Simulate a departure from the Earth

Treat the problem as planar.

See also TwoDEscape, Date2JD, TimeLabl

%--------------------------------------------------------------------------
%   Copyright (c) 2016 Princeton Satellite Systems, Inc.
%   All rights reserved.
%--------------------------------------------------------------------------
%   Since 2017.1
%--------------------------------------------------------------------------

rE      = Constant('equatorial radius earth');
r       = rE + 386;
mu      = Constant('mu earth');
uE      = 100e3; % exhaust velocity [m/s]
m0      = 3500;  % initial mass
mF      = 4000;  % fuel mass
jD0     = Date2JD([2024 5 5 0 0 0]);
thrust  = 10;    % N
[mP,x,t] = TwoDEscape( mu, r, uE, thrust, m0, mF, [1000 6000]+rE );

return
n       = length(t);
rP      = [x(1:2,:);zeros(1,n)];
vP      = [x(3:4,:);zeros(1,n)];
jD      = jD0 + t/86400;
b       = BDipole( rP, jD );
m       = Unit(vP);

[t,tL]  = TimeLabl(t);

% torque from coils during departure
i       = 3e6; % A
a       = 0.5; % m
nCoils  = 8;
mMag    = pi*a^2*i*nCoils; % Dipole

torque  = mMag*Cross(m,b);
torque  = [torque;Mag(torque)];
yL      = {'T_x (Nm)' 'T_y (Nm)' 'T_z (Nm)' '|T| (Nm)'};
s       = sprintf('Torque due to %d %4.1f MA Coils',nCoils,i/1e6);
Plot2D(t,torque,tL,yL,s);


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

Spiral time:         58.49 days
Fuel consumed:       505.37 kg
Final radius:     464244.94 km
Delta-V:               6.98 km/s
Time in radiation belt: 14.37 day