MissileMassEstimation:

Path: ACPro/ACDesign

% Computes missile weight. 

 This is an alternative to AircraftGroupMassStatement that uses a
 different weight model. The model is based on R. Miller's model from
 MIT course 16.751. If you enter fileName it will create a file
 with a latex table. It is similar to HSVMassEstimation except that
 it uses range as an input and does not include landing gear.

 Not all values of parameters will produce a feasible design. If the 
 weight goes to infinity you will need to adjust some of your
 parameters. See the demo for a working set of inputs.

--------------------------------------------------------------------------
   Form:
   d       = MissileMassEstimation; % Return default data structure
   [g, h]  = MissileMassEstimation( d, tol, fileName )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   d           (.)	Data structure
                       .massPayload            (1,1) Mass of payload 
                       .dFuselage              (1,1) Fuselage diameter (m)
                       .lFuselage              (1,1) Fuselage length (m)
                       .wingLoading            (1,1) Wing loading (kg/m^2)
                       .structuralLF           (1,1) Structural load factor
                       .thicknessRatio         (1,1) Thickness Ratio
                       .sweepAngle             (1,1) Sweep ratio
                       .tipRootChordRatio      (1,1) Tip Chord/Root Chord
                       .aspectRatio            (1,1) Aspect ratio
                       .fuelStructuralFraction	(1,1) Fuel to gross weight ratio
                       .massEngine             (1,1) Engine mass
                       .fSMaterial             (1,1) Factor to adjust for materials
                       .range                  (1,1) Range (km)
                       .vCruise                (1,1) Cruise velocity (m/s)
   tol         (1,1) Tolerance on computation
   fileName    (1,:) Filename for the latex table (for one design)

   -------
   Outputs
   -------
   g           (.)   Data structure
                       .gM             (1,1)  Gross mass
                       .wing           (1,1)  Wing mass
                       .fuselageWT     (1,1)  Fuselage mass
                       .engineWT       (1,1)  Engine mass
                       .fuelWT         (1,1)  Fuel mass
                       .fixedEWT      	(1,1)  Fixed equipment mass
                       .empWT          (!,1)  Empanage mass
                       .landingGear    (1,1)  Landing gear mass
                       .payload        (1,1)  Payload mass   
                       .misc           (1,1)  Everything else
   h            (.)  Data structure
                       .wingArea       (1,1)  Wing area
                       .mF             (1,1)  Mass fueld

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

Children:

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

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