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	Mechanical Shock Wave Suppression Structure in Hold-Down and Release Apparatus of Spacecraft 期刊论文 OAI收割 AIAA JOURNAL, 2024 作者: Yang, Yan; Liu, Wei; Zhou, Hao; Yang, Jianzhong; Wang, Xianping \| 收藏 \| 浏览/下载：15/0 \| 提交时间：2024/11/20 Shock Waves Spacecrafts Cylindrical Shell Structures Frequency Response Satellites Aerospace Engineering Finite Element Method Spacecraft Structures Numerical Simulation Cylindrical Coordinate System
	Finite-time leader-following output consensus for multi-agent systems via extended state observer 期刊论文 OAI收割 Automatica, 2021, 卷号: 124, 页码: 1-5 作者: Wang, Yingjie; Yuan Y(袁源); Liu JG(刘金国) \| 收藏 \| 浏览/下载：22/0 \| 提交时间：2020/10/06 Finite-time consensus Multi-agent systems Extended state observer Spacecraft system
	Identification of the time-varying modal parameters of a spacecraft with flexible appendages using a recursive predictor-based subspace identification algorithm 期刊论文 OAI收割 Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2019, 卷号: 233, 期号: 6, 页码: 2032-2050 作者: Ni ZY(倪智宇); Liu JG(刘金国); Wu ZG(吴志刚) \| 收藏 \| 浏览/下载：22/0 \| 提交时间：2018/06/17 Modal parameter identification recursive subspace algorithm spacecraft time-varying system flexible appendage
	Time-varying modal parameters identification of large flexible spacecraft using a recursive algorithm 期刊论文 OAI收割 International Journal of Aeronautical and Space Sciences, 2016, 卷号: 17, 期号: 2, 页码: 184-194 作者: Ni ZY(倪智宇); Wu ZG(吴志刚); Wu SN(邬树楠) 收藏 \| 浏览/下载：28/0 \| 提交时间：2016/07/22 modal parameter identification large flexible spacecraft linear time-varying system recursive subspace algorithm
	Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism 会议论文 OAI收割 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Glasgow, United kingdom, July 6, 2015 - July 9, 2015 作者: Yao W(姚卫); Wang J(王晶); Lu Y(陆阳); Li XP(李晓鹏); Fan XJ(范学军) 收藏 \| 浏览/下载：30/0 \| 提交时间：2016/07/01 Adiabatic flame temperature Combustion Directed graphs Flow separation Heat flux Kerosene Large eddy simulation Musculoskeletal system Real time systems Sensitivity analysis Spacecraft Transients
	AUTONOMOUS INTEGRATED NAVIGATION USING X-RAY PULSARS AND ASTEROIDS 会议论文 OAI收割 63rd International Astronautical Congress 2012, IAC 2012, Naples, Italy, 2012 Yang Chengwei; Gao Dong; Zheng Jianhua 收藏 \| 浏览/下载：41/0 \| 提交时间：2014/04/30 To improve the navigation performance of the spacecraft during interplanetary cruise a novel integrated navigation system is proposed. For X-ray pulsar navigation (XNAV) is a hot and prospective research subject and the optical navigation using asteroids is practical in space engineering we designed an autonomous navigation system using one X-ray detector and one navigation camera. The measurement models of the XNAV based on the time difference of arrival and the optical navigation based on the images of asteroids are presented. To enhance practicality the X-ray pulsars and asteroids are observed by turns. The batch least square filter used by Deep Space I is adopted to estimate the system state. The numerical simulation results show that the integrated navigation is feasible on the interplanetary cruise orbit. Moreover compared with the XNAV and the optical navigation the integrated navigation system can provide higher navigation performance.
	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：33/0 \| 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.
	Level 0 and level 1 data processing for a type of hyper-spectral imager (EI CONFERENCE) 会议论文 OAI收割 2009 International Conference on Optical Instruments and Technology, OIT 2009, October 19, 2009 - October 21, 2009, Shanghai, China Li X.; Yan C. 收藏 \| 浏览/下载：78/0 \| 提交时间：2013/03/25 Hyper-spectral imaging (HSI) is a kind of optical remote sensor that can simultaneously obtain spatial and spectral information of ground targets. We are now designing a data processing system for a type of space-borne push-broom HSI then it performs radiometric and spectral calibration based on the ground calibration results and onboard calibration collection. The detailed algorithms for bad pixel replacement which has 128 spectral channels covering the spectral range from 400nm to 2500nm. With its large amount of spectral channels radiometric and spectral calibration were presented. After processing the HSI collects large volume of spectral imaging data need to be efficiently and accurately processed and calibrated. In this paper the digital numbers downlinked from the spacecraft can be converted into at-sensor absolute spectral radiance of ground targets the detailed Level 0 and Level 1 data processing steps for the HSI were presented. The Level 0 processing refers to a set of tasks performed on the data downlinked from the spacecraft thus providing accurate quantified spectral imaging data for various applications. 2009 SPIE. including decoding to extract science data separating the science data into files corresponding to different tasks (e.g. ground imaging dark imaging and onboard calibration) checking data integrity and instrument settings data format conversion and Level 0 files creation. The Level 1 processing performs several steps on Level 0 data. Firstly it corrects the image artifacts (mostly the SWIR smear effect) subtracts the dark background and performs the bad pixel replacement according to the prelaunch measurement
	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：34/0 \| 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.