?? vecefeci.m
字號:
% vecefeci.m
% Scope: This MATLAB macro performs the transformation from ECEF to ECI
% (Earth Centered Inertial) coordinates for a given position vector
% and time elapsed since reference time; WGS-84 earth's rotation
% rate constant is used.
% Usage: peci = vecefeci(pecef,dtime)
% Description of parameters:
% pecef - input, ECEF position vector (with components in meters)
% dtime - input, time elapsed since reference time in seconds
% peci - output, ECI position vector, with components in
% same units as the input ECEF position vector
% Remarks: The ECEF to ECI transformation takes into account only Earth's
% rotation, i.e. no Earth's precession and mutation effects.
% External Matlab macros used: wgs84con
% Last update: 04/05/00
% Copyright (C) 1997-00 by LL Consulting. All Rights Reserved.
function peci = vecefeci(pecef,dtime)
wgs84con;
% global constants used: rot_rate (WGS-84 earth's rotation rate, in rad/sec)
swie = sin(rot_rate*dtime);
cwie = cos(rot_rate*dtime);
peci = zeros(3,1);
peci(1) = pecef(1) * cwie - pecef(2) * swie;
peci(2) = pecef(1) * swie + pecef(2) * cwie;
peci(3) = pecef(3);
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