大相对孔径轻小型星敏感器光机系统设计
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摘要
星敏感器的光机设计水平直接关系到仪器姿态测量精度的极限。为满足微纳卫星平台使用需求,设计了一种大相对孔径,宽视场的超轻小型星敏感器光学系统及其机械结构。镜头选用6片球面透镜,有效焦距为16mm,工作波长为500～800nm,F#=1.2,视场为20°,全视场内,像点80%的能量集中在3×3像元内,全视场倍率色差小于2μm,相对畸变小于0.1%,优化后所有视场下MTF值均大于0.4。系统总长仅为26mm。针对星敏感器光学系统轻小化需求,选取铍铝合金作为材料进行结构设计。在抗震方面,采用具有相切界面的圆锥类隔圈和压圈以增加接触面积,减小对镜片压强。最终光机系统总质量为10.32g,能够较好的满足小卫星平台的使用需求。
The opto-mechanical design level of the star sensor is directly related to the limit of the instrument's attitude measurement accuracy. In order to meet the usage requirements of the micro-nano satellite platform,an optical system and its mechanical structure of an ultra-light small star sensor with large relative aperture and wide field of view is designed. The system consists of 6 spherical lenses. The effective focal length is 16 mm. The working spectrum is 500 to 800 nano-meter;the F#=1.2,the field of view is 20°;80% of the energy is concentrated in 3×3 pixels in the full field of view;the lateral chromatic aberration is less than 2μm in full field of view and the relative distortion is less than 0.1%. After the optimization,the MTF values in all fields of view are greater than 0.4. The total length of the system is only 26 mm. Aiming at the lightweight and small demand of the star sensor optical system,the beryllium aluminum alloy is selected as the structural material for the structural design. In terms of seismic resistance,conical spacers and pressure coils with tangential interfaces are used to increase the contact area and reduce the pressure on the lens. The final opto-mechanical system has a total mass of 10.32 g,which can better meet the needs of small satellite platforms.
The opto-mechanical design level of the star sensor is directly related to the limit of the instrument's attitude measurement accuracy. In order to meet the usage requirements of the micro-nano satellite platform,an optical system and its mechanical structure of an ultra-light small star sensor with large relative aperture and wide field of view is designed. The system consists of 6 spherical lenses. The effective focal length is 16 mm. The working spectrum is 500 to 800 nano-meter;the F#=1.2,the field of view is 20°;80% of the energy is concentrated in 3×3 pixels in the full field of view;the lateral chromatic aberration is less than 2μm in full field of view and the relative distortion is less than 0.1%. After the optimization,the MTF values in all fields of view are greater than 0.4. The total length of the system is only 26 mm. Aiming at the lightweight and small demand of the star sensor optical system,the beryllium aluminum alloy is selected as the structural material for the structural design. In terms of seismic resistance,conical spacers and pressure coils with tangential interfaces are used to increase the contact area and reduce the pressure on the lens. The final opto-mechanical system has a total mass of 10.32 g,which can better meet the needs of small satellite platforms.
引文
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[2]吴峰,沈为民.折反式大视场星敏感器光学系统设计[J].光学技术,2004(02):142-145.
[3]王虎,苗兴华,汶德胜,等.宽视场大相对孔径星敏感器光学系统设计[J].光子学报,2005(12):1822-1824.
[4]于艇,迟名辰,李艳红,等.1300万像素折衍混合式手机镜头设计[J].长春理工大学学报:自然科学版,2015,38(06):5-11.
[5]谭迪.光学像差对星敏感器亚像元质心定位精度的影响研究[D].长春:中国科学院长春光学精密机械与物理研究所,2017.
[6]何灵娜,崔维鑫,裴云天.CMOS星敏感器光学系统的设计[J].光学技术,2007(S1):195-198.
[7]刘欢,王春艳,庞广宁,等.高精度静态星模拟器光学系统设计[J].长春理工大学学报:自然科学版,2018,41(01):26-29.
[8]王培芳,向阳,王继凯,等.光电显微镜的光学系统设计[J].长春理工大学学报:自然科学版,2015,38(05):17-21.
[9]吴峰,沈为民.轻小型星敏感器光学系统的设计[J].光子学报,2004(11):1336-1338.
[10]杨皓明,王灵杰,翁志成,等.大孔径大视场轻小型星敏感器光学系统[J].光学精密工程,2007(02):151-154.
[11]叶辉,侯昌伦.光学材料与元件制造[M].杭州:浙江大学出版社,2014:6-33
[12]吴卫.高精度星敏感器结构设计和分析[D].西安:中国科学院研究生院(西安光学精密机械研究所),2010.
[13] Paul R,Yoder,Jr.光机系统设计[M].第三版.北京:机械工业出版社,2008:725-735.
[14]杨雪,何煦,张晓辉,等.高频像旋光学目标模拟装置结构设计[J].长春理工大学学报:自然科学版,2018,41(03):10-15.