中国科学院机构知识库网格
Chinese Academy of Sciences Institutional Repositories Grid
首页 机构 成果 学者
  
  1. CAS IR Grid
机构
采集方式
内容类型
发表日期
学科主题
筛选

浏览/检索结果: 共9条，第1-9条 帮助

条数/页： 排序方式：
Pursuing 3-D Scene Structures With Optical Satellite Images From Affine Reconstruction to Euclidean Reconstruction 期刊论文  OAI收割
IEEE TRANSACTIONS ON GEOSCIENCE AND REMOTE SENSING, 2022, 卷号: 60, 页码: 14
作者:  Wang, Pinhe;  Shi, Limin;  Chen, Bao;  Hu, Zhanyi;  Qiao, Jianzhong
  |  收藏  |  浏览/下载：33/0  |  提交时间：2022/11/28
Develop the fiber coupling efficiency based on SPGD control algorithm 会议论文  OAI收割
Chengdu, China, June 26, 2018 - June 29, 2018
作者:  Wu, Shuiqin;  Ren, Wei;  Mao, Yao;  Liu, Qiong;  Duan, Qianwen
  |  收藏  |  浏览/下载：18/0  |  提交时间：2021/05/06
Performance Analysis of Satellite-to-Ground Coherent Optical Communication System with Aperture Averaging 期刊论文  OAI收割
APPLIED SCIENCES-BASEL, 2018, 卷号: 8, 期号: 12, 页码: 2496
作者:  Hongwei Li;  Yongmei Huang;  Qiang Wang;  Dong He;  Zhenming Peng
  |  收藏  |  浏览/下载：52/0  |  提交时间：2019/08/23
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：42/0  |  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.  
Design of ground-based physical simulation system for satellite-borne TDI-CCD dynamic imaging (EI CONFERENCE) 会议论文  OAI收割
Optoelectronic Imaging and Multimedia Technology, October 18, 2010 - October 20, 2010, Beijing, China
作者:  Zhang L.;  Zhang L.;  Sun Z.
收藏  |  浏览/下载：28/0  |  提交时间：2013/03/25
As we know  the existence of image motion has a bad effect on the image quality of satellite-borne TDI CCD camera. Although many theories on image motion are proposed to cope with this problem  few simulations are done to justify the proposed theories on ground. And thus  in this paper  a ground-based physical simulation system for TDI CCD imaging is developed and specified  which consists of a physical simulation subsystem for precise satellite attitude control based on a 3-axis air bearing table  and an imaging and simulation subsystem utilizing area-array CCD to simulate TDI CCD. The designed system could realize not only a precise simulation of satellite attitude control  whose point accuracy is above 0.1 and steady accuracy above 0.01/s  but also an imaging simulation of 16-stage TDI CCD with 0.1s its integration time. This paper also gives a mathematical model of image motion of this system analogous with satellite-borne TDI CCD  and detailed descriptions on the principle utilizing area-array CCD to simulate TDI CCD. It is shown that experiment results are in accordance with mathematical simulation  and that the image quality deteriorate seriously when the correspondence between the image velocity and signal charges transfer velocity is broken out  which suggest not only the validity of the system design but also the validity of the proposed image motion theory of TDI CCD. 2010 SPIE.  
Inspection focus technology of space tridimensional mapping camera based on astigmatic method (EI CONFERENCE) 会议论文  OAI收割
5th International Symposium on Advanced Optical Manufacturing and Testing Technologies: Optoelectronic Materials and Devices for Detector, Imager, Display, and Energy Conversion Technology, April 26, 2010 - April 29, 2010, Dalian, China
作者:  Wang Z.;  Wang Z.;  Zhang L.;  Zhang L.
收藏  |  浏览/下载：29/0  |  提交时间：2013/03/25
The CCD plane of the space tridimensional mapping camera will be deviated from the focal plane(including the CCD plane deviated due to camera focal length changed)  under the condition of space environment and vibration  impact when satellite is launching  image resolution ratio will be descended because defocusing. For tridimensional mapping camera  principal point position and focal length variation of the camera affect positioning accuracy of ground target  conventional solution is under the condition of vacuum and focusing range  calibrate the position of CCD plane with code of photoelectric encoder  when the camera defocusing in orbit  the magnitude and direction of defocusing amount are obtained by photoelectric encoder  then the focusing mechanism driven by step motor to compensate defocusing amount of the CCD plane. For tridimensional mapping camera  under the condition of space environment and vibration  impact when satellite is launching  if the camera focal length changes  above focusing method has been meaningless. Thus  the measuring and focusing method was put forward based on astigmation  a quadrant detector was adopted to measure the astigmation caused by the deviation of the CCD plane  refer to calibrated relation between the CCD plane poison and the asrigmation  the deviation vector of the CCD plane can be obtained. This method includes all factors caused deviation of the CCD plane  experimental results show that the focusing resolution of mapping camera focusing mechanism based on astigmatic method can reach 0.25 m. 2010 Copyright SPIE - The International Society for Optical Engineering.  
