Split GASP mass components

[xjjiang]

Summary

• WingMassTotal is split to two sub-components (with outputs listed):
  • StrutAndFoldMass:
    • Aircraft.Strut.MASS
    • Aircraft.Wing.FOLD_MASS
  • WingMassTotal:
    • Aircraft.Wing.MASS
• ControlMass is split to three sub-components (with outputs listed):
  • MiscControlMass:
    • Aircraft.Controls.COCKPIT_CONTROL_MASS
    • Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS
  • SurfaceControlMass:
    • Aircraft.Wing.SURFACE_CONTROL_MASS
  • SumControlMass:
    • Aircraft.Controls.MASS
• EngineMass is split to three sub-components (with outputs listed):
  • TotalEngineMass:
    • Aircraft.Propulsion.TOTAL_ENGINE_MASS
    • Aircraft.Nacelle.MASS
    • pylon_mass
  • PODMass:
    • Aircraft.Propulsion.TOTAL_ENGINE_POD_MASS
    • Aircraft.Engine.POD_MASS
  • AdditionalEngineMass:
    • Aircraft.Engine.ADDITIONAL_MASS
  • WingMountEngineMass:
    • eng_comb_mass
    • wing_mounted_mass
    • prop_mass_sum
• A new group EngineMassGroup is created to include all the engine sub-components as above.
• Aircraft.Engine.MASS is removed as an output because it is not computed.
• All the engine related components are moved to a new file engine.py from fixed.py.
• Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS is renamed to Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_BASE_MASS.
• A new variable Aircraft.Controls.COCKPIT_CONTROL_MASS is created. This is to meet the desire for output & promote for mass breakdown report.

No change in output from all model runs.

Related Issues

• Resolves #

Backwards incompatibilities

Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS is renamed to Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_BASE_MASS.

New Dependencies

None