aerosandbox.library.weights.raymer_general_aviation_weights =========================================================== .. py:module:: aerosandbox.library.weights.raymer_general_aviation_weights Functions --------- .. autoapisummary:: aerosandbox.library.weights.raymer_general_aviation_weights.mass_wing aerosandbox.library.weights.raymer_general_aviation_weights.mass_hstab aerosandbox.library.weights.raymer_general_aviation_weights.mass_vstab aerosandbox.library.weights.raymer_general_aviation_weights.mass_fuselage aerosandbox.library.weights.raymer_general_aviation_weights.mass_main_landing_gear aerosandbox.library.weights.raymer_general_aviation_weights.mass_nose_landing_gear aerosandbox.library.weights.raymer_general_aviation_weights.mass_engines_installed aerosandbox.library.weights.raymer_general_aviation_weights.mass_fuel_system aerosandbox.library.weights.raymer_general_aviation_weights.mass_flight_controls aerosandbox.library.weights.raymer_general_aviation_weights.mass_hydraulics aerosandbox.library.weights.raymer_general_aviation_weights.mass_avionics aerosandbox.library.weights.raymer_general_aviation_weights.mass_electrical aerosandbox.library.weights.raymer_general_aviation_weights.mass_air_conditioning_and_anti_ice aerosandbox.library.weights.raymer_general_aviation_weights.mass_furnishings Module Contents --------------- .. py:function:: mass_wing(wing, design_mass_TOGW, ultimate_load_factor, mass_fuel_in_wing, cruise_op_point, use_advanced_composites = False) 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). :param wing: The wing object. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param ultimate_load_factor: The ultimate load factor of the aircraft. :param mass_fuel_in_wing: 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. :param cruise_op_point: The cruise operating point of the aircraft. :param use_advanced_composites: Whether to use advanced composites for the wing. If True, the wing mass is modified :param accordingly.: Returns: The mass of the wing [kg]. .. py:function:: mass_hstab(hstab, design_mass_TOGW, ultimate_load_factor, cruise_op_point, use_advanced_composites = False) Computes the mass of a horizontal stabilizer of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param hstab: The horizontal stabilizer object. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param ultimate_load_factor: The ultimate load factor of the aircraft. :param cruise_op_point: The cruise operating point of the aircraft. :param use_advanced_composites: Whether to use advanced composites for the horizontal stabilizer. If True, the :param hstab mass is modified accordingly.: Returns: The mass of the horizontal stabilizer [kg]. .. py:function:: mass_vstab(vstab, design_mass_TOGW, ultimate_load_factor, cruise_op_point, is_t_tail = False, use_advanced_composites = False) Computes the mass of a vertical stabilizer of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param vstab: The vertical stabilizer object. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param ultimate_load_factor: The ultimate load factor of the aircraft. :param cruise_op_point: The cruise operating point of the aircraft. :param is_t_tail: Whether the aircraft is a T-tail or not. :param use_advanced_composites: Whether to use advanced composites for the vertical stabilizer. If True, the vstab :param mass is modified accordingly.: Returns: The mass of the vertical stabilizer [kg]. .. py:function:: 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) Computes the mass of a fuselage of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param fuselage: The fuselage object. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param ultimate_load_factor: The ultimate load factor of the aircraft. :param L_over_D: The lift-to-drag ratio of the aircraft in cruise. :param cruise_op_point: The cruise operating point of the aircraft. :param wing_to_tail_distance: The distance between the wing root-quarter-chord-point and the tail :param root-quarter-chord-point of the aircraft [m].: :param pressure_differential: The absolute value of the pressure differential across the fuselage [Pa]. :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, design_mass_TOGW, n_gear = 2, is_retractable = True, use_advanced_composites = False) Computes the mass of the main landing gear of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param main_gear_length: The length of the main landing gear [m]. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param n_gear: The number of main landing gear. :param is_retractable: Whether the main landing gear is retractable or not. :param use_advanced_composites: Whether to use advanced composites for the main landing gear. If True, the main :param landing gear mass is modified accordingly.: Returns: The mass of the main landing gear [kg]. .. py:function:: mass_nose_landing_gear(nose_gear_length, design_mass_TOGW, n_gear = 1, is_retractable = True, use_advanced_composites = False) Computes the mass of the nose landing gear of a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param nose_gear_length: The length of the nose landing gear [m]. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param n_gear: The number of nose landing gear. :param is_retractable: Whether the nose landing gear is retractable or not. :param use_advanced_composites: Whether to use advanced composites for the nose landing gear. If True, the nose :param landing gear mass is modified accordingly.: Returns: The mass of the nose landing gear [kg]. .. py:function:: 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: A Conceptual Approach. Includes propellers and engine mounts. :param n_engines: The number of engines installed on the aircraft. :param mass_per_engine: The mass of a single engine [kg]. Returns: The mass of the engines installed on the aircraft [kg]. .. py:function:: mass_fuel_system(fuel_volume, n_tanks, n_engines, fraction_in_integral_tanks = 0.5) 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. :param fuel_volume: The volume of fuel in the aircraft [m^3]. :param n_tanks: The number of fuel tanks in the aircraft. :param n_engines: The number of engines 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, design_mass_TOGW, ultimate_load_factor, fuselage = None, main_wing = None) Computes the mass of the flight controls for a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param airplane: The airplane for which to compute the flight controls mass. :param design_mass_TOGW: The design takeoff gross weight of the entire aircraft [kg]. :param ultimate_load_factor: The ultimate load factor of the aircraft. :param fuselage: The fuselage to use for computing the flight controls mass. If fuselage is None, or if there are no :param fuselages in the airplane object: :param the flight controls mass will be computed without a fuselage.: :param main_wing: The main wing to use for computing the flight controls mass. If main_wing is None, or if there are :param no wings in the airplane object: :param the flight controls mass will be computed without a main wing.: Returns: The mass of the flight controls [kg]. .. py:function:: mass_hydraulics(fuselage_width, cruise_op_point) Computes the mass of the hydraulics for a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param fuselage_width: The width of the fuselage [m]. :param cruise_op_point: The cruise operating point of the aircraft. Returns: The mass of the hydraulics [kg]. .. py:function:: mass_avionics(mass_uninstalled_avionics) Computes the mass of the avionics for a general aviation 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_electrical(fuel_system_mass, avionics_mass) Computes the mass of the electrical system for a general aviation aircraft, according to Raymer's Aircraft Design: A Conceptual Approach. :param fuel_system_mass: The mass of the fuel system [kg]. :param avionics_mass: The mass of the avionics [kg]. Returns: The mass of the electrical system [kg]. .. py:function:: mass_air_conditioning_and_anti_ice(design_mass_TOGW, n_crew, n_pax, mass_avionics, cruise_op_point) 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. :param design_mass_TOGW: The design takeoff gross weight of the entire airplane [kg]. :param n_crew: The number of crew members. :param n_pax: The number of passengers. :param mass_avionics: The mass of the avionics [kg]. :param cruise_op_point: The cruise operating point of the aircraft. Returns: The mass of the air conditioning and anti-ice system [kg]. .. py:function:: mass_furnishings(design_mass_TOGW) Computes the mass of the furnishings for a general aviation 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 furnishings [kg].