Aviary
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OpenMDAO
NASA's aircraft analysis, design, and optimization tool
### Summary This PR is optional because it is part of BWB draft PR #749. This PR creates a new GASP based geometry component `WingVolume` and move variable `Aircraft.Fuel.WING_VOLUME_GEOMETRIC_MAX` from...
### Summary - For design load, variable `Aircraft.Wing.LOADING` is replaced by `Mission.Design.GROSS_MASS / Aircraft.Wing.EXPOSED_WING_AREA`. As a result, `BWBLoadSpeeds` and `BWBLoadFactors` replace `LoadSpeeds` and `LoadFactors`. A new group `BWBDesignLoadGroup` is created...
### Summary Overhauls the aerodynamics system to fully support mixing and matching GASP aero methods with energy method mission analysis. - `settings:aerodynamics_method` added to denote which aero method user wants...
### Desired capability or behavior. The off design mission analysis currently instantiates a whole new aviary problem object and re-runs the entirety of the pre-mission block. This is not really...
### Description When running Alternate or fallout missions the masses of avionics and air conditioning systems changes, which is incorrect. The design fuel mass is also incorrectly recalculated. ### Example...
### Desired capability or behavior. Add a phase builder for a on-ground refueling or recharging phase. This would probably be a super simple (explicit) phase with a assumed fixed rate...
### Desired capability or behavior. `EquipAndUsefulLoadMass` in GASP based mass subsystem contains 19 components, each computes one component mass (e.g. APU, control unit, etc.). Each of them should be contained...
### Desired capability or behavior. The default Height-Energy phase info uses boundary constraints for the throttle enforcement rather than a path constraint. I think this needs to be modified to...
### Summary Fixes a bug in the crew & payload preprocessor where providing a passenger count of 0 for a single mission was confused with not providing that particular passenger...
### Description when definining a turboprop engine with an external propeller map provided by the user like this : `shaft_model=EngineDeck(name='shaft',options=options,required_variables=required_vars)` `propeller=PropellerMap(name='Centauri_propeller',options=options)` `turboprop=TurbopropModel('turboprop',options=options,shaft_power_model=shaft_model,propeller_model=propeller)` `prob.load_inputs(r'aircraft_definition.csv',phase_info,engine_builders=[turboprop],verbosity=3)` this leads to an error in the...
