aerosandbox.library.weights.raymer_cargo_transport_weights#

Module Contents#

Functions#

mass_wing(wing, design_mass_TOGW, ultimate_load_factor)

Computes the mass of the wing for a cargo/transport aircraft, according to Raymer's Aircraft Design: A Conceptual

mass_hstab(hstab, design_mass_TOGW, ...[, ...])

Computes the mass of the horizontal stabilizer for a cargo/transport aircraft, according to Raymer's Aircraft

mass_vstab(vstab, design_mass_TOGW, ...[, is_t_tail, ...])

Computes the mass of the vertical stabilizer for a cargo/transport aircraft, according to Raymer's Aircraft

mass_fuselage(fuselage, design_mass_TOGW, ...[, ...])

Computes the mass of the fuselage for a cargo/transport aircraft, according to Raymer's Aircraft Design: A

mass_main_landing_gear(main_gear_length, ...[, ...])

Computes the mass of the main landing gear for a cargo/transport aircraft, according to Raymer's Aircraft Design:

mass_nose_landing_gear(nose_gear_length, design_mass_TOGW)

Computes the mass of the nose landing gear for a cargo/transport aircraft, according to Raymer's Aircraft

mass_nacelles(nacelle_length, nacelle_width, ...[, ...])

Computes the mass of the nacelles for a cargo/transport aircraft, according to Raymer's Aircraft

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

mass_starter(n_engines, mass_per_engine)

Computes the mass of the engine starter for a cargo/transport aircraft, according to Raymer's Aircraft

mass_fuel_system(fuel_volume, n_tanks[, ...])

Computes the mass of the fuel system (e.g., tanks, pumps, but not the fuel itself) for a cargo/transport

mass_flight_controls(airplane, aircraft_Iyy[, ...])

Computes the added mass of the flight control surfaces (and any applicable linkages, in the case of mechanical

mass_APU(mass_APU_uninstalled)

Computes the mass of the auxiliary power unit (APU) for a cargo/transport aircraft, according to Raymer's Aircraft

mass_instruments(fuselage, main_wing, n_engines, n_crew)

Computes the mass of the flight instruments for a cargo/transport aircraft, according to Raymer's Aircraft

mass_hydraulics(airplane, fuselage, main_wing)

Computes the mass of the hydraulic system for a cargo/transport aircraft, according to Raymer's Aircraft

mass_electrical(system_electrical_power_rating, ...)

Computes the mass of the electrical system for a cargo/transport aircraft, according to Raymer's Aircraft

mass_avionics(mass_uninstalled_avionics)

Computes the mass of the avionics for a cargo/transport aircraft, according to Raymer's Aircraft

mass_furnishings(n_crew, mass_cargo, fuselage)

Computes the mass of the furnishings for a cargo/transport aircraft, according to Raymer's Aircraft

mass_air_conditioning(n_crew, n_pax, ...)

Computes the mass of the air conditioning system for a cargo/transport aircraft, according to Raymer's Aircraft

mass_anti_ice(design_mass_TOGW)

Computes the mass of the anti-ice system for a cargo/transport aircraft, according to Raymer's Aircraft

mass_handling_gear(design_mass_TOGW)

Computes the mass of the handling gear for a cargo/transport aircraft, according to Raymer's Aircraft

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
aerosandbox.library.weights.raymer_cargo_transport_weights.mass_wing(wing, design_mass_TOGW, ultimate_load_factor, use_advanced_composites=False)[source]#

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).

Parameters:

  • wing (aerosandbox.Wing) – The wing object.

  • design_mass_TOGW (float) – The design take-off gross weight of the entire airplane [kg].

  • ultimate_load_factor (float) – Ultimate load factor of the airplane.

  • use_advanced_composites (bool) – Whether to use advanced composites for the wing. If True, the wing mass is modified

  • accordingly. –

Returns:

Wing mass [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.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)[source]#

Computes the mass of the horizontal stabilizer for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • hstab (aerosandbox.Wing) – The horizontal stabilizer object.

  • design_mass_TOGW (float) – The design take-off gross weight of the entire airplane [kg].

  • ultimate_load_factor (float) – Ultimate load factor of the airplane.

  • wing_to_hstab_distance (float) – Distance from the wing’s root-quarter-chord-point to the hstab’s

  • [m]. (root-quarter-chord-point) –

  • fuselage_width_at_hstab_intersection (float) – Width of the fuselage at the intersection of the wing and hstab [m].

