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