Analysis of laser jamming to satellite-based detector (EI CONFERENCE) 会议论文  OAI收割
International Symposium on Photoelectronic Detection and Imaging 2009: Laser Sensing and Imaging, June 17, 2009 - June 19, 2009, Beijing, China
作者:  Guo L.-H.;  Guo R.-H.;  Wang S.-W.
收藏  |  浏览/下载：35/0  |  提交时间：2013/03/25
The reconnaissance satellite  communication satellite and navigation satellite used in the military applications have played more and more important role in the advanced technique wars and already become the significant support and aid system for military actions. With the development of all kinds of satellites  anti-satellite laser weapons emerge as the times require. The experiments and analyses of laser disturbing CCD (charge coupled detector) in near ground have been studied by many research groups  but their results are not suitable to the case that using laser disturbs the satellite-based detector. Because the distance between the satellite-based detector and the ground is very large  it is difficult to damage it directly. However the optical receive system of satellite detector has large optical gain  so laser disturbing satellite detector is possible. In order to determine its feasibility  the theoretical analyses and experimental study are carried out in the paper. Firstly  the influence factors of laser disturbing satellite detector are analyzed in detail  which including laser power density on the surface of the detector after long distance transmission  and laser power density threshold for disturbing etc. These factors are not only induced by the satellite orbit  but dependence on the following parameters: laser average power in the ground  laser beam quality  tracing and aiming precision and atmospheric transmission. A calculation model is developed by considering all factors which then the power density entering into the detector can be calculated. Secondly  the laser disturbing experiment is performed by using LD (laser diode) with the wavelength 808 nm disturbing CCD 5 kilometer away  which the disturbing threshold value is obtained as 3.5510-4mW/cm2 that coincides with other researcher's results. Finally  using the theoretical model  the energy density of laser on the photosensitive surface of MSTI-3 satellite detector is estimated as about 100mW/cm2  which is largely exceed the disturbing threshold and therefore verify the feasibility of using this kind of laser disturbing the satellite-based detector. According to the results. using the similar laser power density absolutely saturate the requirements to laser disturbing satellite-based detector. If considering the peak power of pulsed laser  even decrease laser average power  it is also possible to damage the detector. This result will provide the reliable evidences to evaluate the effect of laser disturbing satellite-based detector. 2009 SPIE.  
Modeling of satellite borne TDI CCD pitching imaging image motion velocity vector (EI CONFERENCE) 会议论文  OAI收割
2009 IEEE International Conference on Automation and Logistics, ICAL 2009, August 5, 2009 - August 7, 2009, Shenyang, China
作者:  Zhang L.;  Li S.;  Zhang L.
收藏  |  浏览/下载：20/0  |  提交时间：2013/03/25
In order to obtain three-dimensional observation effect with single satellite borne time delay and integrate charge coupled device (TDI-CCD)  pitching imaging is required. More accurate real-time image motion velocity vector computational model of space camera is also necessary to make the imaging perfect. Imaging motion velocity vector computation model must be set up on image plane at pitching imaging. According to the geometric relationship between the pitching imaging space camera and the Earth's rotation motion  satellite borne TDI CCD pitching imaging motion velocity vector model is derived by mapping the ground speed to the image plane and using coordinate transformation method. The numerical simulation results show that the image velocity model can reduce deviation angle error about 33' and about 30% image motion speed error compared to traditional ground velocity model. 2009 IEEE.  
卫星激光通信Ⅰ链路和终端技术 期刊论文  OAI收割
中国激光, 2007, 卷号: 34, 期号: 1, 页码: 3, 20
刘立人
收藏  |  浏览/下载：897/181  |  提交时间：2009/09/18