AircraftDesign:

Path: ACPro/ACDesign

% Design an aircraft.

   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, p );

   where p is the datastructure from StdAtm.

--------------------------------------------------------------------------
   Form:
   d = AircraftDesign( d, n, tol, p )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   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
   -------
   Outputs
   -------
   d       (1,1)   Data structure

--------------------------------------------------------------------------

Children:

AC: Aircraft/AircraftGroupDataStructure
AC: Aircraft/AircraftGroupMass
ACPro: ACDesign/AircraftGroupMassStatement
ACPro: ACPerformance/FuelFromRange
ACPro: ACProAerodynamics/LiftToDragFromMach
ACPro: Airbreathing/Scimitar
AerospaceUtils: AeroData/AtmData
Common: Atmosphere/StdAtm
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/CreateLatexTable
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Math: Trigonometry/TanD

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