Simulate a low thrust departure from the Earth

Treat the problem as planar. Creates a plot of the simulated spiral and a time history plot of the delta-V, fuel consumed, and orbit eccentricity.

%--------------------------------------------------------------------------
%   Copyright (c) 2018 Princeton Satellite Systems, Inc.
%   All rights reserved.
%--------------------------------------------------------------------------
%   Since 2018.1
%--------------------------------------------------------------------------

rI      = Constant('equatorial radius earth') + 386;
mu      = Constant('mu earth');
uE      = 120e3;
m0      = 40000; % Dry mass
mF      = 10000; % Fuel
thrust  = 200;
TwoDEscape( mu, rI, uE, thrust, m0, mF );


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

% $Id: ce63040114530fd2a89c0550f5405afabf1fb956 $

Spiral time:               19.01 days
Fuel consumed:           2737.95 kg
Final radius:          269950.35 km
Delta-V:                    6.76 km/s
Exhaust velocity:         120.00 km/s

Published with MATLAB® R2024a