ZN3火箭姿态测量用太阳角计  

SUN SENSOR FOR MEASURING THE ATTITUDE OF THE ZN3 ROCKET

作　　者：王英鉴[1] 向绍君[1] 管凤君[1] 

机构地区：[1]中国科学院空间科学与应用研究中心

出　　处：《宇航学报》1995年第2期46-51,共6页Journal of Astronautics

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。This paper describes the principle and measured results,discusses the background suppression and the calibration method, and analyses the sources of measuring error 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 of the measured wavelength region and the method of ratio measurement. It improves the measuring precision greatly. The measured result shows that the rms error of the measurements is about 0. 7°. The sun sensor. is suitable for measuring the attitude of spin stablized rockets or space vehicles.

关 键 词：太阳角计 姿态测量 火箭 火箭姿态角 测量 

分 类 号：V448.151[航空宇航科学与技术—飞行器设计]