aerosandbox.library.weights.raymer_general_aviation_weights#

Module Contents#

Functions#

mass_wing(wing, design_mass_TOGW, ...[, ...])

Computes the mass of a wing of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual

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

Computes the mass of a horizontal stabilizer of a general aviation aircraft, according to Raymer's Aircraft Design:

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

Computes the mass of a vertical stabilizer of a general aviation aircraft, according to Raymer's Aircraft Design:

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

Computes the mass of a fuselage of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual

mass_main_landing_gear(main_gear_length, design_mass_TOGW)

Computes the mass of the main landing gear of a general aviation 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 of a general aviation aircraft, according to Raymer's Aircraft Design:

mass_engines_installed(n_engines, mass_per_engine)

Computes the mass of the engines installed on a general aviation aircraft, according to Raymer's Aircraft Design:

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

Computes the mass of the fuel system (e.g., tanks, pumps, but not the fuel itself) for a general aviation

mass_flight_controls(airplane, design_mass_TOGW, ...)

Computes the mass of the flight controls for a general aviation aircraft, according to Raymer's Aircraft Design:

mass_hydraulics(fuselage_width, cruise_op_point)

Computes the mass of the hydraulics for a general aviation aircraft, according to Raymer's Aircraft Design:

mass_avionics(mass_uninstalled_avionics)

Computes the mass of the avionics for a general aviation aircraft, according to Raymer's Aircraft Design: A

mass_electrical(fuel_system_mass, avionics_mass)

Computes the mass of the electrical system for a general aviation aircraft, according to Raymer's Aircraft Design:

mass_air_conditioning_and_anti_ice(design_mass_TOGW, ...)

Computes the mass of the air conditioning and anti-ice system for a general aviation aircraft, according to

mass_furnishings(design_mass_TOGW)

Computes the mass of the furnishings for a general aviation aircraft, according to Raymer's Aircraft Design: A
aerosandbox.library.weights.raymer_general_aviation_weights.mass_wing(wing, design_mass_TOGW, ultimate_load_factor, mass_fuel_in_wing, cruise_op_point, use_advanced_composites=False)[source]#

Computes the mass of a wing of a general aviation 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 takeoff gross weight of the entire aircraft [kg].

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

  • mass_fuel_in_wing (float) –

    The mass of fuel in the wing [kg]. If there is no fuel in the wing, set this to 0.

    Note: Model extrapolates strangely for infinitesimally-small-but-nonzero fuel masses; don’t let an optimizer land here.

  • cruise_op_point (aerosandbox.OperatingPoint) – The cruise operating point of the aircraft.

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

  • accordingly. –

Return type:

float

Returns: The mass of the wing [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_hstab(hstab, design_mass_TOGW, ultimate_load_factor, cruise_op_point, use_advanced_composites=False)[source]#

Computes the mass of a horizontal stabilizer of a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

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

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

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

  • cruise_op_point (aerosandbox.OperatingPoint) – The cruise operating point of the aircraft.

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

  • accordingly. (hstab mass is modified) –

Return type:

float

Returns: The mass of the horizontal stabilizer [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_vstab(vstab, design_mass_TOGW, ultimate_load_factor, cruise_op_point, is_t_tail=False, use_advanced_composites=False)[source]#

Computes the mass of a vertical stabilizer of a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

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

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

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

  • cruise_op_point (aerosandbox.OperatingPoint) – The cruise operating point of the aircraft.

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

  • use_advanced_composites (bool) – Whether to use advanced composites for the vertical stabilizer. If True, the vstab

  • accordingly. (mass is modified) –

Return type:

float

Returns: The mass of the vertical stabilizer [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_fuselage(fuselage, design_mass_TOGW, ultimate_load_factor, L_over_D, cruise_op_point, wing_to_tail_distance, pressure_differential=0.0, use_advanced_composites=False)[source]#

Computes the mass of a fuselage of a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

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

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

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

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

  • cruise_op_point (aerosandbox.OperatingPoint) – The cruise operating point of the aircraft.

