ZN3火箭姿态测量用太阳角计

	ZN3火箭姿态测量用太阳角计
	王英鉴 ; 向绍君 ; 凤君
刊名	宇航学报
	1995
卷号	16 期号:2 页码:47-51,103
关键词	太阳角计姿态测量
ISSN号	1000-1328
其他题名	SUN SENSOR FOR MEASURING THE ATTITUDEOF THE ZN3 ROCKET
通讯作者	北京8701信箱
中文摘要	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。
英文摘要	This 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.
学科主题	空间技术
语种	中文
内容类型	期刊论文
源URL	[http://ir.cssar.ac.cn/handle/122/1664]
专题	国家空间科学中心_其他部室
推荐引用方式 GB/T 7714	王英鉴,向绍君,凤君. 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.(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.