fastga.models.geometry.geom_components.fuselage.components.compute_fuselage_volume module

Python module for fuselage volume calculation, part of the fuselage geometry.

class fastga.models.geometry.geom_components.fuselage.components.compute_fuselage_volume.ComputeFuselageVolume(**kwargs)[source]

Bases: openmdao.core.explicitcomponent.ExplicitComponent

Fuselage volume computation. Based on geometric consideration assuming the fuselage is cylindrical at the center section and conical at the front and back.

Store some bound methods so we can detect runtime overrides.

setup()[source]

Declare inputs and outputs.

Available attributes:

name pathname comm options

compute(inputs, outputs, discrete_inputs=None, discrete_outputs=None)[source]

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.

compute_partials(inputs, partials, discrete_inputs=None)[source]

Compute sub-jacobian parts. The model is assumed to be in an unscaled state.

Parameters

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

  • partials (Jacobian) – Sub-jac components written to partials[output_name, input_name]..

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