本文整理汇总了Python中SUAVE.Structure.Data.range方法的典型用法代码示例。如果您正苦于以下问题：Python Data.range方法的具体用法？Python Data.range怎么用？Python Data.range使用的例子？那么恭喜您, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类SUAVE.Structure.Data的用法示例。
在下文中一共展示了Data.range方法的2个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的Python代码示例。
示例1: evaluate_range_from_short_field
# 需要导入模块: from SUAVE.Structure import Data [as 别名]
# 或者: from SUAVE.Structure.Data import range [as 别名]
def evaluate_range_from_short_field(vehicle,mission,results):
# unpack
airport_short_field = mission.airport_short_field
tofl = airport_short_field.field_lenght
takeoff_config = vehicle.configs.takeoff
from SUAVE.Methods.Performance import find_takeoff_weight_given_tofl
# evaluate maximum allowable takeoff weight from a short field
tow_short_field = find_takeoff_weight_given_tofl(vehicle,takeoff_config,airport_short_field,tofl)
# determine maximum range based in tow short_field
from SUAVE.Methods.Performance import size_mission_range_given_weights
# unpack
cruise_segment_tag = 'Cruise'
mission_payload = vehicle.mass_properties.payload
# call function
distance,fuel = size_mission_range_given_weights(vehicle,mission,cruise_segment_tag,mission_payload,tow_short_field)
# pack
short_field = Data()
short_field.tag = 'short_field'
short_field.takeoff_weight = tow_short_field
short_field.range = distance
short_field.fuel = fuel
results.short_field = short_field
return results示例2: evaluate_PASS
# 需要导入模块: from SUAVE.Structure import Data [as 别名]
# 或者: from SUAVE.Structure.Data import range [as 别名]
def evaluate_PASS(vehicle,mission):
""" Compute the Pass Performance Calculations using SU AA 241 course notes
"""
# unpack
maxto = vehicle.Mass.mtow
mzfw_ratio = vehicle.Mass.fmzfw
sref = vehicle.Wing['Main Wing'].sref
sfc_sfcref = vehicle.Turbo_Fan['TheTurboFan'].sfc_TF
sls_thrust = vehicle.Turbo_Fan['TheTurboFan'].thrust_sls
eng_type = vehicle.Turbo_Fan['TheTurboFan'].type_engine
out = Data()
# Calculate
fuel_manuever = WeightManeuver(maxto)
fuel_climb_added = WeightClimbAdded(vehicle,mission,maxto)
reserve_fuel = FuelReserve(mission,maxto,mzfw_ratio,0)
out.range,fuel_cruise = CruiseRange(vehicle,mission,maxto,fuel_burn_maneuever,fuel_climb_added,reserve_fuel,sfc_sfcref,sls_thrust,eng_type,mzfw_ratio)
out.fuel_burn = (2 * fuel_manuever) + fuel_climb_added + fuel_cruise
out.tofl = TOFL(vehicle,mission,maxto,sref,sfc_sfcref,sls_thrust,eng_type)
out.climb_grad = ClimbGradient(vehicle,mission,maxto,sfc_sfcref,sls_thrust,eng_type)
out.lfl = LFL(vehicle,mission,maxto,mzfw_ratio,fuel_burn_maneuever,reserve_fuel,sref,sfc_sfcref,sls_thrust,eng_type)
return out