www.pudn.com > GNSS_SDR.zip > e_r_corr.m, change:2006-08-22,size:1135b


function X_sat_rot = e_r_corr(traveltime, X_sat) 
%E_R_CORR  Returns rotated satellite ECEF coordinates due to Earth 
%rotation during signal travel time 
% 
%X_sat_rot = e_r_corr(traveltime, X_sat); 
% 
%   Inputs: 
%       travelTime  - signal travel time 
%       X_sat       - satellite's ECEF coordinates 
% 
%   Outputs: 
%       X_sat_rot   - rotated satellite's coordinates (ECEF) 
 
%Written by Kai Borre 
%Copyright (c) by Kai Borre 
% 
% CVS record: 
% $Id: e_r_corr.m,v 1.1.1.1.2.6 2006/08/22 13:45:59 dpl Exp $ 
%========================================================================== 
 
Omegae_dot = 7.292115147e-5;           %  rad/sec 
 
%--- Find rotation angle -------------------------------------------------- 
omegatau   = Omegae_dot * traveltime; 
 
%--- Make a rotation matrix ----------------------------------------------- 
R3 = [ cos(omegatau)    sin(omegatau)   0; 
      -sin(omegatau)    cos(omegatau)   0; 
       0                0               1]; 
 
%--- Do the rotation ------------------------------------------------------ 
X_sat_rot = R3 * X_sat; 
 
%%%%%%%% end e_r_corr.m %%%%%%%%%%%%%%%%%%%%