ECI与ECEF坐标变换

ECI与ECEF坐标变换 matlab代码

%----------------------- Begin Code Sequence -----------------------------%
% Purpose:                                                                %
% Convert ECI （CIS Epoch J2000.0） Coordinates to WGS 84 （CTS ECEF）      %
% Coordinates. This function has been vectorized for speed.               %
%                                                                         %
% Inputs:                                                                 %
%-------                                                                  %
%JD                     [1 x N]                         Julian Date Vector
%
%r_ECI                  [3 x N]                         Position Vector
%                                                       in ECI coordinate
%                                                       frame of reference
%
%v_ECI                  [3 x N]                         Velocity Vector in
%                                                       ECI coordinate
%                                                       frame of reference
%
%a_ECI                  [3 x N]                         Acceleration Vector
%                                                       in ECI coordinate
%                                                       frame of reference
%
%
% Outputs:
%---------                                                                %
%r_ECEF                 [3 x N]                         Position Vector in
%                                                       ECEF coordinate
%                                                       frame of reference
%
%v_ECEF                 [3 x N]                         Velocity vector in
%                                                       ECEF coordinate
%                                                       frame of reference
%
%a_ECEF                 [3 x N]                         Acceleration Vector
%                                                       in ECEF coordinate
%                                                       frame of reference
%
% References:
%-------------
%Orbital Mechanics with Numerit http://www.cdeagle.com/omnum/pdf/csystems.pdf
%
%
% Function Dependencies:
%------------------
% JD2GMST
%------------------------------------------------------------------       %
% Programed by Darin Koblick  07-05-2010                                  %
% Modified on 03/01/2012 to add acceleration vector support               %
%------------------------------------------------------------------       %
function [r_ECEF v_ECEF a_ECEF] = ECItoECEF（JDr_ECIv_ECIa_ECI）
%Enforce JD to be [N x 1]
JD = JD（:）;

%Calculate the Greenwich Apparent Sideral Time （THETA）
%See http://www.cdeagle.com/omnum/pdf/csystems.pdf equation 27
THETA = JD2GAST（JD）;

%Average inertial rotation rate of the earth radians per second
omega_e = 7.29211585275553e-005;

%Assemble the transformation matricies to go from ECI to ECEF
%See http://www.c

 属性            大小     日期    时间   名称
----------- ---------  ---------- -----  ----
     文件        4257  2012-03-01 07:15  ECItoECEF.m
     文件        2304  2012-05-28 17:31  JD2GAST.m
     文件        1669  2012-03-01 07:15  JD2GMST.m
     文件        1334  2012-05-28 20:40  license.txt