def weight(nexus):
vehicle = nexus.vehicle_configurations.base
# weight analysis
weights = nexus.analyses.base.weights.evaluate()
# print "nexus_rest"
compute_component_centers_of_gravity(vehicle)
nose_load_fraction = .06
compute_aircraft_center_of_gravity(vehicle, nose_load_fraction)
weights = nexus.analyses.cruise.weights.evaluate()
# print weights # FIXME
weights = nexus.analyses.landing.weights.evaluate()
# print weights
weights = nexus.analyses.takeoff.weights.evaluate()
# weights = nexus.analyses.short_field_takeoff.weights.evaluate()
empty_weight = vehicle.mass_properties.operating_empty
passenger_weight = 0
for config in nexus.vehicle_configurations:
# config.mass_properties.max_zero_fuel = empty_weight+passenger_weight
config.mass_properties.zero_fuel_center_of_gravity = vehicle.mass_properties.zero_fuel_center_of_gravity
config.fuel = vehicle.fuel
return nexus
def weight(nexus):
vehicle = nexus.vehicle_configurations.base
# weight analysis
weights = nexus.analyses.base.weights.evaluate()
# print "nexus_rest"
compute_component_centers_of_gravity(vehicle)
nose_load_fraction = .06
compute_aircraft_center_of_gravity(vehicle, nose_load_fraction)
weights = nexus.analyses.cruise.weights.evaluate()
# print weights # FIXME
weights = nexus.analyses.landing.weights.evaluate()
# print weights
weights = nexus.analyses.takeoff.weights.evaluate()
# weights = nexus.analyses.short_field_takeoff.weights.evaluate()
empty_weight = vehicle.mass_properties.operating_empty
passenger_weight = 0
for config in nexus.vehicle_configurations:
# config.mass_properties.max_zero_fuel = empty_weight+passenger_weight
config.mass_properties.zero_fuel_center_of_gravity = vehicle.mass_properties.zero_fuel_center_of_gravity
config.fuel = vehicle.fuel
return nexus
def simple_sizing(configs, analyses):
base = configs.base
base.pull_base()
# zero fuel weight
base.mass_properties.max_zero_fuel = 0.9 * base.mass_properties.max_takeoff
# wing areas
for wing in base.wings:
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
# fuselage seats
base.fuselages['fuselage'].number_coach_seats = base.passengers
# weight analysis
#need to put here, otherwise it won't be updated
weights = analyses.configs.base.weights
breakdown = weights.evaluate()
#compute centers of gravity
#need to put here, otherwise, results won't be stored
compute_component_centers_of_gravity(base,compute_propulsor_origin=True)
compute_aircraft_center_of_gravity(base)
# diff the new data
base.store_diff()
# ------------------------------------------------------------------
# Landing Configuration
# ------------------------------------------------------------------
landing = configs.landing
# make sure base data is current
landing.pull_base()
# landing weight
landing.mass_properties.landing = 0.85 * base.mass_properties.takeoff
# diff the new data
landing.store_diff()
# done!
return