fastga.models.geometry.geom_components.wing_tank.compute_mfw_advanced module

Python module for maximum fuel weight calculation with detailed approach, part of the geometry component.

class fastga.models.geometry.geom_components.wing_tank.compute_mfw_advanced.ComputeMFWAdvanced(**kwargs)

Bases: openmdao.core.group.Group

Max fuel weight estimation based on [JM03] p.65. It discretizes the fuel tank in the wings along the span. Only works for linear chord and thickness profiles. The xml quantities “data:geometry:propulsion:tank:LE_chord_percentage”, “data:geometry:propulsion:tank:TE_chord_percentage”, “data:geometry:propulsion:tank:y_ratio_tank_beginning” and “data:geometry:propulsion:tank:y_ratio_tank_end” have to be determined as close to possible as the real aircraft quantities. The quantity “settings:geometry:fuel_tanks:depth” allows to calibrate the model for each aircraft. WARNING : If this class is updated, update_wing_area will have to be updated as well as it uses the same approach.

Set the solvers to nonlinear and linear block Gauss–Seidel by default.

initialize()

Perform any one-time initialization run at instantiation.

setup()

Build this group.

This method should be overidden by your Group’s method. The reason for using this method to add subsystem is to save memory and setup time when using your Group while running under MPI. This avoids the creation of systems that will not be used in the current process.

You may call ‘add_subsystem’ to add systems to this group. You may also issue connections, and set the linear and nonlinear solvers for this group level. You cannot safely change anything on children systems; use the ‘configure’ method instead.

Available attributes:

name pathname comm options