Low thrust geo transfer

Corrects both semi-major axis and inclination. It corrects the semi-major axis first then the inclination. Uses a right-hand-side function in the script.

See also: OrbMnvrPhaseChange

Contents

%--------------------------------------------------------------------------
%   Copyright (c) 2017 Princeton Satellite Systems, Inc.
%   All Rights Reserved.
%--------------------------------------------------------------------------
%   Since 2017.1
%--------------------------------------------------------------------------

Parameters

elS     = [42167 0 0 0 0 0];
elT     = [42167 0 0 0 0 pi/4];
dT      = 10;
hours   = 8;
deltaA	= pi/16;

[r,v]   = El2RV(elS);
[rT,vT] = El2RV(elT);
vMagGeo = Mag(v);
tEnd    = hours*3600;
n       = ceil(tEnd/dT);
xP      = zeros(12,n);
x       = [r;v;rT;vT];
r2      = RVOrbGen(elT,tEnd);
vChase  = LambertTOF( r, r2, tEnd );
x(4:6)  = vChase(:,1);

Simulate

for k = 1:n
  xP(:,k) = x;
  x       = RK4(@RHS,x,dT,0);
end

Plot

[t,tL] = TimeLabl((0:n-1)*dT);
NewFig('Orbits')
plot(xP(1,:),xP(2,:),'r');
hold on
plot(xP(7,:),xP(8,:),'g');
legend('Chase','Target')
plot(xP(1,1),xP(2,1),'ro');
plot(xP(7,1),xP(7,1),'go');
grid on
axis image
yL = { '\Delta r (km)' '|v| (km/s)'};
dR = Mag(xP(7:8,:) - xP(1:2,:));
vMag = Mag(xP(4:6,:));
Plot2D(t,[dR;vMag;vMagGeo*ones(1,n)],tL,yL,'Maneuver','lin',{'1' '[2 3]'})
legend('Satellite', 'Geo','location','best')

function xDot = RHS(x,~)

Right hand side

r     = x(1:3);
v     = x(4:6);
rT    = x(7:9);
vT    = x(10:12);
mu    = 3.98600436e5;
xDot  = [v;-mu*r/Mag(r)^3;vT;-mu*rT/Mag(rT)^3];

end


%--------------------------------------

Published with MATLAB® R2019a