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浏览/检索结果: 共3条，第1-3条 帮助 已选(0)清除 条数/页：5101520253035404550556065707580859095100   排序方式：请选择作者升序作者降序题名升序题名降序发表日期升序发表日期降序提交时间升序提交时间降序 A vertex tracking technique based on airborne opticalequipment (EI CONFERENCE) 会议论文 2011 International Conference on Electronics and Optoelectronics, ICEOE 2011, July 29, 2011 - July 31, 2011, Dalian, China Li Q. 收藏  |  浏览/下载：12/0  |  提交时间：2013/03/25 After analyzing the advantages and disadvantages of photoelectric tracking system withhorizontal gimbal and X-Y double-axis gimbal  a vertex tracking method based on airborne photoelectricequipmenthas been presented. The method  which combines advantages of horizontal gimbal and X-Y double-axis gimbal  can effectively track target in the blind area. experiments show that the tracking method is simple  tracking accuracy is 3  meet the technical requirements. 2011 IEEE.   Design and calibration of the solar irradiance monitor (EI CONFERENCE) 会议论文 International Symposium on Photoelectronic Detection and Imaging 2011: Space Exploration Technologies and Applications, May 24, 2011 - May 26, 2011, Beijing, China Yang D.-J.; Fang W.; Ye X.; Wang Y.-P.; Gong C.-H.; Zhang G.-W. 收藏  |  浏览/下载：18/0  |  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.   Research of error correction of LEO satellite orbit prediction for vehicle-borne tracking and position device (EI CONFERENCE) 会议论文 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010, August 24, 2010 - August 26, 2010, Changchun, China Zhang P.-L.; Guo L.-H.; Wang J.-J. 收藏  |  浏览/下载：20/0  |  提交时间：2013/03/25 Vehicle-borne tracking and position device is used to track LEO satellite. Because of the absence of the target which might be caused by cloud or zenith blind zone  the forecasting data will be used to acquire the target. While orbit prediction has serious errors  the target is always missed. Meanwhile  in its application to the vehicle-borne tracking and position device  due to the base of instability in the tracking process  it will result in significant difference between predicting data and tracking data  so the target will be not tracked rapidly. We applied tracking data to predict satellite orbits by improving Laplace method  and then corrected the error between Predicted data and actual measured data by interpolation method of Lagrange which improves the accuracy of prediction values. The testing data shows the accuracy of predicted data ranging from 3' to 10" for both azimuth and elevation when extrapolated satellite orbit to 7 seconds time. 2010 IEEE.