中国科学院机构知识库网格系统: 检索

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	Research on a six-degree-of-freedom disturbance force and moment simulator for space micro-vibration experiments 期刊论文 OAI收割 Journal of Sound and Vibration, 2018, 卷号: 432, 页码: 530-548 作者: Wang, X. M.; Xu, Z. B.; Xia, M. Y.; He, S.; Li, H. \| 收藏 \| 浏览/下载：26/0 \| 提交时间：2019/09/17 Reaction wheel assembly Disturbance force Disturbance moment Iterative control Simulator isolation platform design Acoustics Engineering Mechanics
	Aircraft flight simulation with landing gear based on multi-domain modeling technology (EI CONFERENCE) 会议论文 OAI收割 2012 2nd International Conference on Computer Application and System Modeling, ICCASM 2012, July 27, 2012 - July 29, 2012, Shenyang, China 作者: Li M. 收藏 \| 浏览/下载：23/0 \| 提交时间：2013/03/25 This paper create a full aircraft flight simulation model for accurately analyzing the performance and influence of landing gear system. The use of multi-domain modeling technology enables detailed modeling of the flight dynamic and landing gear dynamic. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is actual in the physical process. The parameter design space is easily searched by considering a number of different landing scenarios to optimize the design. the authors.
	Establishment of airplane flight model and simulation analysis of landing behavior (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: Li L.; Li M. 收藏 \| 浏览/下载：33/0 \| 提交时间：2013/03/25 This paper create a high fidelity plant model of an aircraft landing gear to inclusion into a full aircraft flight simulation for accurately analyzing the performance and influence of landing gear system. The use of domain specific modeling software enables detailed modeling of the physics and facilitates accurate computational simulation of the flight dynamic aerodynamic landing gear dynamic and mechanical loads that occur when the landing gear are deployed and retracted during landing and take-off operations. The parameter design space is easily searched by considering a number of different landing scenarios including touching down on one wheel first to optimize the design. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is actual in the physical process. 2011 IEEE.
	Aircraft landing gear simulation using multidomain modeling technology (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Information Technology, Computer Engineering and Management Sciences, ICM 2011, September 24, 2011 - September 25, 2011, Nanjing, Jiangsu, China 作者: Li M. 收藏 \| 浏览/下载：46/0 \| 提交时间：2013/03/25 In order to accurately analyze the performance and influence of landing gear system this paper presents a high fidelity plant model of an aircraft landing gear to inclusion into a full aircraft flight simulation. The use of domain specific modeling software enables detailed modeling of the physics and facilitates accurate computational simulation of the flight dynamic aerodynamic landing gear dynamic and mechanical loads that occur when the landing gear are deployed and retracted during landing and take-off operations. The parameter design space is easily searched by considering a number of different landing scenarios including touching down on one wheel first to optimize the design. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is improve the precision of flight simulation. 2011 IEEE.
	A 3-axis simulator for spacecraft attitude control research (EI CONFERENCE) 会议论文 OAI收割 2010 IEEE International Conference on Information and Automation, ICIA 2010, June 20, 2010 - June 23, 2010, Harbin, Heilongjiang, China 作者: Dai L. 收藏 \| 浏览/下载：36/0 \| 提交时间：2013/03/25 This article presents the details of a new 3-axis simulator for spacecraft attitude control research and simulation. The air bearing allows the test bed to rotate about three axes with tiny friction. The attitude determination system consists of three fibre optical gyros an inclinometer and a magnetometer. The actuator of the system consists of three reaction flywheels and four control moment gyros (CMG). Mathematical models of the sensors and actuators are given to help algorithm design. An extended Kalman filter was designed to provide attitude information for controller. Mathematical simulation results prove the attitude determination system can achieve high precision. A coulomb friction model of reaction wheels is given with experimental results. A friction compensation algorithm was developed to raise the pointing accuracy of the control system. The article also describes the details of the hardware structure. A PD stabilizing controller is implemented to test the validation of the whole control system at last. 2010 IEEE.
	Design and analysis of power system of micro-electromechanical actuator (EI CONFERENCE) 会议论文 OAI收割 2010 2nd International Conference on Industrial Mechatronics and Automation, ICIMA 2010, May 30, 2010 - May 31, 2010, Wuhan, China 作者: Zhang J.; Zhang J.; Zhang J. 收藏 \| 浏览/下载：32/0 \| 提交时间：2013/03/25 In order to apply the electromechanical actuator to tactical mini-missiles maximum rotational speed of output shafts is greater than 250/s. Test results basically correspond to the requirement of technical indexes. It is proved that this analysis and design method is congruent with the design of micro-electromechanical actuators this paper researches on the key technology such as load-bearing ability the system bandwidth can reach 25.3Hz on the condition of no load and 23.4Hz on the condition of load thus the method is feasible. 2010 IEEE. rapidity and miniaturization of the micro-electromechanical actuator power system based on the ball screw. First according to specific technical indexes the power electromechanical time constant and the size of the motors are screened originally through theoretical analysis. Finally based on the characteristics of ball screw transmission load locus of the micro-electromechanical actuator dynamic system is theoretically analyzed and the optimum speed ratio is determined through parameter optimization. The results of the double closed loop controlled test on the principle prototype show: the system can operate normally with 2.5N.m hinge moment
	The calculating formulae, and experimental methods in error propagation analysis 期刊论文 iSwitch采集 Ieee transactions on reliability, 2006, 卷号: 55, 期号: 2, 页码: 169-181 作者: Zhang, Jianfang 收藏 \| 浏览/下载：34/0 \| 提交时间：2019/05/10 Error propagation Experiment Moment-design S-normal distribution System
	Low dipole moment large ss electrooptic chromophores based on exocyclic double bond conjugated bridge 期刊论文 OAI收割 CHINESE SCIENCE BULLETIN, 2001, 卷号: 46, 期号: 18, 页码: 1517-1522 作者: Wang, P; Li, SJ; Ye, C \| 收藏 \| 浏览/下载：18/0 \| 提交时间：2019/04/09 Am1/ff Zindo/s-ci Molecular Design Dipole Moment (Mu) First Hyperpolarizability (Ss) Exocyclic Double Bond