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Path: ACPro/ACDesign
% Design an aircraft for a trajectory.
The function generates the group mass statement for the aircraft from
the range, speed and altitude of the aircraft along with the number of
passengers and the payload. The input is a data structure described
below.
The function fEngine is of the form
[thrust, sfc] = MyEngine( mach, altitude );
Since Version 5.
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Form:
d = AircraftDesign( d, n, tol, p )
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Inputs
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d (1,1) Data structure
.range (1,1) Aircraft range (km)
.altitude (1,1) Cruise altitude (km)
.machClimb (1,1) Climb and descent Mach
.machCruise (1,1) Cruise Mach
.runway (1,1) Runway length (m)
.fPAClimb (1,1) Climb flight path angle (rad)
.fEngine (1,:) Engine function
.nEngine (1,1) Number of engines
.tTaxi (1,1) Taxiing time (min)
.nPassengers.economy (1,1) Number of passengers economy
.nPassengers.business (1,1) Number of passengers business
.nPassengers.first (1,1) Number of passengers first
.fuselage.length (1,1) Fuselage length (m)
.fuselage.diameter (1,1) Fuselage diameter (m)
.nCrew (1,1) Number of flight crew
.mass (1,1) Mass (kg)
.nAttendants (1,1) Number of attendants
.rhoFuel (1,1) Fuel density (kg/m^3)
.specificMassTank (1,1) Fuel tank specific mass (kg/kg)
.s (1,1) Wing area (m^2)
.length (1,1) Wing chord (m)
.aspectRatio (1,1) Wing aspect ratio
.cLAlpha (1,1) Lift coefficient (1/rad)
.thickness (1,1) Wing thickness ratio
.lOverD (1,1) Lift/Drag
n (1,1) Steps per segment
tol (1,1) Tolerance for the mass computation (kg)
p (1,1) Group mass datastructure -
see AircraftGroupDataStructure
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Outputs
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d (1,1) Data structure
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ACPro: ACDesign/AircraftGroupMassStatement ACPro: ACPerformance/AircraftGroupDataStructure ACPro: ACPerformance/FuelFromRange Common: Atmosphere/StdAtm Common: Graphics/Plot2D Math: Trigonometry/TanD
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