Contents
Demonstrate RectilinearMission - burn, coast, burn.
The spacecraft accelerates until it reaches a target maximum velocity and then it turns and decelerates. ------------------------------------------------------------------------ See also: Constant, RectilinearMission, Plot2D ------------------------------------------------------------------------
%-------------------------------------------------------------------------- % Copyright (c) 2012 Princeton Satellite Systems, Inc. % All rights reserved. %-------------------------------------------------------------------------- % Target distance: Alpha Centauri at 4.3 light years %--------------------------------------------------- c = Constant('speed of light')*1000; xF = 4.3*c*365.25*86400; % Exhaust velocity of engine (m/s) and thrust (N) %--------------------------------------------------- uE = 6e6; thrust = 160; % Spacecraft dry mass %-------------------- massDry = 4000; % Vary the maximum velocity as a fraction of the speed of light. The fuel % ratio obtained shows how much fuel must be carried to deliver the dry % mass of the spacecraft to the target distance. %------------------------------------------------------------------------ f = linspace(0.01,0.04); n = length(f); mF = zeros(1,n); t = zeros(1,n); eff = 0.5; for k = 1:n uMax = f(k)*c; [mX, tX] = RectilinearMission( thrust, massDry, uMax, uE, xF, eff ); mF(k) = mX(1); t(k) = tX(3); end
Plot
%------ t = t/(365.25*86400); Plot2D(f,[mF/massDry;t],'Fraction c',{'Fuel Ratio' 'Duration (yrs)'},'Mission'); % Built-in plot of RectilinearMission for a single uMax. Shows the mission % duration at which the target distance is reached and the velocity % profile. %------------------------------------------------------------------------- uMax = 0.02*c; RectilinearMission( thrust, massDry, uMax, uE, xF, eff ); %-------------------------------------- % $Date$ % $Id: 024c9b6c9c33a2aba66747e0e78278d5735beea7 $
