aerosandbox.library.weights.torenbeek_weights ============================================= .. py:module:: aerosandbox.library.weights.torenbeek_weights Functions --------- .. autoapisummary:: aerosandbox.library.weights.torenbeek_weights.mass_wing_simple aerosandbox.library.weights.torenbeek_weights.mass_wing_high_lift_devices aerosandbox.library.weights.torenbeek_weights.mass_wing_basic_structure aerosandbox.library.weights.torenbeek_weights.mass_wing_spoilers_and_speedbrakes aerosandbox.library.weights.torenbeek_weights.mass_wing aerosandbox.library.weights.torenbeek_weights.mass_fuselage_simple aerosandbox.library.weights.torenbeek_weights.mass_fuselage aerosandbox.library.weights.torenbeek_weights.mass_propeller Module Contents --------------- .. py:function:: mass_wing_simple(wing, design_mass_TOGW, ultimate_load_factor, suspended_mass, main_gear_mounted_to_wing = True) Computes the mass of a wing of an aircraft, according to Torenbeek's "Synthesis of Subsonic Airplane Design". This is the simple version of the wing weight model, which is found in: Section 8.4: Weight Prediction Data and Methods 8.4.1: Airframe Structure Eq. 8-12 A more detailed version of the wing weight model is available in the `mass_wing()` function in this same module. :param wing: The wing object. Should be an AeroSandbox 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. 1.5x the limit load factor. :param suspended_mass: The mass of the aircraft that is suspended from the wing [kg]. :param main_gear_mounted_to_wing: Whether the main gear is mounted to the wing structure. Returns: The total mass of the wing [kg]. .. py:function:: mass_wing_high_lift_devices(wing, max_airspeed_for_flaps, flap_deflection_angle = 30, k_f1 = 1.0, k_f2 = 1.0) The function mass_high_lift() is designed to estimate the weight of the high-lift devices on an airplane wing. It uses Torenbeek's method, which is based on multiple factors like wing design and flap deflection. :param wing: :param an instance of AeroSandbox's Wing class: :param : :param max_airspeed_for_flaps: :param the maximum airspeed at which the flaps can be deployed [m/s]: :param flap_deflection_angle: :param the angle to which the flaps can be deflected [deg]. Default value is 30 degrees.: :param k_f1: = 1.0 for single-slotted; double-slotted, fixed hinge = 1.15 for double: slotted, 4-bar movement; single-slotted Fowler = 1.3 for double-slotted Fowler = 1.45 for triple-slotted Fowler :param configuration factor 1: = 1.0 for single-slotted; double-slotted, fixed hinge = 1.15 for double: slotted, 4-bar movement; single-slotted Fowler = 1.3 for double-slotted Fowler = 1.45 for triple-slotted Fowler :param with values: = 1.0 for single-slotted; double-slotted, fixed hinge = 1.15 for double: slotted, 4-bar movement; single-slotted Fowler = 1.3 for double-slotted Fowler = 1.45 for triple-slotted Fowler :param k_f2: = 1.0 for slotted flaps with fixed vanes = 1.25 for double-slotted flaps with "variable geometry", i.e., extending flaps with separately moving vanes or auxiliary flaps :param configuration factor 2: = 1.0 for slotted flaps with fixed vanes = 1.25 for double-slotted flaps with "variable geometry", i.e., extending flaps with separately moving vanes or auxiliary flaps :param with values: = 1.0 for slotted flaps with fixed vanes = 1.25 for double-slotted flaps with "variable geometry", i.e., extending flaps with separately moving vanes or auxiliary flaps Returns: Mass of the wing's high-lift system only [kg] .. py:function:: mass_wing_basic_structure(wing, design_mass_TOGW, ultimate_load_factor, suspended_mass, never_exceed_airspeed, main_gear_mounted_to_wing = True, strut_y_location = None, k_e = 0.95, return_dict = False) Computes the mass of the basic structure of the wing of an aircraft, according to Torenbeek's "Synthesis of Subsonic Airplane Design", 1976, Appendix C: "Prediction of Wing Structural Weight". This is the basic wing structure without movables like spoilers, high-lift devices, etc. Likely more accurate than the Raymer wing weight models. :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 [-]. 