  • wing_to_tail_distance (float) – The distance between the wing root-quarter-chord-point and the tail

  • [m]. (root-quarter-chord-point of the aircraft) –

  • pressure_differential (float) – The absolute value of the pressure differential across the fuselage [Pa].

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

  • accordingly. (modified) –

Return type:

float

Returns: The mass of the fuselage [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_main_landing_gear(main_gear_length, design_mass_TOGW, n_gear=2, is_retractable=True, use_advanced_composites=False)[source]#

Computes the mass of the main landing gear of a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

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

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

  • n_gear (int) – The number of main landing gear.

  • is_retractable (bool) – Whether the main landing gear is retractable or not.

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

  • accordingly. (landing gear mass is modified) –

Return type:

float

Returns: The mass of the main landing gear [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_nose_landing_gear(nose_gear_length, design_mass_TOGW, n_gear=1, is_retractable=True, use_advanced_composites=False)[source]#

Computes the mass of the nose landing gear of a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • nose_gear_length (float) – The length of the nose landing gear [m].

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

  • n_gear (int) – The number of nose landing gear.

  • is_retractable (bool) – Whether the nose landing gear is retractable or not.

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

  • accordingly. (landing gear mass is modified) –

Return type:

float

Returns: The mass of the nose landing gear [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_engines_installed(n_engines, mass_per_engine)[source]#

Computes the mass of the engines installed on a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach. Includes propellers and engine mounts.

Parameters:

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

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

Return type:

float

Returns: The mass of the engines installed on the aircraft [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_fuel_system(fuel_volume, n_tanks, n_engines, 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 general aviation 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.

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

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

  • tanks. (protected) –

Return type:

float

Returns: The mass of the fuel system [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_flight_controls(airplane, design_mass_TOGW, ultimate_load_factor, fuselage=None, main_wing=None)[source]#

Computes the mass of the flight controls for a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • airplane (aerosandbox.Airplane) – The airplane for which to compute the flight controls mass.

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

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

  • fuselage (aerosandbox.Fuselage) – The fuselage to use for computing the flight controls mass. If fuselage is None, or if there are no

  • object (no wings in the airplane) –

  • fuselage. (the flight controls mass will be computed without a) –

  • main_wing (aerosandbox.Wing) – The main wing to use for computing the flight controls mass. If main_wing is None, or if there are

  • object –

  • wing. (the flight controls mass will be computed without a main) –

Return type:

float

Returns: The mass of the flight controls [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_hydraulics(fuselage_width, cruise_op_point)[source]#

Computes the mass of the hydraulics for a general aviation aircraft, according to Raymer’s Aircraft Design: A Conceptual Approach.

Parameters:

  • fuselage_width (float) – The width of the fuselage [m].

  • cruise_op_point (aerosandbox.OperatingPoint) – The cruise operating point of the aircraft.

Return type:

float

Returns: The mass of the hydraulics [kg].

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

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

Parameters:

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

Return type:

float

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

aerosandbox.library.weights.raymer_general_aviation_weights.mass_electrical(fuel_system_mass, avionics_mass)[source]#

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

Parameters:

  • fuel_system_mass (float) – The mass of the fuel system [kg].

  • avionics_mass (float) – The mass of the avionics [kg].

Return type:

float

Returns: The mass of the electrical system [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_air_conditioning_and_anti_ice(design_mass_TOGW, n_crew, n_pax, mass_avionics, cruise_op_point)[source]#

Computes the mass of the air conditioning and anti-ice system for a general aviation 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].

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

  • n_pax (int) – The number of passengers.

  • mass_avionics (float) – The mass of the avionics [kg].

  • cruise_op_point (aerosandbox.OperatingPoint) – The cruise operating point of the aircraft.

Returns: The mass of the air conditioning and anti-ice system [kg].

aerosandbox.library.weights.raymer_general_aviation_weights.mass_furnishings(design_mass_TOGW)[source]#

Computes the mass of the furnishings for a general aviation 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 furnishings [kg].