Contents
Calculate distance achieved for a 18 year mission
See also: Straight2DStructure, TripDistance, EngineReport
%-------------------------------------------------------------------------- % Copyright (c) 2017 Princeton Satellite Systems, Inc. % All rights reserved. %-------------------------------------------------------------------------- % Constants aU = Constant('au'); year = 365.25*86400; % Mission parameters years = 18; thrust = 6; % Set up problem d = Straight2DStructure; d.mP = 300; d.uE = 500; d.eta = 0.3; d.sigma = 1000; d.f = 0.02; d.tF = years*year; [dF,vF,vS,tS] = TripDistance( thrust, d ); d.dF = dF; [~,data] = EngineReport( thrust,d );
Output
k = 1;
s = {};
s{k,1} = 'Final position'; s{k,2} = sprintf('%12.2f',dF/aU); s{k,3} = 'AU'; k = k + 1;
s{k,1} = 'Final velocity'; s{k,2} = sprintf('%12.2f',vF); s{k,3} = 'km/s'; k = k + 1;
s{k,1} = 'Final time'; s{k,2} = sprintf('%12.2f',years); s{k,3} = 'yr'; k = k + 1;
s{k,1} = 'Fuel'; s{k,2} = sprintf('%12.2f',data.mF); s{k,3} = 'kg'; k = k + 1;
s{k,1} = 'Mass Total'; s{k,2} = sprintf('%12.2f',data.m0); s{k,3} = 'kg'; k = k + 1;
s{k,1} = 'Mass Engine'; s{k,2} = sprintf('%12.2f',data.mE); s{k,3} = 'kg'; k = k + 1;
s{k,1} = 'Mass Payload'; s{k,2} = sprintf('%12.2f',d.mP); s{k,3} = 'kg'; k = k + 1;
s{k,1} = 'Exhaust Velocity'; s{k,2} = sprintf('%12.2f',d.uE); s{k,3} = 'km/s'; k = k + 1;
s{k,1} = 'Power'; s{k,2} = sprintf('%12.2f',data.p/1e6); s{k,3} = 'MW'; k = k + 1;
s{k,1} = 'Thrust'; s{k,2} = sprintf('%12.2f',data.thrust); s{k,3} = 'N'; k = k + 1;
s{k,1} = 'Specific power'; s{k,2} = sprintf('%12.2f',d.sigma); s{k,3} = 'kW/kg'; k = k + 1;
s{k,1} = 'Efficiency'; s{k,2} = sprintf('%12.2f',d.eta); s{k,3} = ''; k = k + 1;
s{k,1} = 'Tank fraction'; s{k,2} = sprintf('%12.2f',d.f); s{k,3} = '';
DisplayLatexTable(s)
CreateLatexTable(s,'PointDesignSGL')
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% PSS internal file version information
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% $Date$
% $Id: 1b54d5350080536c38df10defd606c135b49b8c2 $
Final position 380.49 AU
Final velocity 0.00 km/s
Final time 18.00 yr
Fuel 6816.44 kg
Mass Total 12252.77 kg
Mass Engine 5000.00 kg
Mass Payload 300.00 kg
Exhaust Velocity 500.00 km/s
Power 5.00 MW
Thrust 6.00 N
Specific power 1000.00 kW/kg
Efficiency 0.30
Tank fraction 0.02