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	Active optical system for any field angle zoom 期刊论文 OAI收割 optical engineering, 2011, 卷号: 50, 期号: 11, 页码: 113001 作者: Hu, Shaolei; Zhao, Xin; Dong, Weihui; Xie, Yongjun 收藏 \| 浏览/下载：26/0 \| 提交时间：2012/06/29 any field angle deformable mirror active zoom system optical systems design
	Design and calibration of the solar irradiance monitor (EI CONFERENCE) 会议论文 OAI收割 International Symposium on Photoelectronic Detection and Imaging 2011: Space Exploration Technologies and Applications, May 24, 2011 - May 26, 2011, Beijing, China 作者: Yang D.-J.; Gong C.-H.; Wang Y.-P.; Ye X.; Fang W. 收藏 \| 浏览/下载：27/0 \| 提交时间：2013/03/25 The solar irradiance monitor (SIM) with the design accuracy of 5 used to monitor the secular changes of the total solar irradiance on FY-3 satellite takes the sun-scanning measurement method on-orbit. Compared to the sun-tracking measurement method this method simplifies the structure and cuts the cost but the measuring accuracy is affected by the sun-synchronous orbit sunlight incidence angle and the installing angle of the SIM in the satellite. Through the ground calibration experiment studies on the affection of different sunlight incidence angles to the measurement accuracy. First by the satellite tool kit (STK) simulation software simulates the orbital parameters of the sun-synchronous satellite and calculates the Sun ascension and declination at any time. By the orbit coordinate transformation matrix gets the components of the Sun vectors to the axes of the satellite and base on the components designs the field of view and the installing angles of the SIM. Then designs and completes the calibration experiment to calibrate the affection of the incidence angles. Selecting 11 different angles between the sunlight and the satellite X-axis measures the total solar irradiance by the SIM at each angle and compares to the irradiances of the SIAR reference radiometers and gets the coefficient curves of the three channels of the SIM. Finally by the quadratic fitting gets the correction equations on the incidence angles: R 1=5.7110-52 -2.45310 -3+1.0302 R2=2.8410-5-1. 96510-3+1.0314 and R3 =1.7210 -52-4.18410-4+0.9946. The equations will aimprove the on-orbit measurement accuracy of the solar irradiance and are very important to the on-orbit data processing after the satellite launched. 2011 SPIE.
	基于主动光学技术的任意视场变分辨率空间望远镜(英文) 期刊论文 OAI收割光子学报, 2011, 期号: 11, 页码: 1619-1624 作者: 赵惠; 高伟收藏 \| 浏览/下载：19/0 \| 提交时间：2012/06/29 Any field angle Deformable mirror Active zoom system Optical systems design
	United steering of control moment gyros for small satellite with limited gimbal rate (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 Xu K.; Jin G.; Chen C. 收藏 \| 浏览/下载：18/0 \| 提交时间：2013/03/25 Single Gimbal Control Moment Gyroscopes (SGCMG) can could provide large control torque and quick attitude maneuver rate to small satellites without any increase in power volume and mass which will help small satellites become more powerful. Singularity avoidance and failure steering are two important problems to SGCMGs and also the main focus in this field. A new united steering law for SGCMGs with capabilities of singularity avoidance and quick transition of singularity surfaces is developed in this paper. To ensuring the existence of null motion the commanded output of controller was changed real-timely as the variation of singularity measurement of SGCMGs which can avoid the gimbal angle rate saturation. This developed steering law could help the SGCMGs provide real-time control toques in spite of limitation of gimbal angle rate. Simulation analysis is conducted for a certain 4-SGCMG system mounted on a small satellite. Simulation results indicate that the steering law is very effective in singularity avoidance. 2010 IEEE.