Source code for RCAIDE.Library.Methods.Powertrain.Converters.Supersonic_Nozzle.append_supersonic_nozzle_conditions
# RCAIDE/Library/Methods/Powertrain/Converters/Supersonic_Nozzle/append_supersonic_nozzle_conditions.py
#
# Created: Jun 2024, M. Clarke
from RCAIDE.Framework.Mission.Common import Conditions
# ----------------------------------------------------------------------------------------------------------------------
# append_supersonic_nozzle_conditions
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def append_supersonic_nozzle_conditions(supersonic_nozzle, segment, energy_conditions):
"""
Initializes and appends supersonic nozzle conditions data structures to the propulsor conditions dictionary.
Parameters
----------
supersonic_nozzle : SupersonicNozzle
The supersonic nozzle component for which conditions are being initialized.
segment : Segment
The mission segment in which the supersonic nozzle is operating.
energy_conditions : dict
Dictionary containing conditions for all propulsion components.
Returns
-------
None
This function modifies the propulsor_conditions dictionary in-place.
Notes
-----
This function creates empty Conditions objects for the supersonic nozzle's inputs and outputs
within the propulsor_conditions dictionary. These conditions will be populated during
the mission analysis process.
See Also
--------
RCAIDE.Library.Methods.Powertrain.Converters.Supersonic_Nozzle.compute_supersonic_nozzle_performance
"""
energy_conditions.converters[supersonic_nozzle.tag] = Conditions()
energy_conditions.converters[supersonic_nozzle.tag].inputs = Conditions()
energy_conditions.converters[supersonic_nozzle.tag].outputs = Conditions()
return
