aerosandbox.library.mass_structural#
Module Contents#
Functions#
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Finds the mass of the wing structure of a human powered aircraft (HPA), following Juan Cruz's correlations in |
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Finds the mass of the spar for a wing on a single- or multi-boom lightweight aircraft. Model originally designed for solar aircraft. |
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Finds the mass of a stabilizer structure of a human powered aircraft (HPA), following Juan Cruz's correlations in |
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Finds the mass of a tail boom structure of a human powered aircraft (HPA), following Juan Cruz's correlations in |
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Estimates the mass of a lifting surface constructed with balsa-monokote-carbon-fiber construction techniques. |
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Estimates the mass of a lifting surface constructed out of a solid piece of material. |
Attributes#
- aerosandbox.library.mass_structural.mass_hpa_wing(span, chord, vehicle_mass, n_ribs, n_wing_sections=1, ultimate_load_factor=1.75, type='cantilevered', t_over_c=0.128, include_spar=True)[source]#
Finds the mass of the wing structure of a human powered aircraft (HPA), following Juan Cruz’s correlations in http://journals.sfu.ca/ts/index.php/ts/article/viewFile/760/718 :param span: wing span [m] :param chord: wing mean chord [m] :param vehicle_mass: aircraft gross weight [kg] :param n_ribs: number of ribs in the wing :param n_wing_sections: number of wing sections or panels (for disassembly?) :param ultimate_load_factor: ultimate load factor [unitless] :param type: Type of bracing: “cantilevered”, “one-wire”, “multi-wire” :param t_over_c: wing airfoil thickness-to-chord ratio :param include_spar: Should we include the mass of the spar? Useful if you want to do your own primary structure calculations. [boolean] :return: Wing structure mass [kg]
- aerosandbox.library.mass_structural.mass_wing_spar(span, mass_supported, ultimate_load_factor=1.75, n_booms=1)[source]#
Finds the mass of the spar for a wing on a single- or multi-boom lightweight aircraft. Model originally designed for solar aircraft. Data was fit to the range 3 < wing_span < 120 [m] and 5 < supported_mass < 3000 [kg], but validity should extend somewhat beyond that. Extremely accurate fits within this range; R^2 > 0.995 for all fits. Source: AeroSandboxstudiesMultiBoomSparMass_v2 Assumptions:
Elliptical lift distribution
Constraint that local wing dihedral/anhedral angle must not exceed 10 degrees anywhere in the ultimate load case.
If multi-boom, assumes roughly static-aerostructurally-optimal placement of the outer booms and equal boom weights.
- Parameters:
span – Wing span [m]
mass_supported – Total mass of all fuselages + tails
ultimate_load_factor – Design load factor. Default taken from Daedalus design.
n_booms – Number of booms on the design. Can be 1, 2, or 3. Assumes optimal placement of the outer booms.
- Returns:
- aerosandbox.library.mass_structural.mass_hpa_stabilizer(span, chord, dynamic_pressure_at_manuever_speed, n_ribs, t_over_c=0.128, include_spar=True)[source]#
Finds the mass of a stabilizer structure of a human powered aircraft (HPA), following Juan Cruz’s correlations in http://journals.sfu.ca/ts/index.php/ts/article/viewFile/760/718 Note: apply this once to BOTH the rudder and elevator!!! :param span: stabilizer span [m] :param chord: stabilizer mean chord [m] :param dynamic_pressure_at_manuever_speed: dynamic pressure at maneuvering speed [Pa] :param n_ribs: number of ribs in the wing :param t_over_c: wing airfoil thickness-to-chord ratio :param include_spar: Should we include the mass of the spar? Useful if you want to do your own primary structure calculations. [boolean] :return: Stabilizer structure mass [kg]
- aerosandbox.library.mass_structural.mass_hpa_tail_boom(length_tail_boom, dynamic_pressure_at_manuever_speed, mean_tail_surface_area)[source]#
Finds the mass of a tail boom structure of a human powered aircraft (HPA), following Juan Cruz’s correlations in http://journals.sfu.ca/ts/index.php/ts/article/viewFile/760/718 Assumes a tubular tail boom of high modules (E > 228 GPa) graphite/epoxy :param length_tail_boom: length of the tail boom [m]. Calculated as distance from the wing 1/4 chord to the furthest tail surface. :param dynamic_pressure_at_manuever_speed: dynamic pressure at maneuvering speed [Pa] :param mean_tail_surface_area: mean of the areas of the tail surfaces (elevator, rudder) :return: mass of the tail boom [m]
- aerosandbox.library.mass_structural.mass_surface_balsa_monokote_cf(chord, span, mean_t_over_c=0.08)[source]#
Estimates the mass of a lifting surface constructed with balsa-monokote-carbon-fiber construction techniques. Warning: Not well validated; spar sizing is a guessed scaling and not based on structural analysis. :param chord: wing mean chord [m] :param span: wing span [m] :param mean_t_over_c: wing thickness-to-chord ratio [unitless] :return: estimated surface mass [kg]
- aerosandbox.library.mass_structural.mass_surface_solid(chord, span, density=2700, mean_t_over_c=0.08)[source]#
Estimates the mass of a lifting surface constructed out of a solid piece of material. Warning: Not well validated; spar sizing is a guessed scaling and not based on structural analysis. :param chord: wing mean chord [m] :param span: wing span [m] :param mean_t_over_c: wing thickness-to-chord ratio [unitless] :return: estimated surface mass [kg]