【作者】 李平；

【导师】 孙晶华；

【作者基本信息】 哈尔滨工程大学 ， 光学工程， 2006， 硕士

【摘要】 星敏感器作为一种高精度和高灵敏度的测角设备，为飞行器的制导和导航设备提供精确的方向基准。研制高精度星敏感器对于我国的航空、航天以及国防事业的发展具有重要的现实意义。 迄今为止，国内研制的导弹用星敏感器工程样机未见使用遮光罩的先例，为了提高星敏感器的工程实用性，减少空间杂散光引入的噪声，借鉴空间星敏感器遮光罩的设计原理和国外弹用星敏感器遮光罩的相关资料，提出星敏感器遮光罩的参数设计选择方案，对原理样机进行工程化改进。 从提高星敏感器测角精度的角度出发，对星光测量所采用的方案进行分析并给出优化选择。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。最后，分析系统静态仿真试验数据误差引入的可能原因。更多还原

【Abstract】 As a type of angle measurement instrument, with high precision and high sensitivity, star sensor provides fiducial direction for guidance and navigation instrument of aircrafts. R&D of high precision star sensor plays a significantly practical role in development of aeronautics, astronautics and national defense.So far, none of star sensor prototypes has been found equipped with lens hood in native missiles. For improving engineering practicability of star sensor and reducing noise of space scattering lights, designing and selecting of lens hood parameters of star sensor and engineering amelioration of prototype were brought forward, based on design principles and correlative data of foreign missile, which regard lens hood of space star sensor.From the point of view of improving angle measurement of star sensor, scheme analysis and optimal selection were carried out. Theoretical precision analysis of angle measurement was done, and practical engineering subdivision arithmetic was presented, which meets system requirement for precision. In the end, causation was discussed, which possibly introduces data error to system static simulating test.更多还原