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ZN3火箭姿态测量用太阳角计
Alternative TitleSUN SENSOR FOR MEASURING THE ATTITUDEOF THE ZN3 ROCKET
王英鉴; 向绍君; 凤君; 北京8701信箱
Department火箭与气球探空技术研究室
Source Publication宇航学报
1995
Volume16Issue:2Pages:47-51,103
ISSN1000-1328
Language中文
Keyword太阳角计 姿态测量
Abstract本文给出了用于ZN3火箭姿态测量太阳角计的原理和测量结果,讨论了背景抑制和标定方法,分析了误差来源。该仪器采用选取适当探测波段和比值测量方法较好地消除了地外太阳辐照和大气消光的影响,也有效地抑制了背景辐射的干扰,大大提高了测量精度。实测结果表明,火箭姿态角测量的均方根误差约为0.7°。这一方法适用于各种自旋稳定飞行器的姿态测量。
Other AbstractThis paper describes the principle and measured results,discusses the back- ground suppression and the calibration method,and analyses the sources of measuring er- ror of the sun sensor for measuring the attitude of ZN3 rocket. For this instrument,the effects of extraterrestrial solar irradiation and atmospheric extinction are removed basically and the interference of background radiation. is suppressed effectively using the proper choice }f the measured wavelength region and the method of ratio measurement. It im- proves the measuring precision greatly. The measured result shows that the rms error of the measurements is about 0. 70. The sun sensor, is suitable for measuring the attitude of spin stablized rockets or space vehicles.
Funding Project中国科学院空间科学与应用研究中心
Document Type期刊论文
Identifierhttp://ir.nssc.ac.cn/handle/122/1664
Collection其他部室
Corresponding Author北京8701信箱
Recommended Citation
GB/T 7714
王英鉴,向绍君,凤君,等. ZN3火箭姿态测量用太阳角计[J]. 宇航学报,1995,16(2):47-51,103.
APA 王英鉴,向绍君,凤君,&北京8701信箱.(1995).ZN3火箭姿态测量用太阳角计.宇航学报,16(2),47-51,103.
MLA 王英鉴,et al."ZN3火箭姿态测量用太阳角计".宇航学报 16.2(1995):47-51,103.
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