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	Activities to Promote the Moon as an Absolute Calibration Reference 期刊论文 OAI收割 REMOTE SENSING, 2023, 卷号: 15, 期号: 9 作者: Jing, Zhenhua; Hu, Xiuqing; Wang, Yang; Wu, Ronghua; Chen, Lin \| 收藏 \| 浏览/下载：17/0 \| 提交时间：2023/06/12 lunar calibration traceability space radiometric measurement Moon small satellites constellations remote sensing
	Small satellites for space science A COSPAR scientific roadmap 期刊论文 OAI收割 ADVANCES IN SPACE RESEARCH, 2019, 卷号: 64, 期号: 8, 页码: 1466-1517 作者: Millan, Robyn M.; von Steiger, Rudolf; Ariel, Meir; Bartalev, Sergey; Borgeaud, Maurice \| 收藏 \| 浏览/下载：33/0 \| 提交时间：2019/12/17 Small satellites Space science
	Energy response of GECAM gamma-ray detector based on LaBr3:Ce and SiPM array 期刊论文 OAI收割 Nuclear Instruments and Methods in Physics Research, Section A: Accelerators, Spectrometers, Detectors and Associated Equipment, 2019, 卷号: 921, 页码: 8--13 作者: Zhang, Dali; Li, Xinqiao; Xiong, Shaolin; Li, Yanguo; Sun, Xilei \| 收藏 \| 浏览/下载：34/0 \| 提交时间：2020/10/19 Gamma rays Gravitational effects Gravity waves Radioactivity Scintillation counters Small satellites
	Thermospheric Variations From GNSS and Accelerometer Measurements on Small Satellites 期刊论文 OAI收割 PROCEEDINGS OF THE IEEE, 2018, 卷号: 106, 期号: 3, 页码: 484-495 作者: Jin, Shuanggen; Calabia, Andres; Yuan, Liangliang \| 收藏 \| 浏览/下载：21/0 \| 提交时间：2019/04/08 Accelerometer Global Navigation Satellite System (GNSS) small satellites thermosphere
	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：20/0 \| 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.
	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.
	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：19/0 \| 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.
	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：27/0 \| 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.
	CMOS APS imaging system application in star tracker (EI CONFERENCE) 会议论文 OAI收割 Advanced Materials and Devices for Sensing and Imaging II, November 8, 2004 - November 10, 2004, Beijing, China 作者: Li J.; Liu Y.; Liu Y.; Liu Y.; Liu J. 收藏 \| 浏览/下载：56/0 \| 提交时间：2013/03/25 Small satellites are capable of performing space explore missions that require accurate attitude determination and control. However low weight size power and cost requirements limit the types of attitude sensor of small craft such as CCD are not practical for small satellites. CMOS APS is a good substitute for attitude sensors of small craft. Some of the technical advantages of CMOS APS are no blooming single power low power consumption small size and little support circuitry direct digital output simple to system design in particular radiation-hard characteristic compare with CCD. This paper discusses the application probability of CMOS APS in star tracker for small satellites further more a prototype ground-based star camera based on STAR250 CMOS image sensor has been built. In order to extract stars positions coordinates subpixel accuracy centroiding algorithm has been developed and tested on some ground-based images. Moreover the camera system star sensitivity and noise model are analyzed and the system accuracy is been evaluated. Experimental results indicate that a star camera based on CMOS APS is a viable practical attitude sensor appropriate for space small satellites.