Data Structures#

class tuduam.data_structures.Aerodynamics(*, cL_alpha: float | None = None, alpha_zero_lift: float | None = None, cd0: float | None = None, spanwise_points: int | None = None)[source]#

Bases: Parent

alpha_zero_lift: float | None#

cL_alpha: float | None#

cd0: float | None#: “Zero lift drag coefficient

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

spanwise_points: int | None#: “The spanwise points used in the Weissinger-L/Lifiting line method. Odd integer

class tuduam.data_structures.Airfoil(*, cl_alpha: Annotated[float, Gt(gt=2)], thickness_to_chord: float | None = None)[source]#

Bases: Parent

cl_alpha: float#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

thickness_to_chord: float | None#

Bases: Parent

diameter: float | None#

ignore_loc: List | None#: “Index of which engne positions to ignore in the wingbox analysis. For example when the engine is placed on the fuselage

mass: float | None#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

n_engines: int#

power_grav_density: float | None#

power_vol_density: float | None#

thrust: float | None#

x_rotor_loc: List | None#: “A list of the x coordinates of your engines for both sides. Thus if you have 4 engines in total, the list must be 4 elements long. eg [2,4,4,2]. See section about coordinate systems if you have questions regardign this.

x_rotor_rel_loc: List | None#: “Same as x_rotor_locations but relative to the wing, that is the leading edge of the spanwise location of the engine. Negative values are infront the wing

y_rotor_loc: List | None#: “A list of the y coordinates of your engines for both sides. Thus if you have 4 engines in total, the list must be 4 elements long and correspond to the elements x_rotor_locations. eg [-6,-3,3,6]. See section about coordinate systems if you have questions regardign this.

Bases: Parent

cL_cruise: float | None#

h_cruise: float | None#: “cruise altitude

mission_energy: float | None#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

n_ult: float | None#

v_cruise: float | None#

wingloading: float | None#

class tuduam.data_structures.Fuselage(*, length_fuselage: float | None = None, width_fuselage: float | None = None, height_fuselage: float | None = None, mass: float | None = None)[source]#

Bases: Parent

height_fuselage: float | None#

length_fuselage: float | None#

mass: float | None#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

width_fuselage: float | None#

class tuduam.data_structures.HybridPowertrain(*, fuel_cell_mass: float | None = None, battery_mass: float | None = None)[source]#

Bases: Parent

battery_mass: float | None#

fuel_cell_mass: float | None#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

Bases: Parent

beta_crippling: float | None#: Material constant specific for crippling

density: float | None#

g_crippling: float | None#

Material constant specific for crippling Source

[1] T.H.G.Megson. Aerospace Structural Design an Analysis, 4th ed. Oxford, UK: Elsevier, 2007. isbn: -13: 978-0-75066-7395.

load_factor: float | None#

m_crippling: float | None#: Material constant specific for crippling

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

poisson: float | None#

post_buckling_ratio: float | None#

(PB) The ratio of the applied load to the bucklingload and, for post-buckled structures is greater than 1

Source

[1] Kassapoglou, C. (2010). page 145, Design and analysis of composite structures: With applications to aerospace structures. John Wiley & Sons.

safety_factor: float#

shear_modulus: float | None#

shear_strength: float | None#

sigma_ultimate: float | None#

sigma_yield: float | None#

young_modulus: float | None#

class tuduam.data_structures.Parent[source]#

Bases: BaseModel

classmethod load_from_json(file_path: Annotated[Path, PathType(path_type=file)])[source]#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

class tuduam.data_structures.Propeller(*, n_blades: float, r_prop: float, rpm_cruise: float, xi_0: float, chord_arr: list | None = None, rad_arr: list | None = None, pitch_arr: list | None = None, tc_ratio: float | None = None)[source]#

Bases: Parent

chord_arr: list | None#: “Array with the chords at each station

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

n_blades: float#: The number of blades on the propellor

pitch_arr: list | None#: “Array with the pitch at each station

r_prop: float#: “Propeller radius

rad_arr: list | None#: “Radial coordinates for each station

rpm_cruise: float#: “The rotations per minute during cruise flight

tc_ratio: float | None#: Thickness over chord ratio of the airfoil

xi_0: float#: “Non-dimensional hub radius (r_hub/R) [-]

Bases: Parent

aspect_ratio: float#

chord_mac: float | None#

chord_root: float | None#

chord_tip: float | None#

fl_thickness: float | None#

mass: float | None#

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

n_ribs: int | None#

n_str: int | None#: “The amount of stringers on one flange

quarterchord_sweep: float#

rib_loc: List | None#: “A list of the spanwise position of the ribs. Can be left to None as it will be automatically created. Howeve if pre-defined it will keep this list

skin_thickness: float | None#

span: float | None#

spar_thickness: float | None#

stringer_height: float | None#

stringer_thickness: float | None#

stringer_width: float | None#

surface: float | None#

sweep_le: float | None#

t_rib: float | None#

taper: float#

washout: float#: “The geometric twist between the tip and root chord in radians. Negative value indicates washin i.e the tip is at a higher AoA.

wingbox_end: float | None#

wingbox_start: float | None#

x_le_root_global: float | None#: “The coordinate of the leading edge of the root chord. Defines the positioning of the wing

x_lemac_local: float | None#

y_mac: float | None#

class tuduam.data_structures.VTOL(*, mtom: float | None = None, oem: float | None = None)[source]#

Bases: Parent

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

mtom: float | None#

oem: float | None#

Bases: Parent

area_str: float | None#: “Area of the stringer. Note that if you define area of the stringer. You can’t define stringers dimensions. The reason both options exists is a result of how the API developped over time and the requirement for stringer geometry for constraints.

h_st: float | None#: “ Thickness of the stringer

model_config = {'extra': 'forbid', 'validate_assignment': True}#: Configuration for the model, should be a dictionary conforming to [ConfigDict][pydantic.config.ConfigDict].

n_cell: int#: “The amount of cells in the wingbox structure

spar_loc_nondim: list#: “The location of the spar over the chord so dimensionless. Length should be n_cell - 1

str_cell: list | None#: “List of stringers (both top and bottom) per cell. Length should be n_cell. Due to the discretization it also required to be an even number

t_sk_cell: list | None#: The thickness of the skin in each cell, length should be equal to n_cell

t_sp: float | None#: The thickness of the spars

t_st: float | None#: “ Thickness of the stringer

w_st: float | None#: “ Thickness of the stringer

Data Structures#

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