Source code for RCAIDE.Library.Components.Powertrain.Converters.Prop_Rotor
# RCAIDE/Library/Components/Propulsors/Converters/Prop_Rotor.py
#
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from RCAIDE.Framework.Core import Data
from .Rotor import Rotor
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# PROP-ROTOR CLASS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Prop_Rotor(Rotor):
"""
A prop-rotor component model for tiltrotor and convertible aircraft applications, inheriting from the base Rotor class.
Attributes
----------
tag : str
Identifier for the prop-rotor. Default is 'prop_rotor'.
orientation_euler_angles : list
Vector of angles [rad] defining rotor orientation [θ, φ, ψ].
Default is [0., 0., 0.] for X-direction thrust in vehicle frame.
use_2d_analysis : bool
Flag for using 2D aerodynamic analysis. Default is False.
hover : Data
Hover mode performance parameters
- design_thrust : float
Design point thrust [N]. Default is None.
- design_torque : float
Design point torque [N·m]. Default is None.
- design_power : float
Design point power [W]. Default is None.
- design_angular_velocity : float
Design point rotational speed [rad/s]. Default is None.
- design_tip_mach : float
Design point blade tip Mach number. Default is None.
- design_acoustics : Data
Acoustic characteristics at design point. Default is None.
- design_performance : Data
Performance metrics at design point. Default is None.
- design_freestream_velocity : float
Design point forward velocity [m/s]. Default is None.
- design_SPL_dBA : float
Design point sound pressure level [dBA]. Default is None.
- design_blade_pitch_command : float
Design point blade pitch command [rad]. Default is 0.0.
- design_Cl : float
Design point lift coefficient. Default is None.
- design_thrust_coefficient : float
Design point thrust coefficient. Default is None.
- design_power_coefficient : float
Design point power coefficient. Default is None.
cruise : Data
Cruise mode performance parameters
- design_thrust : float
Design point thrust [N]. Default is None.
- design_torque : float
Design point torque [N·m]. Default is None.
- design_power : float
Design point power [W]. Default is None.
- design_angular_velocity : float
Design point rotational speed [rad/s]. Default is None.
- design_tip_mach : float
Design point blade tip Mach number. Default is None.
- design_acoustics : Data
Acoustic characteristics at design point. Default is None.
- design_performance : Data
Performance metrics at design point. Default is None.
- design_SPL_dBA : float
Design point sound pressure level [dBA]. Default is None.
- design_blade_pitch_command : float
Design point blade pitch command [rad]. Default is 0.0.
- design_Cl : float
Design point lift coefficient. Default is None.
- design_thrust_coefficient : float
Design point thrust coefficient. Default is None.
- design_power_coefficient : float
Design point power coefficient. Default is None.
oei : Data
One engine inoperative performance parameters
(Similar structure to hover and cruise attributes)
optimization_parameters : Data
- multiobjective_performance_weight : float
Weight factor for multi-objective optimization. Default is 0.5.
Notes
-----
The Prop_Rotor class models rotors designed for both hover and forward flight,
typical of tiltrotor aircraft. It includes capabilities for:
* Hover and cruise performance analysis
* One engine inoperative (OEI) conditions
* Variable pitch operation
* Acoustic analysis
* Performance optimization
* Multi-mode operation
**Definitions**
'OEI'
One Engine Inoperative - emergency condition where one engine fails
'SPL'
Sound Pressure Level - measure of acoustic intensity
'Tip Mach'
Mach number at the blade tip, including rotational and forward flight effects
'Multi-objective Performance'
Combined optimization of multiple performance metrics
See Also
--------
RCAIDE.Library.Components.Powertrain.Converters.Rotor
RCAIDE.Library.Components.Powertrain.Converters.Lift_Rotor
"""
def __defaults__(self):
"""This sets the default values for the component to function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
self.tag = 'prop_rotor'
self.orientation_euler_angles = [0.,0.,0.] # This is X-direction thrust in vehicle frame
self.use_2d_analysis = False
self.hover = Data()
self.hover.design_thrust = None
self.hover.design_torque = None
self.hover.design_power = None
self.hover.design_angular_velocity = None
self.hover.design_tip_mach = None
self.hover.design_acoustics = None
self.hover.design_performance = None
self.hover.design_freestream_velocity = None
self.hover.design_SPL_dBA = None
self.hover.design_blade_pitch_command = 0.0
self.hover.design_efficiency = 0.86
self.hover.design_Cl = None
self.hover.design_thrust_coefficient = None
self.hover.design_power_coefficient = None
self.hover.design_torque_coefficient = None
self.oei = Data()
self.oei.design_thrust = None
self.oei.design_torque = None
self.oei.design_power = None
self.oei.design_angular_velocity = None
self.oei.design_tip_mach = None
self.oei.design_acoustics = None
self.oei.design_performance = None
self.oei.design_freestream_velocity = None
self.oei.design_blade_pitch_command = 0.0
self.oei.design_efficiency = 0.86
self.oei.design_altitude = None
self.oei.design_SPL_dBA = None
self.oei.design_Cl = None
self.oei.design_thrust_coefficient = None
self.oei.design_power_coefficient = None
self.oei.design_torque_coefficient = None
self.cruise = Data()
self.cruise.design_thrust = None
self.cruise.design_torque = None
self.cruise.design_power = None
self.cruise.design_angular_velocity = None
self.cruise.design_tip_mach = None
self.cruise.design_acoustics = None
self.cruise.design_performance = None
self.cruise.design_SPL_dBA = None
self.cruise.design_blade_pitch_command = 0.0
self.cruise.design_efficiency = 0.86
self.cruise.design_Cl = None
self.cruise.design_thrust_coefficient = None
self.cruise.design_power_coefficient = None
self.cruise.design_torque_coefficient = None
self.optimization_parameters.multiobjective_performance_weight = 0.5
