def __init__(self, min_update_dt=1): super(OpenAP, self).__init__() self.min_update_dt = min_update_dt # second, minimum update dt self.current_sim_time = 0 # last update simulation time self.ac_warning = False # aircraft mdl to default warning self.eng_warning = False # aircraft engine to default warning self.coeff = coeff.Coefficient() with RegisterElementParameters(self): self.actypes = np.array([], dtype=str) self.phase = np.array([]) self.lifttype = np.array([]) # lift type, fixwing [1] or rotor [2] self.engnum = np.array([], dtype=int) # number of engines self.engthrust = np.array([]) # static engine thrust self.engbpr = np.array([]) # engine bypass ratio self.thrustratio = np.array([]) # thrust ratio at current alt spd self.ff_coeff_a = np.array([]) # icao fuel flows coefficient a self.ff_coeff_b = np.array([]) # icao fuel flows coefficient b self.ff_coeff_c = np.array([]) # icao fuel flows coefficient c self.engpower = np.array([]) # engine power, rotor ac self.cd0 = np.array([]) # zero drag coefficient self.cd0_clean = np.array([]) # Cd0, clean configuration self.cd0_gd = np.array([]) # Cd0, ground mode self.cd0_to = np.array([]) # Cd0, taking-off self.cd0_ic = np.array([]) # Cd0, initial climb self.cd0_ap = np.array([]) # Cd0, landing self.cd0_ld = np.array([]) # Cd0, landing self.k = np.array([]) # induced drag coeff
def __init__(self): super(OpenAP, self).__init__() self.ac_warning = False # aircraft mdl to default warning self.eng_warning = False # aircraft engine to default warning self.coeff = coeff.Coefficient() with RegisterElementParameters(self): self.actypes = np.array([], dtype=str) self.phase = np.array([]) self.lifttype = np.array([]) # lift type, fixwing [1] or rotor [2] self.mass = np.array([]) # mass of aircraft self.engnum = np.array([], dtype=int) # number of engines self.engthrmax = np.array([]) # static engine thrust self.engbpr = np.array([]) # engine bypass ratio self.thrust = np.array([]) # thrust ratio at current alt spd self.max_thrust = np.array([]) # thrust ratio at current alt spd self.ff_coeff_a = np.array([]) # icao fuel flows coefficient a self.ff_coeff_b = np.array([]) # icao fuel flows coefficient b self.ff_coeff_c = np.array([]) # icao fuel flows coefficient c self.engpower = np.array([]) # engine power, rotor ac self.cd0 = np.array([]) # zero drag coefficient self.cd0_clean = np.array([]) # Cd0, clean configuration self.k_clean = np.array([]) # k, clean configuration self.cd0_to = np.array([]) # Cd0, takeoff configuration self.k_to = np.array([]) # k, takeoff configuration self.cd0_ld = np.array([]) # Cd0, landing configuration self.k_ld = np.array([]) # k, landing configuration self.delta_cd_gear = np.array([]) # landing gear self.vmin = np.array([]) self.vmax = np.array([]) self.vminic = np.array([]) self.vminer = np.array([]) self.vminap = np.array([]) self.vmaxic = np.array([]) self.vmaxer = np.array([]) self.vmaxap = np.array([]) self.vsmin = np.array([]) self.vsmax = np.array([]) self.hmax = np.array([]) self.axmax = np.array([]) self.vminto = np.array([]) self.hcross = np.array([]) self.mmo = np.array([])
def __init__(self, min_update_dt=1): super(OpenAP, self).__init__() self.min_update_dt = min_update_dt # second, minimum update dt self.current_sim_time = 0 # last update simulation time self.ac_warning = False # aircraft mdl to default warning self.eng_warning = False # aircraft engine to default warning self.coeff = coeff.Coefficient() self.n_ac = 0 with RegisterElementParameters(self): self.actypes = np.array([], dtype=str) self.lifttype = np.array([]) # lift type, fixwing [1] or rotor [2] self.engnum = np.array([], dtype=int) # number of engines self.engthrust = np.array([]) # static engine thrust self.engbpr = np.array([]) # engine bypass ratio self.thrustratio = np.array([]) # thrust ratio at current alt spd self.ff_coeff_a = np.array([]) # icao fuel flows coefficient a self.ff_coeff_b = np.array([]) # icao fuel flows coefficient b self.ff_coeff_c = np.array([]) # icao fuel flows coefficient c self.engpower = np.array([]) # engine power, rotor ac