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	Space advanced technology demonstration satellite 期刊论文 OAI收割 Science China Technological Sciences, 2024, 卷号: 67, 期号: 1, 页码: 240-258 作者: Zhang, XiaoFeng; Chen, Wen; Zhu, XiaoCheng; Meng, Na; He, JunWang \| 收藏 \| 浏览/下载：53/0 \| 提交时间：2024/02/01 SATech-01 spacecraft design scientific instruments on-orbit performance
	Space advanced technology demonstration satellite 期刊论文 OAI收割 SCIENCE CHINA-TECHNOLOGICAL SCIENCES, 2023, 页码: 19 作者: Zhang, Xiaofeng; Chen, Wen; Zhu, Xiaocheng; Meng, Na; He, Junwang \| 收藏 \| 浏览/下载：34/0 \| 提交时间：2024/02/05 SATech-01 spacecraft design scientific instruments on-orbit performance
	Space advanced technology demonstration satellite 期刊论文 OAI收割 SCIENCE CHINA-TECHNOLOGICAL SCIENCES, 2023, 页码: 19 作者: Zhang, Xiaofeng; Chen, Wen; Zhu, Xiaocheng; Meng, Na; He, Junwang \| 收藏 \| 浏览/下载：55/0 \| 提交时间：2024/02/22 SATech-01 spacecraft design scientific instruments on-orbit performance
	The Earth 2.0 space mission analysis and spacecraft design 会议论文 OAI收割 Montreal, CANADA, 2022-07-17 作者: Chen Wen; Chen Kun; Yang Yingquan; Han Xingbo; Bi Xingzi \| 收藏 \| 浏览/下载：72/0 \| 提交时间：2022/11/21 Earth 2.0 mission analysis spacecraft design high stability high photometry precision
	SGCMG design and time accumulation error analysis (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Mechatronic Science, Electric Engineering and Computer, MEC 2011, August 19, 2011 - August 22, 2011, Jilin, China Xu W. 收藏 \| 浏览/下载：26/0 \| 提交时间：2013/03/25 SGCMG receives much concern due to the performance of its excellent torque output on spacecraft control it has been applied to large foreign spacecraft already but late start and only limited to configurations and steering law study in China. Based on the needs of agility small satellites this article explained the method of SGCMG principle prototype design and proposed the influence on SGCMG output torque precision generated by time accumulation error first time. This article provided a new idea for future SGCMG project development and had good reference value for SGCMG research. 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.
	Application of CMOS APS star tracker with large FOV in attitude and angular velocity determination (EI CONFERENCE) 会议论文 OAI收割 Advanced Sensor Systems and Applications III, November 12, 2007 - November 14, 2007, Beijing, China Lu D.; Guang J.; Shaoju W.; Tao C. 收藏 \| 浏览/下载：36/0 \| 提交时间：2013/03/25 The paper deals with the spacecraft attitude determination problem using a new kind of star tracker with large FOV based on CMOS APS. Star tracker has been developed since 1970s and proved to be the most accurate sensor ever used in the spacecraft attitude determination systems. But the traditional CCD star tracker also has some disadvantages such as small FOV high power consumption low sample rate and low working angular rate limit which prevent the use of CCD star tracker in attitude large angle maneuvering process. The new kind of star tracker based on CMOS APS has no such disadvantages and is more applicable on modern low-cost agile small satellites. Its higher sample rate and working angular rate limit over traditional CCD star tracker make it more adapt for spacecraft angular velocity determination. Because of the large FOV of the star tracker the mathematical model of traditional CCD star tracker with a small FOV is not appropriate. So a new mathematical model was quoted to fit the star tracker with a large FOV. An alternative adaptive algorithm was also introduced in the paper. It can help the EKF algorithm work lacking of accurate covariance of the observation noise. An optimal estimation algorithm was used to estimate the angular velocity directly from the star tracker measurements. Mathematic simulation results indicate the CMOS APS star tracker can give accurate attitude information and estimated angular rate. The method can be used as the chief attitude determination system design of low-cost satellite without gyros or be used as a backup strategy in the event of gyro failures to enhance the reliability of the attitude determination system.