Ejemplo n.º 1
0
 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)
Ejemplo n.º 2
0
def run_test5():
    import convert
    ac = load('X47B')
    mis = mission_profile.load('profile3')
    wf = ac.get_mission_fuel(mis)
    wTO = ac.get_mass()
    wE  = ac.get_mass_empty()
    
    print convert.kg_to_lb(wf)
    print convert.kg_to_lb(wTO)
    print convert.kg_to_lb(wE)
Ejemplo n.º 3
0
 def _mass_engine_section(self):
     cg = self.emptyMass.get_item_cg_by_name('engine')
     We = convert.kg_to_lb(self.ac.propulsion.engine.mass)
     m = 0.01*We**0.717*self.Ne*self.Nz
     self._add_mass1('engine section',m,cg)