Design an aircraft.
Print the resulting mass statement to the command line. ------------------------------------------------------------------------- See also AircraftDesign, AircraftGroupMassStatement -------------------------------------------------------------------------
%-------------------------------------------------------------------------- % Copyright (c) 2013 Princeton Satellite Systems, Inc. % All rights reserved. %-------------------------------------------------------------------------- d.range = 15345; % km Newark to Singapore d.altitude = 25400; % km d.machClimb = 0.8; d.machCruise = 5; d.runway = 3; d.fPAClimb = 10; % deg d.fEngine = 'Scimitar'; d.nEngine = 4; d.tTaxi = 10; % Minutes d.nPassengers.economy = 210; d.nPassengers.business = 72; d.nPassengers.first = 32; d.fuselage.length = 70; d.fuselage.diameter = (4*20 + 10*18)*0.025400; d.nCrew = 2; d.mass = 100000; % Guess d.nAttendants = 8; d.rhoFuel = 85; % 67.8; % kg/m^2 slush 85 d.specificMassTank = 287/1250; d.s = 100; % m^2 d.length = 70; % m d.aspectRatio = 2; d.cLAlpha = 2*pi; d.thickness = 0.1; d.lOverD = 7; tol = 10; n = 10; d = AircraftDesign( d, n, tol ); j = strncmp('fuel',d.groupMass.group,5); mFuel = d.groupMass.mass(j); AircraftGroupMassStatement( mFuel, d.p, 'AircraftGroupMassStatement' ) % PSS internal file version information %--------------------------------------
Trip time = 3.13 hours
Group Mass (kg) Mass (%)
1. fuselage 58792.6 29.04
2. wing 4156.5 2.05
3. empennage horizontal 582.9 0.29
4. empennage vertical 259.5 0.13
5. nacelle 213.7 0.11
6. undercarriage 8098.2 4.00
7. power plant 1061.2 0.52
8. systems 22270.1 11.00
9. furnishings 13159.6 6.50
10. contingency 3036.8 1.50
11. crew 180.0 0.09
12. payload 28260.0 13.96
13. fuel 50735.2 25.06
14. fuel tank 11648.8 5.75
---------------- ------------ ------------
Total 202455.2 100.00
