Simulate a departure from the Earth

Treat the problem as planar. Uses a thrust and mass consistent with an SGL mission. See also: TwoDEscape

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%   Copyright (c) 2016 Princeton Satellite Systems, Inc.
%   All rights reserved.
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%   Since 2017.1
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rE        = Constant('equatorial radius earth');
r         = rE + 386;
mu        = Constant('mu earth');
power     = 1.7e6; % W
eff       = 0.3;
thrust    = 10;    % N
uE        = 2*eff*power/thrust;
mF        = 400;   % kg
m0        = 5282 + mF;  % initial mass
jD0       = Date2JD([2024 5 5 0 0 0]);
[mP,x,t]  = TwoDEscape( mu, r, uE, thrust, m0, mF, [1000 6000]+rE );


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% $Id: 7b6f59f94d067335017dd8200a62f026c3423e8b $

Spiral time:               47.22 days
Fuel consumed:            399.97 kg
Final radius:          418477.12 km
Delta-V:                    6.94 km/s
Exhaust velocity:         102.00 km/s
Time in radiation belt: 1.67 week