  • aircraft_y_radius_of_gyration (float) – Radius of gyration of the aircraft about the y-axis [m]. If None, estimates

  • wing_to_hstab_distance. (this as 0.3 *) –

  • use_advanced_composites (bool) – Whether to use advanced composites for the hstab. If True, the hstab mass is modified

  • accordingly. –

Returns:

The mass of the horizontal stabilizer [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.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)[source]#

Computes the mass of the vertical stabilizer for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • vstab (aerosandbox.Wing) – The vertical stabilizer object.

  • design_mass_TOGW (float) – The design take-off gross weight of the entire airplane [kg].

  • ultimate_load_factor (float) – Ultimate load factor of the airplane.

  • wing_to_vstab_distance (float) – Distance from the wing’s root-quarter-chord-point to the vstab’s

  • [m]. (root-quarter-chord-point) –

  • is_t_tail (bool) – Whether the airplane is a T-tail or not.

  • aircraft_z_radius_of_gyration (float) – The z-radius of gyration of the entire airplane [m]. If None, estimates this

  • wing_to_vstab_distance. (as 1 *) –

  • use_advanced_composites (bool) – Whether to use advanced composites for the vstab. If True, the vstab mass is modified

  • accordingly. –

Returns:

The mass of the vertical stabilizer [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.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)[source]#

Computes the mass of the fuselage for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • fuselage (aerosandbox.Fuselage) – The fuselage object.

  • design_mass_TOGW (float) – The design take-off gross weight of the entire airplane [kg].

  • ultimate_load_factor (float) – Ultimate load factor of the airplane.

  • L_over_D (float) – The lift-to-drag ratio of the airplane in cruise.

  • main_wing (aerosandbox.Wing) –

    The main wing object. Can be:

    • An instance of an AeroSandbox wing object (asb.Wing)

    • None, if the airplane has no main wing.

  • n_cargo_doors (int) – The number of cargo doors on the fuselage.

  • has_aft_clamshell_door (bool) – Whether or not the fuselage has an aft clamshell door.

  • landing_gear_mounted_on_fuselage (bool) – Whether or not the landing gear is mounted on the fuselage.

  • use_advanced_composites (bool) – Whether to use advanced composites for the fuselage. If True, the fuselage mass is

  • accordingly. (modified) –

Returns:

The mass of the fuselage [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.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)[source]#

Computes the mass of the main landing gear for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • main_gear_length (float) – length of the main landing gear [m].

  • landing_speed (float) – landing speed [m/s].

  • design_mass_TOGW (float) – The design take-off gross weight of the entire airplane [kg].

  • is_kneeling (bool) – whether the main landing gear is capable of kneeling.

  • n_gear (int) – number of landing gear.

  • n_wheels (int) – number of wheels in total on the main landing gear.

  • n_shock_struts (int) – number of shock struts.

  • use_advanced_composites (bool) – Whether to use advanced composites for the landing gear. If True, the landing gear mass

  • accordingly. (is modified) –

Returns:

mass of the main landing gear [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_nose_landing_gear(nose_gear_length, design_mass_TOGW, is_kneeling=False, n_gear=1, n_wheels=2, use_advanced_composites=False)[source]#

Computes the mass of the nose landing gear for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • nose_gear_length (float) – Length of nose landing gear when fully-extended [m].

  • design_mass_TOGW (float) – The design take-off gross weight of the entire airplane [kg].

  • is_kneeling (bool) – Whether the nose landing gear is capable of kneeling.

  • n_gear (int) – Number of nose landing gear.

  • n_wheels (int) – Number of wheels in total on the nose landing gear.

  • use_advanced_composites (bool) – Whether to use advanced composites for the landing gear. If True, the landing gear mass

  • accordingly. (is modified) –

Returns:

Mass of nose landing gear [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.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)[source]#

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.

Parameters:

  • nacelle_length (float) – length of the nacelle, front to back [m]

  • nacelle_width (float) – width of the nacelle [m]

  • nacelle_height (float) – height of the nacelle, top to bottom [m]

  • ultimate_load_factor (float) – ultimate load factor of the aircraft

  • mass_per_engine (float) – mass of the engine itself [kg]

  • n_engines (int) – number of engines

  • is_pylon_mounted (bool) – whether the engine is pylon-mounted or not

  • engines_have_propellers (bool) – whether the engines have propellers or not (e.g., a jet)

  • engines_have_thrust_reversers (bool) – whether the engines have thrust reversers or not

  • use_advanced_composites (bool) – Whether to use advanced composites for the nacelles. If True, the nacelles mass

  • accordingly. (is modified) –

Returns:

mass of the nacelles [kg]

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_engine_controls(n_engines, cockpit_to_engine_length)[source]#

Computes the mass of the engine controls for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • n_engines (int) – The number of engines in the aircraft.

