Commit ebcc2527 authored by aelkawas's avatar aelkawas
Browse files

trash merging

parent 7aeb9aa5
Re = 6378;
mu = 398600.4;
R0 = [-8.058685464116713e+002;...
-4.135050989428283e+003;...
5.071447347723579e+003];
R0 = [7016;...
0;...
0];
V0 = [6.04068079277917;
3.52422658592595;
3.83339310219652];
V0 = [0;
7.5374;
0];
X0 = [R0; V0];
......
Re = 6378;
mu = 398600.4;
a_p = 638+Re;%parking orbit
i_p = 46 *pi/180; %average inclnation
e=0;
RAAN =0;
ArgofPerigee = 0;
p = a_p;
r= p;
trueAnomoly = 0; %Assumpion
%p.117 notes: Direction Cosine Matrix
OPG = [cos(ArgofPerigee) sin(ArgofPerigee) 0;...
-sin(ArgofPerigee) cos(ArgofPerigee) 0; 0 0 1]...
*[1 0 0; 0 cos(i_p) sin(i_p ); 0 -sin(i_p ) cos(i_p)]...
*[cos(RAAN) sin(RAAN) 0; -sin(RAAN) cos(RAAN) 0; 0 0 1]; %check this
%At perifocal frame p.115
rVec = [r*cos(trueAnomoly); r*sin(trueAnomoly); 0];
vVec = [-sin(trueAnomoly)*sqrt(mu/p); (e+cos(trueAnomoly))...
*sqrt(mu/p); 0];
%From Perifocal to ECI
rG = OPG.' * rVec;
rdotG = OPG.' * vVec;
# Aero343 Project - Satellite Taxi
Satellite taxi concept project as part of the Aero 343 Class
Authors: Sidharth Anantha, Ahmed Al Kawas, Rutvik Marathe
function Xdot = newton(t, X)
mu = 398600.4405;
r= X(1:3);
v = X(4:6);
Xdot(1:3) = v;
rn = norm(r);
Xdot(4:6) = -mu/rn^3*r;
Xdot = Xdot(:);
return;
\ No newline at end of file
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