Code covered by the BSD License
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CalcEA(M,ecc,tol)
Orbit eccentric anomaly, Kepler's equation keplers equation
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Groundtrack(Kepler,GMSTo,Tf,f...
Orbit groundtrack plot Latitude longitude lat long
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Hohmann(R_init,R_fin,U)
Orbit Hohmann transfer
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JD(yr,day)
Julian Date
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KeplerCOE(Ro,Vo,dT,U,tol)
Orbit Kepler position velocity
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NodeChange(dO,inc,Vinit)
Node change right ascension of the ascending node RAAN raan orbit
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R1(x)
Rotation matrix direction cosine matrix
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R2(x)
Rotation matrix direction cosine matrix
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R3(x)
Rotation matrix direction cosine matrix
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RVtoLatLong(ECEF)
orbit radius velocity latitude longitude ECEF
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TwoBody(t,X,U)
Two body Orbit gravity
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dInc(V,dI,fpa)
Inclination change orbit gravity
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dVdI(R_init,R_fin,Inc,U,Tol)
Inclination change velocity change orbit hohmann transfer
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ecef2eci(ECEF, GST, V_ECEF)
Orbit ECEF ECI Coordinate conversion
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eci2ecef(ECI, GST, V_ECI)
Orbit ECEF ECI Coordinate conversion
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elorb(R,V,U,tol)
Kepler orbital elements ECI Position orbit conversion
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nuFromM(M,ecc,tol)
Kepler Orbit Anomaly true mean
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nuFromTp(Tp,ecc,n,tol)
Kepler Orbit Anomaly true time periapse perigee
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plotorb(ECEF, V_ECEF, mu, Rbo...
Orbit gravity plot orbit spherical
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randv(a,ecc,inc,Omega,w,nu,U)
Kepler orbital elements ECI Position orbit conversion
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topo(ECEF, lat, long, h, Rp)
Orbit range elevation azimuth position ground station site latitude longitude
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zeroTo360(x,unit)
Angle reduce reduction degrees radians
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Constants.m
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View all files
from
Orbital Mechanics Library
by Richard Rieber
A compilation of all of the functions I wrote for my orbital mechanics class
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| R3(x)
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%Rotation matrix direction cosine matrix
% Richard Rieber
% September 21, 2006
% rrieber@gmail.com
%
% Revision 8/21/07: Deleted unneeded ; in function name.
% Added example.
% Added H1 line for lookfor functionality
%
% function A = R3(x)
%
% This function creates a rotation matrix about the 3-axis (or the Z-axis)
%
% A = [cos(x) sin(x) 0;
% -sin(x) cos(x) 0;
% 0 0 1];
%
% Inputs: x - rotation angle in radians
% Outputs: A - the rotation matrix about the Z-axis
%
% EXAMPLE:
%
% R3(pi/4) =
% 0.7071 0.7071 0
% -0.7071 0.7071 0
% 0 0 1.0000
function A = R3(x)
if nargin > 1
error('Too many inputs. See help file')
end
A = [cos(x) sin(x) 0;
-sin(x) cos(x) 0;
0 0 1];
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