光学系统是星敏感器的重要组成部分。
CCD星敏感器的关键问题是星图识别。
The key importance in star map recognition is CCD star sensor.
研究了面向星敏感器的星模式识别算法。
In the article the star-pattern recognition algorithms for a star tracker are studied.
本课题根据星敏感器发展趋势，采用此种探测器件。
Under the trend of development of star sensor, we choose this kind of detector.
星图识别则是星敏感器确定空间飞行器姿态的关键技术。
Star pattern recognition is the key technic of satellite position confirmation from start sensor.
姿态测量精度是衡量星敏感器性能的一项最重要的指标之一。
Attitude accuracy is one of the most important parameters to evaluate the performance of the star tracker.
然后，介绍星敏感器相关的导航星星表的建立、星图识别技术。
Secondly, the establishment of the guide star catalog and its star identification technology are introduced.
星敏感器是为空间飞行器姿态控制系统提供姿态信息的测量系统。
The star sensor is a measuring unit used for providing information to the attitude control system on spacecraft .
本文阐述了利用星敏感器和红外地球敏感器进行自主导航的原理。
The principle of autonomous navigation using star sensors and scanning infrared earth sensors is studied.
利用星敏感器和地平仪测量“星光仰角”，进行自主导航方案设计。
An autonomous navigation scheme is designed by using the star sensor and horizontal instrument to observe the elevation Angle of star.
星敏感器是天文导航系统的主要设备，是一种高精度、高可靠性的姿态测量部件。
Star sensor is a high-precision, high reliability attitude measurement equipment of astronomical navigation system.
仪器星等对正确评估星敏感器的灵敏度、捕获概率以及建立导航星表都有重要的意义。
Stellar instrument magnitudes are important for star trackers; however, there are not simple and accurate methods to estimate stellar instrument magnitudes.
星模拟器是卫星控制系统中姿态测量关键部件——星敏感器的一项重要地面试验设备。
The star simulator instrument is an important test equipment on the ground of star sensitivity instrument which is a stance test key component in planet control system.
从星光信号能量和系统传输函数理论出发，分析了影响星敏感器的探测能力的各个环节。
Analyzes the various infections on the detection ability by researching the star energy and system MTF.
最后利用所构建的半物理仿真系统，对星图识别算法和星敏感器性能进行了静态和动态的试验。
At last, by using the hybrid simulation system, some algorithms of star map identification and performance of star sensor could be effectively verified by dynamical and statical test in this platform.
具有自主导航能力的新一代星敏感器的显著特点是视场大、精度高、体积小、质量轻、功耗低。
Wide field, high precision, small volume and mass, less power consumption are distinct characters of new generation star sensor, which has self-navigation capability.
分析比较了同时瞄准恒星的个数、星敏感器的精度以及改变采样周期对航天器定位误差的影响。
The effect on the number of sighting star, the precision of star sensor and the change of sampling period to the error determination is analyzed and compared.
对星敏感器测量精度从理论上进行分析，给出了工程实用的细分算法，满足系统对精度的需求。
Theoretical precision analysis of Angle measurement was done, and practical engineering subdivision arithmetic was presented, which meets system requirement for precision.
微型星敏感器以其质量小、体积小、功耗小、精度高的优点在小型卫星中得到了越来越多的应用。
Featuring micro mass, volume, power consumption and high accuracy, micro star tracker gains broad application in microsatellites.
进而以给定的APS星敏感器参数为基础，研究了计算窗口、曝光时间等精度影响因素的选择方法；
Then choice of the calculation window and the exposure time influencing the dynamic accuracy is analyzed based on given APS star sensor parameters.
论文以星敏感器在军事上应用为背景，系统地研究并解决了星敏感器在实用中面临的两大关键技术问题。
The dissertation takes the application of a star sensor in military area as background, and systematically studies and solves the above two key technology problems of the star sensor in practice.
由于航天实验费用大，为测试星敏感器性能和星图识别算法，需在地面构建天文导航半物理仿真试验平台。
Because of high spaceflight laboratory fees, it is impractical to take star-pictures real time in order to debug star sensor and test the algorithm of star map identification.
利用光学导航相机以及星敏感器，通过测量星光信息以及天体边缘的信息，进行了自主光学导航方案的设计。
An autonomous optical navigation scheme was designed using the star light data and body edge data which is measured by star sensor and optical navigation camera.
理论分析和计算机仿真都表明，星敏感器的测量精度和焦距，下行信号光的束散角将影响激光链路成功建立概率。
Theory analysis and computer simulation show that the precision and focus of star tracker, the divergence angle of down beam influence the probability of laser link setting up.
利用标定结果对连续拍摄的星图进行识别，得到星敏感器光轴指向误差为4.8462″，标定结果比较理想。
The obtained star maps are identified using the calibration result. It is indicated that optical axis directional error is 4.846 2", which shows the calibration result is more perfect."
为了满足军用卫星姿态测量高精度的需要，提出了基于状态估计法的陀螺仪和星敏感器组成的卫星姿态测量系统的方案。
To get high accuracy of satellite attitude determination, a new approach of satellite attitude determination system, which combines the star-sensors with gyro, is presented in the article.
为了满足军用卫星姿态测量高精度的需要，提出了基于状态估计法的陀螺仪和星敏感器组成的卫星姿态测量系统的方案。
To get high accuracy of satellite attitude determination, a new approach of satellite attitude determination system, which combines the star-sensors with gyro, is presented in the article.
应用推荐