  • cockpit_to_engine_length (float) – The distance from the cockpit to the engine [m].

Returns:

The mass of the engine controls [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_starter(n_engines, mass_per_engine)[source]#

Computes the mass of the engine starter for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • n_engines (int) – The number of engines in the aircraft.

  • mass_per_engine (float) – The mass of the engine [kg].

Returns:

The mass of the engine starter [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_fuel_system(fuel_volume, n_tanks, fraction_in_integral_tanks=0.5)[source]#

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.

Parameters:

  • fuel_volume (float) – The volume of fuel in the aircraft [m^3].

  • n_tanks (int) – The number of fuel tanks in the aircraft.

  • fraction_in_integral_tanks (float) – The fraction of the fuel volume that is in integral tanks, as opposed to

  • tanks. (protected) –

Returns:

The mass of the fuel system [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_flight_controls(airplane, aircraft_Iyy, fraction_of_mechanical_controls=0)[source]#

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.

Parameters:

  • airplane (aerosandbox.Airplane) – The airplane to calculate the mass of the flight controls for.

  • aircraft_Iyy (float) – The moment of inertia of the aircraft about the y-axis.

  • fraction_of_mechanical_controls (int) – The fraction of the flight controls that are mechanical, as opposed to

  • hydraulic. –

Returns:

The mass of the flight controls [kg].

Return type:

float

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_APU(mass_APU_uninstalled)[source]#

Computes the mass of the auxiliary power unit (APU) for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

mass_APU_uninstalled (float) – The mass of the APU uninstalled [kg].

Returns:

The mass of the APU, as installed [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_instruments(fuselage, main_wing, n_engines, n_crew, engine_is_reciprocating=False, engine_is_turboprop=False)[source]#

Computes the mass of the flight instruments for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • fuselage (aerosandbox.Fuselage) – The fuselage of the airplane.

  • main_wing (aerosandbox.Wing) – The main wing of the airplane.

  • n_engines (int) – The number of engines on the airplane.

  • n_crew (Union[int, float]) – The number of crew members on the airplane. Use 0.5 for a UAV.

  • engine_is_reciprocating (bool) – Whether the engine is reciprocating.

  • engine_is_turboprop (bool) – Whether the engine is a turboprop.

Returns:

The mass of the instruments [kg]

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_hydraulics(airplane, fuselage, main_wing)[source]#

Computes the mass of the hydraulic system for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:
Returns:

The mass of the hydraulic system [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_electrical(system_electrical_power_rating, electrical_routing_distance, n_engines)[source]#

Computes the mass of the electrical system for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • system_electrical_power_rating (float) –

    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

  • electrical_routing_distance (float) – The electrical routing distance, generators to avionics to cockpit. [meters]

  • n_engines (int) –

Returns:

The mass of the electrical system [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_avionics(mass_uninstalled_avionics)[source]#

Computes the mass of the avionics for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

mass_uninstalled_avionics (float) – The mass of the avionics, before installation [kg].

Returns:

The mass of the avionics, as installed [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_furnishings(n_crew, mass_cargo, fuselage)[source]#

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.

Parameters:

  • n_crew (Union[int, float]) – The number of crew members on the airplane. Use 0.5 for a UAV.

  • mass_cargo (float) – The mass of the cargo [kg].

  • fuselage (aerosandbox.Fuselage) – The fuselage of the airplane.

Returns:

The mass of the furnishings [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_air_conditioning(n_crew, n_pax, volume_pressurized, mass_uninstalled_avionics)[source]#

Computes the mass of the air conditioning system for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • n_crew (int) – The number of crew members on the airplane.

  • n_pax (int) – The number of passengers on the airplane.

  • volume_pressurized (float) – The volume of the pressurized cabin [meters^3].

  • mass_uninstalled_avionics (float) – The mass of the avionics, before installation [kg].

Returns:

The mass of the air conditioning system [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_anti_ice(design_mass_TOGW)[source]#

Computes the mass of the anti-ice system for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

design_mass_TOGW (float) – The design takeoff gross weight of the entire airplane [kg].

Returns:

The mass of the anti-ice system [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_handling_gear(design_mass_TOGW)[source]#

Computes the mass of the handling gear for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

design_mass_TOGW (float) – The design takeoff gross weight of the entire airplane [kg].

Returns:

The mass of the handling gear [kg].

aerosandbox.library.weights.raymer_cargo_transport_weights.mass_military_cargo_handling_system(cargo_floor_area)[source]#

Computes the mass of the military cargo handling system for a cargo/transport aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

cargo_floor_area (float) – The floor area of the cargo compartment [meters^2].

Returns:

The mass of the military cargo handling system [kg].