风云系列近地轨道卫星整流罩透波口设计方法

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英文篇名：Design Method of Wave through Mouth of Fengyun Series Low Earth Orbit Satellite Fairing 作者：茅永兴 ; 朱振华 ; 向颉 ; 倪晓秋 ; 徐曼睿 英文作者：Mao Yongxing;Zhu Zhenhua;Xiang Jie;Ni Xiaoqiu;Xu Manrui;China maritime Satellite tracking and controlling department;Southeast University; 关键词：卫星整流罩 ; 透波口 ; 测量线 ; 卫星状态监视 ; 相对位置 英文关键词：Satellite fairing;;Permeable port;;Measurement line;;Satellite state monitoring;;Relative position 中文刊名：HTKZ 英文刊名：Aerospace Control 机构：中国卫星海上测控部;东南大学; 出版日期：2019-06-15 出版单位：航天控制 年：2019 期：v.37;No.179 语种：中文; 页：HTKZ201903007 页数：5 CN：03 ISSN：11-1989/V 分类号：37-41

摘要

针对风云系列近地轨道卫星铝合金蜂窝夹层结构的整流罩对无线电信号具有屏蔽功能,若在整流罩抛弃前接收卫星信号以监视卫星状态,就需要在卫星整流罩上开设透波口。提出了根据运载火箭理论飞行弹道设计结果和测站位置,计算测站跟踪运载火箭或卫星时,测量线在各时间节点的α和β角,并根据卫星天线装箭状态下在整流罩内的相对位置关系,精确计算测量线在整流罩壳体上轨迹的方法,设计出满足测站接收卫星信号的整流罩透波口开设的最小区域。既实现了整流罩抛弃前对卫星状态的监视,又最大限度地减小对卫星整流罩结构强度的影响,确保卫星整流罩的安全。
        Fengyun series low earth orbit satellite fairing with aluminum alloy honeycomb structure has shielding function for radio signal. To receive satellite signal to monitor the satellite status before discarding the fairing,it needs to open a wave through mouth in the fairing. According to the designated orbit of the launch vehicle and the position of station,the α and β angles of measuring line of tracking launch vehicle or satellite are calculated at each time node,and the projective line of the measuring line on the shell is also calculated according to the relative location of satellite in the fairing. Then,the minimum zone can be obtained,which can receive the satellite signal. It realizes the monitor of the satellite before the satellite discards fairing. Meanwhile,the affection is minimized for the structure strength of the fairing to ensure the safety of the fairing.

引文

[1]陈烈民.航天器结构与机构[M].北京:中国科学技术出版社,2005:66-84.(Chen L M.Spacecraft Structures and Mechanisms[M].Beijing:China Science and Technology Press,2005:66-84.)
    [2]陈福升,周玉娟.运载火箭卫星整流罩的材料与工艺[J].宇航材料工艺,1994,(1):38-39.(Chen F S,Zhou Y J.Material and Technology of Carrier Rocket Satellite Fairing[J].Aerospace Material&Technology,1994,(1):38-39.)
    [3]程昌,范开春,郭辉荣等.航天器整流罩结构优化设计.机械设计与制造[J],2013,(8):48-50.(Cheng C,Fan K C,Guo H R.The Structures Optimization Design of Spacecraft Fairing[J].Machinery Design&Manufacture,2013,(8):48-50.)
    [4]张必产.航天测控系统与天线应用[J].航天控制,1994,12(2):51-59.(Zhang B C.Space TT&C System and Antenna Application[J].Aerospace Control,1994,12(2):51-59.)
    [5]杨萍,郭军海,孙刚.航天测控系统卫星鉴定技术研究[J].航天控制,2008,26(1):65-68.(Yang P,Guo HJ,Sun G.The Research of Accuracy Evaluation by Satellite Technology For Space Tracking Telemetry and Command System[J].Aerospace Control,2008,26(1):65-68.)
    [6]宋青平,余跃,高军等.一种用于测控通信的抗干扰软扩频算法研究[J].航天控制,2016,34(6):76-78.(Song Q P,Yu Y,Gao J.A Tamed Spread Spectrum Algorithm for the Anti-Interference of Telemetry Tracking and Control[J].Aerospace Control,2016,34(6):76-78.)
    [7]刘冰,傅敏辉,薛国虎等.航天测量船海上测控任务分析与设计方法[M],北京:国防工业出版社,2015.(Liu B,Fu M H,Xue G H,et al.The Method of Analyze and Design for Marine Measurement and Control Task of Spacecraft TT&C Ship[M].Beijing:Beijing Aerodynamics Institute,2015.)
    [8]航天测控系统坐标系.中华人民共和国国家标准GJB2250A-2011[S]:成求青,邓洛凤,刘广军等,2011.(Coordinate System of Space TT&C System.State Standard of the People's Republic of China GJB 2250A-2011[S]:Cheng Q Q,Den L F,Liu G J,et al,2011.)