Path: ACPro/ACDesign
% AIRCRAFTWEIGHTS Compute weights using a simple model.
The function generates the weights for an aircraft as a function
of flight phase.
frac is optional. Defaults are from Rayment.
It uses the Bregeut range equation for cruise.
Takeoff, climb and landiing use frac. 1-w(5) is the fraction of fuel.
Type AircraftWeights for a demo of a 747-300
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Form:
[w,phase,wFR] = AircraftWeights(range, iSp, lD, u, frac)
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Inputs
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range (1,1) Range (km)
iSp (1,1) Cruise specific impulse (s)
lD (1,1) Cruise lift/drag ratio
u (1,1) Cruise velocity (km/hr)
frac (1,3) Fractional weight after [takeoff climb landing]
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Outputs
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w (1,5) Weight
phase {1,5} Corresponding phase
wFR (1,1) Weight fuel/Weight takeoff
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Common: Graphics/NewFig
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