, 2015, 卷号: 12, 期号: 2, 页码: 431-441 作者:  Xu ZG(徐志刚);  Bai XL(白鑫林);  Yang MY(杨明毅);  Wang JY(王军义) 收藏  |  浏览/下载：36/0  |  提交时间：2015/03/17 Space Station Redocking Manipulator  Ultra-large Moment of Inertia Simulation  Equivalent Dynamics  Equivalent Moment of Inertia   Rotational properties in even-even superheavy (254-258)Rf nuclei based on total-Routhian-surface calculations 期刊论文  OAI收割 CHINESE PHYSICS C, 2014, 卷号: 38 作者:  Liu Min-Liang;  Jiang Jin-Ge;  Chai Qing-Zhen;  Wang Hua-Lei   |  收藏  |  浏览/下载：25/0  |  提交时间：2018/07/05 Rotational Property  Total-routhian-surface Calculation  Moment Of Inertia  Band Crossing   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.   On the moment of inertia of a proto neutron star 期刊论文  OAI收割 CHINESE PHYSICS C, 2010, 卷号: 34, 页码: 1587-1592 作者:  Zhao Xian-Feng;  Zhang Hua;  Jia Huan-Yu   |  收藏  |  浏览/下载：21/0  |  提交时间：2018/05/31 neutron star  moment of inertia  relativistic mean field theory   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.   Influence of high-j intruder orbitals in odd mass transfermium nuclei No-253 and Md-251 期刊论文  OAI收割 NUCLEAR PHYSICS A, 2009, 卷号: 817, 页码: 45-60 作者:  He, Xiao-tao;  Ren, Zhong-zhou;  Liu, Shu-xin;  Zhao, En-guang   |  收藏  |  浏览/下载：10/0  |  提交时间：2018/07/16 High-j intruder orbital  Transfermium nuclei  Backbending  Cranked shell model  Moment of inertia