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
