def WeightClimbAdded(vehicle, mission, maxto): """Fuel increment added to cruise fuel burned over distance when aircraft is climbing to the cruise altitude Assumptions: Inputs: mission.segments['Initial Cruise'].mach mission.segments['Initial Cruise'].atmo mission.segments['Initial Cruise'].alt Outputs: fuel_burn_climb_inc """ # AA 241 Notes Section 11.3 # Atmosphere atmo = mission.segments['Initial Cruise'].atmo atm = Atmosphere() atm.alt = mission.segments['Initial Cruise'].alt # in km atm.dt = 0.0 #Return ISA+(value)C properties Climate.EarthIntlStandardAtmosphere(atm) # Unpack cruise_mach = mission.segments['Initial Cruise'].mach speed_of_sound = atm.vsnd #in m/s # Calculate cruise_speed = speed_of_sound * cruise_mach / 1000 * 3600 # in km/hr cruise_velocity = Units.ConvertDistance(cruise_speed, 'km', 'nm') #Converting to knots alt_kft = Units.ConvertLength(alt * 1000, 'm', 'ft') / 1000 #Converting to kft fuel_burn_climb_inc = maxto * (alt_kft / 31.6 + (cruise_velocity / 844)**2) return fuel_burn_climb_inc