aerosandbox.library.weights.raymer_cargo_transport_weights ========================================================== .. py:module:: aerosandbox.library.weights.raymer_cargo_transport_weights Functions --------- .. autoapisummary:: aerosandbox.library.weights.raymer_cargo_transport_weights.mass_wing aerosandbox.library.weights.raymer_cargo_transport_weights.mass_hstab aerosandbox.library.weights.raymer_cargo_transport_weights.mass_vstab aerosandbox.library.weights.raymer_cargo_transport_weights.mass_fuselage aerosandbox.library.weights.raymer_cargo_transport_weights.mass_main_landing_gear aerosandbox.library.weights.raymer_cargo_transport_weights.mass_nose_landing_gear aerosandbox.library.weights.raymer_cargo_transport_weights.mass_nacelles aerosandbox.library.weights.raymer_cargo_transport_weights.mass_engine_controls aerosandbox.library.weights.raymer_cargo_transport_weights.mass_starter aerosandbox.library.weights.raymer_cargo_transport_weights.mass_fuel_system aerosandbox.library.weights.raymer_cargo_transport_weights.mass_flight_controls aerosandbox.library.weights.raymer_cargo_transport_weights.mass_APU aerosandbox.library.weights.raymer_cargo_transport_weights.mass_instruments aerosandbox.library.weights.raymer_cargo_transport_weights.mass_hydraulics aerosandbox.library.weights.raymer_cargo_transport_weights.mass_electrical aerosandbox.library.weights.raymer_cargo_transport_weights.mass_avionics aerosandbox.library.weights.raymer_cargo_transport_weights.mass_furnishings aerosandbox.library.weights.raymer_cargo_transport_weights.mass_air_conditioning aerosandbox.library.weights.raymer_cargo_transport_weights.mass_anti_ice aerosandbox.library.weights.raymer_cargo_transport_weights.mass_handling_gear aerosandbox.library.weights.raymer_cargo_transport_weights.mass_military_cargo_handling_system Module Contents --------------- .. py:function:: mass_wing(wing, design_mass_TOGW, ultimate_load_factor, use_advanced_composites = False) Computes the mass of the wing for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. Note: Torenbeek's wing mass model is likely more accurate; see `mass_wing()` in `torenbeek_weights.py` (same directory). :param wing: The wing object. :param design_mass_TOGW: The design take-off gross weight of the entire airplane [kg]. :param ultimate_load_factor: Ultimate load factor of the airplane. :param use_advanced_composites: Whether to use advanced composites for the wing. If True, the wing mass is modified :param accordingly.: :returns: Wing mass [kg]. .. py:function:: mass_hstab(hstab, design_mass_TOGW, ultimate_load_factor, wing_to_hstab_distance, fuselage_width_at_hstab_intersection, aircraft_y_radius_of_gyration = None, use_advanced_composites = False) Computes the mass of the horizontal stabilizer for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param hstab: The horizontal stabilizer object. :param design_mass_TOGW: The design take-off gross weight of the entire airplane [kg]. :param ultimate_load_factor: Ultimate load factor of the airplane. :param wing_to_hstab_distance: Distance from the wing's root-quarter-chord-point to the hstab's :param root-quarter-chord-point [m].: :param fuselage_width_at_hstab_intersection: Width of the fuselage at the intersection of the wing and hstab [m]. :param aircraft_y_radius_of_gyration: Radius of gyration of the aircraft about the y-axis [m]. If None, estimates :param this as `0.3 * wing_to_hstab_distance`.: :param use_advanced_composites: Whether to use advanced composites for the hstab. If True, the hstab mass is modified :param accordingly.: :returns: The mass of the horizontal stabilizer [kg]. .. py:function:: mass_vstab(vstab, design_mass_TOGW, ultimate_load_factor, wing_to_vstab_distance, is_t_tail = False, aircraft_z_radius_of_gyration = None, use_advanced_composites = False) Computes the mass of the vertical stabilizer for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param vstab: The vertical stabilizer object. :param design_mass_TOGW: The design take-off gross weight of the entire airplane [kg]. :param ultimate_load_factor: Ultimate load factor of the airplane. :param wing_to_vstab_distance: Distance from the wing's root-quarter-chord-point to the vstab's :param root-quarter-chord-point [m].: :param is_t_tail: Whether the airplane is a T-tail or not. :param aircraft_z_radius_of_gyration: The z-radius of gyration of the entire airplane [m]. If None, estimates this :param as `1 * wing_to_vstab_distance`.: :param use_advanced_composites: Whether to use advanced composites for the vstab. If True, the vstab mass is modified :param accordingly.: :returns: The mass of the vertical stabilizer [kg]. .. py:function:: mass_fuselage(fuselage, design_mass_TOGW, ultimate_load_factor, L_over_D, main_wing, n_cargo_doors = 1, has_aft_clamshell_door = False, landing_gear_mounted_on_fuselage = False, use_advanced_composites = False) Computes the mass of the fuselage for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param fuselage: The fuselage object. :param design_mass_TOGW: The design take-off gross weight of the entire airplane [kg]. :param ultimate_load_factor: Ultimate load factor of the airplane. :param L_over_D: The lift-to-drag ratio of the airplane in cruise. :param main_wing: The main wing object. Can be: * An instance of an AeroSandbox wing object (`asb.Wing`) * None, if the airplane has no main wing. :param n_cargo_doors: The number of cargo doors on the fuselage. :param has_aft_clamshell_door: Whether or not the fuselage has an aft clamshell door. :param landing_gear_mounted_on_fuselage: Whether or not the landing gear is mounted on the fuselage. :param use_advanced_composites: Whether to use advanced composites for the fuselage. If True, the fuselage mass is :param modified accordingly.: :returns: The mass of the fuselage [kg]. .. py:function:: mass_main_landing_gear(main_gear_length, landing_speed, design_mass_TOGW, is_kneeling = False, n_gear = 2, n_wheels = 12, n_shock_struts = 4, use_advanced_composites = False) Computes the mass of the main landing gear for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param main_gear_length: length of the main landing gear [m]. :param landing_speed: landing speed [m/s]. :param design_mass_TOGW: The design take-off gross weight of the entire airplane [kg]. :param is_kneeling: whether the main landing gear is capable of kneeling. :param n_gear: number of landing gear. :param n_wheels: number of wheels in total on the main landing gear. :param n_shock_struts: number of shock struts. :param use_advanced_composites: Whether to use advanced composites for the landing gear. If True, the landing gear mass :param is modified accordingly.: :returns: mass of the main landing gear [kg]. .. py:function:: mass_nose_landing_gear(nose_gear_length, design_mass_TOGW, is_kneeling = False, n_gear = 1, n_wheels = 2, use_advanced_composites = False) Computes the mass of the nose landing gear for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param nose_gear_length: Length of nose landing gear when fully-extended [m]. :param design_mass_TOGW: The design take-off gross weight of the entire airplane [kg]. :param is_kneeling: Whether the nose landing gear is capable of kneeling. :param n_gear: Number of nose landing gear. :param n_wheels: Number of wheels in total on the nose landing gear. :param use_advanced_composites: Whether to use advanced composites for the landing gear. If True, the landing gear mass :param is modified accordingly.: :returns: Mass of nose landing gear [kg]. .. py:function:: mass_nacelles(nacelle_length, nacelle_width, nacelle_height, ultimate_load_factor, mass_per_engine, n_engines, is_pylon_mounted = False, engines_have_propellers = False, engines_have_thrust_reversers = False, use_advanced_composites = False) Computes the mass of the nacelles for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. Excludes the engine itself and immediate engine peripherals. :param nacelle_length: length of the nacelle, front to back [m] :param nacelle_width: width of the nacelle [m] :param nacelle_height: height of the nacelle, top to bottom [m] :param ultimate_load_factor: ultimate load factor of the aircraft :param mass_per_engine: mass of the engine itself [kg] :param n_engines: number of engines :param is_pylon_mounted: whether the engine is pylon-mounted or not :param engines_have_propellers: whether the engines have propellers or not (e.g., a jet) :param engines_have_thrust_reversers: whether the engines have thrust reversers or not :param use_advanced_composites: Whether to use advanced composites for the nacelles. If True, the nacelles mass :param is modified accordingly.: :returns: mass of the nacelles [kg] .. py:function:: mass_engine_controls(n_engines, cockpit_to_engine_length) Computes the mass of the engine controls for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param n_engines: The number of engines in the aircraft. :param cockpit_to_engine_length: The distance from the cockpit to the engine [m]. :returns: The mass of the engine controls [kg]. .. py:function:: mass_starter(n_engines, mass_per_engine) Computes the mass of the engine starter for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param n_engines: The number of engines in the aircraft. :param mass_per_engine: The mass of the engine [kg]. :returns: The mass of the engine starter [kg]. .. py:function:: mass_fuel_system(fuel_volume, n_tanks, fraction_in_integral_tanks = 0.5) Computes the mass of the fuel system (e.g., tanks, pumps, but not the fuel itself) for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param fuel_volume: The volume of fuel in the aircraft [m^3]. :param n_tanks: