def _get_data(self):
self._get_coefficients()
self.Nz = 1.5 * self.ac.designGoals.loadFactor # ultimate load factor
self.Wdg = convert.kg_to_lb(self.ac.designGoals.grossMass)
self.Nl = self.ac.designGoals.loadFactorLanding
self.Wt = self.Wdg
self.Wl = self.Wdg
self.Ne = self.ac.propulsion.numberOfEngines
self.T = convert.kgf_to_lbf(self.ac.propulsion.totalThrust)
self.mUav = convert.kg_to_lb(self.ac.designGoals.avionicsMass)
Vi = self.ac.designGoals.fuelMass/self.fuelProp['kerosene']
self.Vi = convert.cubm_to_gal(Vi)
def _mass_starter_pneumatic(self):
Te = convert.kgf_to_lbf(self.ac.propulsion.engine.thrustMC)
m = 0.025*Te**0.760*self.Ne**0.72
self._add_mass1('engine starter',m)