1.5x the limit load factor. :param suspended_mass: The mass of the aircraft that is suspended from the wing [kg]. It should exclude any wing attachments that are not part of the wing structure. :param never_exceed_airspeed: The never-exceed airspeed of the aircraft [m/s]. Used for flutter calculations. :param main_gear_mounted_to_wing: Whether the main gear is mounted to the wing structure. Boolean. :param strut_y_location: The spanwise-location of the strut (if any), as measured from the wing root [meters]. If None, it is assumed that there is no strut (i.e., the wing is a cantilever beam). :param k_e: represents weight knockdowns due to bending moment relief from engines mounted in front of elastic axis. see Torenbeek unlabeled equations, between C-3 and C-4. k_e = 1.0 if engines are not wing mounted, k_e = 0.95 (default) two wing mounted engines in front of the elastic axis and k_e = 0.90 four wing-mounted engines in front of the elastic axis :param return_dict: Whether to return a dictionary of all the intermediate values, or just the final mass. Defaults to False, which returns just the final mass [kg]. Returns: If return_dict is False (default), returns a single value: the mass of the basic wing [kg]. If return_dict is True, returns a dictionary of all the intermediate values. .. py:function:: mass_wing_spoilers_and_speedbrakes(wing, mass_basic_wing) The function mass_spoilers_and_speedbrakes() estimates the weight of the spoilers and speedbrakes according to Torenbeek's "Synthesis of Subsonic Airplane Design", 1976, Appendix C: "Prediction of Wing Structural Weight". N.B. the weight is coming out unrealistic and approx. 20-30% of the weight of the wing. This needs a correction. It uses normally the 12.2 kg/m^2 wing area. :param wing: an instance of AeroSandbox's Wing class. :param mass_basic_wing: The basic weight of the wing (without spoilers, speedbrakes, flaps, slats) [kg] Returns: The mass of the spoilers and speed brakes only [kg] N.B. the weight estimation using the 12.2 kg/m^2 figure comes out too high if using the wing as a referenced area. Reduced to 1.5% of the basic wing mass. .. py:function:: mass_wing(wing, design_mass_TOGW, ultimate_load_factor, suspended_mass, never_exceed_airspeed, max_airspeed_for_flaps, main_gear_mounted_to_wing = True, flap_deflection_angle = 30, strut_y_location = None, return_dict = False) Computes the mass of a wing of an aircraft, according to Torenbeek's "Synthesis of Subsonic Airplane Design", 1976, Appendix C: "Prediction of Wing Structural Weight". Likely more accurate than the Raymer wing weight models. :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. 1.5x the limit load factor. :param suspended_mass: The mass of the aircraft that is suspended from the wing [kg]. :param never_exceed_airspeed: The never-exceed airspeed of the aircraft [m/s]. Used for flutter calculations. :param max_airspeed_for_flaps: The maximum airspeed at which the flaps are allowed to be deployed [m/s]. In the :param absence of other information: :param 1.8x stall speed is a good guess.: :param main_gear_mounted_to_wing: Whether the main gear is mounted to the wing structure. :param flap_deflection_angle: The maximum deflection angle of the flaps [deg]. :param strut_y_location: The y-location of the strut (if any), relative to the wing's leading edge [m]. If None, it is assumed that there is no strut (i.e., the wing is a cantilever beam). :param return_dict: Whether to return a dictionary of all the intermediate values, or just the final mass. Defaults to False, which returns just the final mass. Returns: If return_dict is False (default), returns a single value: the total mass of the wing [kg]. If return_dict is True, returns a dictionary of all the intermediate values. .. py:function:: mass_fuselage_simple(fuselage, never_exceed_airspeed, wing_to_tail_distance) Computes the mass of the fuselage, using Torenbeek's simple version of the calculation. Source: Torenbeek: "Synthesis of Subsonic Airplane Design", 1976 Section 8.4: Weight Prediction Data and Methods 8.4.1: Airframe Structure Eq. 8-16 :param fuselage: The fuselage object. Should be an AeroSandbox Fuselage object. :param never_exceed_airspeed: The never-exceed airspeed of the aircraft, in m/s. :param wing_to_tail_distance: The distance from the quarter-chord of the wing to the quarter-chord of the tail, :param in meters.: Returns: The mass of the fuselage, in kg. .. py:function:: mass_fuselage(fuselage, design_mass_TOGW, ultimate_load_factor, never_exceed_airspeed, wing_to_tail_distance) .. py:function:: mass_propeller(propeller_diameter, propeller_power, n_blades) Computes the mass of a propeller. From Torenbeek: "Synthesis of Subsonic Airplane Design", 1976, Delft University Press. Table 8-9 (pg. 286, PDF page 306) :param propeller_diameter: Propeller diameter, in meters. :param propeller_power: Propeller power, in watts. :param n_blades: Number of propeller blades. Returns: Propeller mass, in kilograms.