The number of fuel tanks in the aircraft. :param fraction_in_integral_tanks: The fraction of the fuel volume that is in integral tanks, as opposed to :param protected tanks.: :returns: The mass of the fuel system [kg]. .. py:function:: mass_flight_controls(airplane, aircraft_Iyy, fraction_of_mechanical_controls = 0) Computes the added mass of the flight control surfaces (and any applicable linkages, in the case of mechanical controls) for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param airplane: The airplane to calculate the mass of the flight controls for. :param aircraft_Iyy: The moment of inertia of the aircraft about the y-axis. :param fraction_of_mechanical_controls: The fraction of the flight controls that are mechanical, as opposed to :param hydraulic.: :returns: The mass of the flight controls [kg]. .. py:function:: mass_APU(mass_APU_uninstalled) Computes the mass of the auxiliary power unit (APU) for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param mass_APU_uninstalled: The mass of the APU uninstalled [kg]. :returns: The mass of the APU, as installed [kg]. .. py:function:: mass_instruments(fuselage, main_wing, n_engines, n_crew, engine_is_reciprocating = False, engine_is_turboprop = False) Computes the mass of the flight instruments for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param fuselage: The fuselage of the airplane. :param main_wing: The main wing of the airplane. :param n_engines: The number of engines on the airplane. :param n_crew: The number of crew members on the airplane. Use 0.5 for a UAV. :param engine_is_reciprocating: Whether the engine is reciprocating. :param engine_is_turboprop: Whether the engine is a turboprop. :returns: The mass of the instruments [kg] .. py:function:: mass_hydraulics(airplane, fuselage, main_wing) Computes the mass of the hydraulic system for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param airplane: The airplane to calculate the mass of the hydraulic system for. :param fuselage: The fuselage of the airplane. :param main_wing: The main wing of the airplane. :returns: The mass of the hydraulic system [kg]. .. py:function:: mass_electrical(system_electrical_power_rating, electrical_routing_distance, n_engines) Computes the mass of the electrical system for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param system_electrical_power_rating: The total electrical power rating of the aircraft's electrical system [Watts]. Typical values: * Transport airplane: 40,000 - 60,000 W * Fighter/bomber airplane: 110,000 - 160,000 W :param electrical_routing_distance: The electrical routing distance, generators to avionics to cockpit. [meters] :returns: The mass of the electrical system [kg]. .. py:function:: mass_avionics(mass_uninstalled_avionics) Computes the mass of the avionics for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param mass_uninstalled_avionics: The mass of the avionics, before installation [kg]. :returns: The mass of the avionics, as installed [kg]. .. py:function:: mass_furnishings(n_crew, mass_cargo, fuselage) Computes the mass of the furnishings for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. Does not include cargo handling gear or seats. :param n_crew: The number of crew members on the airplane. Use 0.5 for a UAV. :param mass_cargo: The mass of the cargo [kg]. :param fuselage: The fuselage of the airplane. :returns: The mass of the furnishings [kg]. .. py:function:: mass_air_conditioning(n_crew, n_pax, volume_pressurized, mass_uninstalled_avionics) Computes the mass of the air conditioning system for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param n_crew: The number of crew members on the airplane. :param n_pax: The number of passengers on the airplane. :param volume_pressurized: The volume of the pressurized cabin [meters^3]. :param mass_uninstalled_avionics: The mass of the avionics, before installation [kg]. :returns: The mass of the air conditioning system [kg]. .. py:function:: mass_anti_ice(design_mass_TOGW) Computes the mass of the anti-ice system for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param design_mass_TOGW: The design takeoff gross weight of the entire airplane [kg]. :returns: The mass of the anti-ice system [kg]. .. py:function:: mass_handling_gear(design_mass_TOGW) Computes the mass of the handling gear for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param design_mass_TOGW: The design takeoff gross weight of the entire airplane [kg]. :returns: The mass of the handling gear [kg]. .. py:function:: mass_military_cargo_handling_system(cargo_floor_area) Computes the mass of the military cargo handling system for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param cargo_floor_area: The floor area of the cargo compartment [meters^2]. :returns: The mass of the military cargo handling system [kg].