ECI惯性坐标系转ECEF地心地固坐标系

Convert ECI (CIS, Epoch J2000.0) Coordinates to WGS 84 (CTS, ECEF)

%----------------------- 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               %
% Modified by LHC on 2016-03-02 to add nargin                             %
%------------------------------------------------------------------       %
function [r_ECEF v_ECEF a_ECEF] = ECItoECEF（JDr_ECIv_ECIa_ECI）
if nargin<2 || nargin>4
    error（‘input num error‘）;
end
%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 ea

 属性            大小     日期    时间   名称
----------- ---------  ---------- -----  ----

     文件       2304  2014-02-12 14:01  JD2GAST.m

     文件       1669  2014-02-12 14:01  JD2GMST.m

     文件       4915  2016-03-02 09:36  ECItoECEF.m

----------- ---------  ---------- -----  ----

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