fastga.models.load_analysis.wing.aerostructural_loads module

Computes the aerostructural loads on the wing of the aircraft.

class fastga.models.load_analysis.wing.aerostructural_loads.AerostructuralLoad(**kwargs)

Bases: openmdao.core.explicitcomponent.ExplicitComponent

Store some bound methods so we can detect runtime overrides.

setup()

Declare inputs and outputs.

Available attributes:

name pathname comm options

compute(inputs, outputs, discrete_inputs=None, discrete_outputs=None)

Compute outputs given inputs. The model is assumed to be in an unscaled state.

Parameters

• inputs (Vector) – Unscaled, dimensional input variables read via inputs[key].

• outputs (Vector) – Unscaled, dimensional output variables read via outputs[key].

• discrete_inputs (dict or None) – If not None, dict containing discrete input values.

• discrete_outputs (dict or None) – If not None, dict containing discrete output values.

static compute_shear_diagram(y_vector, force_array)

Function that computes the shear diagram of a given array with linear forces in them

@param y_vector: an array containing the position of the different station at which the linear forces are given @param force_array: an array containing the linear forces @return: shear_force_diagram an array representing the shear diagram of the linear forces given in input

static compute_bending_moment_diagram(y_vector, force_array)

Function that computes the root bending diagram of a given array with linear forces in them

@param y_vector: an array containing the position of the different station at which the linear forces are given @param force_array: an array containing the linear forces @return: bending_moment_diagram an array representing the root bending diagram of the linear forces given in input

static compute_cl_s(y_vector_cl_orig, y_vector_chord_orig, y_vector, cl_list, chord_list)

Function that computes linear lift on all section of y_vector based on an original cl distribution

@param y_vector_cl_orig: an array containing the position of the different station at which the original lift distribution was computed, typically a result of OpenVSP or VLM @param y_vector_chord_orig: an array containing the position of the different station at which the chord distribution was computed, typically a result of OpenVSP or VLM @param y_vector: an array containing the position of the different station at which the linear forces are given @param cl_list: an array containing the original lift coefficient distribution @param chord_list: an array containing the original wing chord length at the different station @return: lift_chord an array representing the linear lift at the different station of y_vector, integrating this vector along the wing span and multiplying it by the dynamic pressure will give you the actual lift distribution

static compute_relief_force(inputs, y_vector, chord_vector, wing_mass, fuel_mass, point_mass=True)

Function that computes the baseline weight distribution and modify the y_vector to account for point masses. We chose to represent point masses as linear masses on finite length and to do this we need to modify the y_vector

@param inputs: inputs parameters defined within FAST-OAD-GA @param y_vector: an array containing the original position of the different station at which the chords are given @param chord_vector: an array containing the chord of the wing at different span station @param wing_mass: a float containing the mass of the wing @param fuel_mass: a float containing the mass of the fuel @param point_mass: a boolean, if it’s FALSE all point mass will be equal to zero used in the post-processing @return: y_vector an array containing the position of the wing span at which the wing mass are sampled @return: weight_array an array containing linear masses of all structural components on the wing

static insert_in_sorted_array(array, element)

Function that insert an element in a sorted array to keep it sorted

@param array: a sorted array in which we want to insert an element @param element: the element we want to insert in the sorted array @return: final_array a sorted array based on the input array with the argument float inserted in it @return: index the location at which we add to insert the element ot keep the initial array sorted

static delete_additional_zeros(array, length: Optional[int] = None)

Function that delete the additional zeros we had to add to fit the format imposed by OpenMDAO

@param array: an array with additional zeros we want to delete @param length: if len is specified leave zeros up until the length of the array is len @return: final_array an array containing the same elements of the initial array but with the additional zeros deleted

static add_point_mass(y_vector, chord_vector, point_mass_array, y_point_mass, point_mass, inputs)

Function that add a point mass to an already created point_mass_array. Modify the y station sampling and chord sampling to account for the additional station added.

@param y_vector: the original y_vector which will be modified by adding NB_POINTS_POINT_MASS + 2 points to represent the location of the new point mass @param chord_vector: the original chord vector which will be modified by adding NB_POINTS_POINT_MASS + 2 points to represent the chord at the newly added location @param point_mass_array: the original point mass vector on which we will add the point mass @param y_point_mass: the y station of the point mass @param point_mass: the value of the mass which we want to add @param inputs: inputs parameters defined within FAST-OAD-GA @return: y_vector_new : the new vector contains the y station at which we sample the point mass array with the newly added point mass @return: chord_vector_new : the new vector contains the chord at the new y_station @return: point_mass_array_new : the new vector contains the sampled point mass

fastga.models.load_analysis.wing.aerostructural_loads.tank_volume_distribution(inputs, y_array_orig)

Computes the cross-section of the tank at each span-wise position given in inputs. Assumes a linear variation of the wing chord and relative thickness. Includes a correction coefficient for tank height and includes the effect of landing gear and engine nacelle as reduced capacity. :param inputs: problem inputs vector :param y_array_orig: span-wise location at which to compute the tank cross-section.

Returns

tank cross-section at the input span-wise location.