地心地固坐标系ECEF转地心惯性系ECI matlab代码

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

%----------------------- Begin Code Sequence -----------------------------%
% Purpose:                                                                %
% Convert WGS 84 （CTS ECEF） Coordinates to ECI （CIS Epoch J2000.0）      %
% Coordinates. This function has been vectorized for speed.               %
%                                                                         %
% Inputs:                                                                 %
%-------                                                                  %
%JD                     [1 x N]                         Julian Date Vector
%
%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
%

%
% Outputs:
%---------                                                                %
%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
%
% References:
%-------------
%Orbital Mechanics with Numerit http://www.cdeagle.com/omnum/pdf/csystems.pdf
%
%
% Function Dependencies:
%------------------
% JD2GMST
%------------------------------------------------------------------       %
% Programed by Darin Koblick  07-17-2010                                  %
% Modified on 03/01/2012 to add acceleration vector support               %
%------------------------------------------------------------------       %
function [r_ECI v_ECI a_ECI] = ECEFtoECI（JDr_ECEFv_ECEFa_ECEF）
%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 ECEF to ECI
%See http://w

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

     文件       2123  2014-02-12 13:52  JD2GAST.m

     文件       1669  2014-02-12 13:52  JD2GMST.m

     文件       4482  2016-02-01 14:43  ECEFtoECI.m

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

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