aerosandbox.library.weights.raymer_general_aviation_weights
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Module Contents#
Functions#
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Computes the mass of a wing of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual |
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Computes the mass of a horizontal stabilizer of a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of a vertical stabilizer of a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of a fuselage of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual |
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Computes the mass of the main landing gear of a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of the nose landing gear of a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of the engines installed on a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of the fuel system (e.g., tanks, pumps, but not the fuel itself) for a general aviation |
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Computes the mass of the flight controls for a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of the hydraulics for a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of the avionics for a general aviation aircraft, according to Raymer's Aircraft Design: A |
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Computes the mass of the electrical system for a general aviation aircraft, according to Raymer's Aircraft Design: |
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Computes the mass of the air conditioning and anti-ice system for a general aviation aircraft, according to |
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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].