微带天线对GPS卫星的可视性计算方法  

Computation Method and Simulation of GPS Visibility to Micro-strip Antenna

作　　者：屈新芬[1] 李世玲[1] 谭惠民[2] 胡兆权[1] 

机构地区：[1]中国工程物理研究院电子工程研究所,四川绵阳621900 [2]北京理工大学机电工程学院,北京100081

出　　处：《探测与控制学报》2006年第5期8-11,共4页Journal of Detection & Control

基　　金：中国工程物理研究院科学技术基金(20060325)和行业重点预研(426010502-3)资助项目

摘　　要：在空中高动态飞行的旋转载体内GPS接收微带天线安装于载体内随动平台上是一较佳的选择方案,载体本身和地球是影响该微带天线对GPS卫星可视与否的主要因素。针对此,在坐标转换理论的基础上,结合载体的飞行环境,从理论的角度推导了在载体和地球遮挡下,微带天线对卫星的可视性条件及计算方法;结合GPS卫星在轨位置预测公式和某一载体在某一时间段内的轨道参数,对微带天线对卫星的可视性进行了仿真,给出了载体飞行过程中微带天线可视的卫星。For the complex and large - scale electronic system, setting up the simulation system in the laboratory is one main part of the system design. Besides, the computation of GPS visibility to the spacecraft is one part of the design for the simulation system. For a fast revolving spacecraft, in order to receive better and reliable GPS wireless information, fixing the micro-strip antenna on the plat controlled by the information of INS is a better scheme, the plat is kept stable or rotating slowly relative to a reference system. Under this case, the earth and the spacecraft are the main factors to keep the spacecraft out of GPS. In this paper, based on the theory of the coordinate transformation, the computation method of GPS visibility to the spacecraft under the shade of the earth and the spacecraft is deduced, and the precondition of GPS visibility is given. The simulation computation model of GPS visibility is presented, and some simulation results of GPS visibility to specific flight time of the spacecraft are given.

关 键 词：慢旋载体 GPS卫星 微带天线 坐标转换 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]