Maneuver from Gateway to 15 km

A two maneuver sequence to go from the Gateway orbit to a 15 km circular orbit.

%--------------------------------------------------------------------------
%   Copyright (c) 2019 Princeton Satellite Systems, Inc.
%   All rights reserved.
%--------------------------------------------------------------------------
%   Since 2019.1
%--------------------------------------------------------------------------

% Constants
mu        = Constant('mu moon');
rM        = Constant('equatorial radius moon');

% Gateway
rA        = 70000;
rP        = 3000;
[a, e]    = RPRA2AE( rP, rA );
el        = [a pi/2 0 0 e 0];

% For plotting
OrbMnvrLowerApogee( el, rP, mu );

% Circularize
deltaVLA  = OrbMnvrLowerApogee( el, rP, mu );

% Hohman
rF        = 15+rM;
deltaVH   = DVHoh( rP, 15+rM, [], mu );

fprintf('Gateway Apolune                 %8.2f km\n',rA);
fprintf('Gateway Perilune                %8.2f km\n',rP);
fprintf('Final orbit radius              %8.2f km\n',rF);
fprintf('Cicularization maneuver delta v    %5.2f km/s\n',deltaVLA);
fprintf('Hohmann maneuver        delta v    %5.2f km/s\n',deltaVH);

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

Gateway Apolune                 70000.00 km
Gateway Perilune                 3000.00 km
Final orbit radius               1753.00 km
Cicularization maneuver delta v     0.49 km/s
Hohmann maneuver        delta v     0.39 km/s

Published with MATLAB® R2020a