Source code for RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop.append_turboprop_conditions
# RCAIDE/Library/Methods/Powertrain/Propulsors/Turboprop/append_turboprop_conditions.py
#
# Created: Jun 2024, M. Clarke
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# IMPORT
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# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Mission.Common import Conditions
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# append_turboprop_conditions
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[docs]
def append_turboprop_conditions(propulsor, segment, energy_conditions, noise_conditions):
"""
Initializes turboprop operating conditions for a mission segment.
Parameters
----------
propulsor : RCAIDE.Library.Components.Propulsors.Turboprop
Turboprop propulsor component with the following attributes:
- tag : str
Identifier for the turboprop
- items : dict
Dictionary of subcomponents
segment : RCAIDE.Framework.Mission.Segments.Segment
Mission segment with the following attributes:
- state : Data
Segment state
- ones_row : function
Function to create array of ones with specified length
energy_conditions : RCAIDE.Framework.Mission.Common.Conditions
Energy conditions container where turboprop conditions will be stored
noise_conditions : RCAIDE.Framework.Mission.Common.Conditions
Noise conditions container where turboprop noise conditions will be stored
Returns
-------
None
Results are stored in energy_conditions.propulsors[propulsor.tag] and
noise_conditions.propulsors[propulsor.tag]
Notes
-----
This function initializes the necessary data structures for storing turboprop
operating conditions during a mission segment. It creates zero-filled arrays
for various performance parameters and recursively calls the append_operating_conditions
method for each subcomponent of the turboprop.
The function initializes the following parameters:
* throttle
* commanded_thrust_vector_angle
* power
* fuel_flow_rate
* inputs and outputs containers
It also creates a core_nozzle container in the noise conditions.
**Major Assumptions**
* All arrays are initialized with zeros
* Each component has an append_operating_conditions method
See Also
--------
RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop.compute_turboprop_performance
RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop.compute_thrust
"""
# unpack
ones_row = segment.state.ones_row
# add propulsor conditions
energy_conditions.propulsors[propulsor.tag] = Conditions()
energy_conditions.propulsors[propulsor.tag].throttle = 0. * ones_row(1)
energy_conditions.propulsors[propulsor.tag].commanded_thrust_vector_angle = 0. * ones_row(1)
energy_conditions.propulsors[propulsor.tag].power = 0. * ones_row(1)
energy_conditions.propulsors[propulsor.tag].fuel_flow_rate = 0. * ones_row(1)
energy_conditions.propulsors[propulsor.tag].inputs = Conditions()
energy_conditions.propulsors[propulsor.tag].outputs = Conditions()
noise_conditions.propulsors[propulsor.tag] = Conditions()
noise_conditions.propulsors[propulsor.tag].core_nozzle = Conditions()
for tag, item in propulsor.items():
if issubclass(type(item), RCAIDE.Library.Components.Component):
item.append_operating_conditions(segment,energy_conditions)
for sub_tag, sub_item in item.items():
if issubclass(type(sub_item), RCAIDE.Library.Components.Component):
sub_item.append_operating_conditions(segment,energy_conditions)
return
