Source code for RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.blade_geometry_setup
# RCAIDE/Methods/Energy/Propulsors/Rotor_Design/optimization_setup.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE Imports
import RCAIDE
from RCAIDE.Library.Methods.Geometry.Airfoil import compute_airfoil_properties, compute_naca_4series, import_airfoil_geometry
# Python package imports
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Blade Geometry Setup
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def blade_geometry_setup(rotor, number_of_stations):
"""
Defines a configuration for prop-rotor blade optimization.
Parameters
----------
rotor : RCAIDE.Library.Components.Powertrain.Converters.Rotor
Rotor component with the following attributes:
- number_of_blades : int
Number of blades on the rotor
- tip_radius : float
Tip radius of the rotor [m]
- hub_radius : float
Hub radius of the rotor [m]
- hover : Data
Hover conditions
- design_thrust : float, optional
Design thrust at hover [N]
- design_power : float, optional
Design power at hover [W]
- design_freestream_velocity : float
Freestream velocity at hover [m/s]
- design_altitude : float
Altitude at hover [m]
- oei : Data
One engine inoperative conditions
- design_freestream_velocity : float, optional
Freestream velocity at OEI [m/s]
- design_altitude : float, optional
Altitude at OEI [m]
- design_thrust : float, optional
Design thrust at OEI [N]
- design_power : float, optional
Design power at OEI [W]
- airfoils : dict
Dictionary of airfoil objects
- airfoil_polar_stations : list
List of airfoil section indices for each station
number_of_stations : int
Number of radial stations for blade discretization
Returns
-------
configs : RCAIDE.Library.Components.Configs.Config.Container
Configuration container with the following configs:
- hover : Config
Hover configuration
- oei : Config
One engine inoperative configuration
- cruise : Config (only for prop-rotors)
Cruise configuration
Notes
-----
This function prepares the necessary configurations for rotor blade optimization by:
1. Unpacking rotor geometry parameters
2. Validating design requirements (thrust or power must be specified)
3. Processing airfoil data (importing geometry and computing polars if needed)
4. Setting up the radial distribution of stations
5. Extracting thickness-to-chord ratios from airfoils
6. Setting default OEI conditions if not specified
7. Creating vehicle and network configurations for analysis
The function creates separate configurations for hover, OEI, and cruise (for prop-rotors)
conditions, which are used during the optimization process to evaluate the rotor
performance at different operating points.
**Major Assumptions**
* Either design thrust or design power must be specified (not both)
* If OEI conditions are not specified, they default to hover conditions with 10% increase
* Rotor orientation is set to [0.0, π/2, 0.0] (horizontal rotor)
See Also
--------
RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.optimization_setup
RCAIDE.Library.Methods.Geometry.Airfoil.compute_airfoil_properties
RCAIDE.Library.Methods.Geometry.Airfoil.compute_naca_4series
RCAIDE.Library.Methods.Geometry.Airfoil.import_airfoil_geometry
"""
# Unpack prop-rotor geometry
N = number_of_stations
B = rotor.number_of_blades
R = rotor.tip_radius
Rh = rotor.hub_radius
design_thrust_hover = rotor.hover.design_thrust
design_power_hover = rotor.hover.design_power
chi0 = Rh/R
chi = np.linspace(chi0,1,N+1)
chi = chi[0:N]
airfoils = rotor.airfoils
a_loc = rotor.airfoil_polar_stations
# determine target values
if (design_thrust_hover == None) and (design_power_hover== None):
raise AssertionError('Specify either design thrust or design power at hover!')
elif (design_thrust_hover!= None) and (design_power_hover!= None):
raise AssertionError('Specify either design thrust or design power at hover!')
num_airfoils = len(airfoils.keys())
if num_airfoils>0:
if len(a_loc) != N:
raise AssertionError('\nDimension of airfoil sections must be equal to number of stations on propeller')
for _,airfoil in enumerate(airfoils):
if airfoil.geometry == None: # first, if airfoil geometry data not defined, import from geoemtry files
if type(airfoil) == RCAIDE.Library.Components.Airfoils.NACA_4_Series_Airfoil: # check if naca 4 series of airfoil from datafile
airfoil.geometry = compute_naca_4series(airfoil.NACA_4_Series_code,airfoil.number_of_points)
else:
airfoil.geometry = import_airfoil_geometry(airfoil.coordinate_file,airfoil.number_of_points)
if airfoil.polars == None: # compute airfoil polars for airfoils
airfoil.polars = compute_airfoil_properties(airfoil.geometry, airfoil_polar_files= airfoil.polar_files)
# thickness to chord
t_c = np.zeros(N)
if num_airfoils>0:
for j,airfoil in enumerate(airfoils):
a_geo = airfoil.geometry
locs = np.where(np.array(a_loc) == j )
t_c[locs] = a_geo.thickness_to_chord
# append additional prop-rotor properties for optimization
rotor.number_of_blades = int(B)
rotor.thickness_to_chord = t_c
rotor.radius_distribution = chi*R
# set oei conditions if they are not set
if rotor.oei.design_freestream_velocity == None:
rotor.oei.design_freestream_velocity = rotor.hover.design_freestream_velocity
if rotor.oei.design_altitude == None:
rotor.oei.design_altitude = rotor.hover.design_altitude
if design_thrust_hover == None:
if rotor.oei.design_power == None:
rotor.oei.design_power = rotor.hover.design_power*1.1
elif design_power_hover == None:
if rotor.oei.design_thrust == None:
rotor.oei.design_thrust = rotor.hover.design_thrust*1.1
vehicle = RCAIDE.Vehicle()
net = RCAIDE.Framework.Networks.Electric()
propulsor = RCAIDE.Library.Components.Powertrain.Propulsors.Electric_Rotor()
propulsor.rotor = rotor
net.propulsors.append(propulsor)
vehicle.append_energy_network(net)
configs = RCAIDE.Library.Components.Configs.Config.Container()
base_config = RCAIDE.Library.Components.Configs.Config(vehicle)
config = RCAIDE.Library.Components.Configs.Config(base_config)
config.tag = 'hover'
config.networks.electric.propulsors.electric_rotor.rotor.orientation_euler_angles = [0.0,np.pi/2,0.0]
configs.append(config)
config = RCAIDE.Library.Components.Configs.Config(base_config)
config.tag = 'oei'
config.networks.electric.propulsors.electric_rotor.rotor.orientation_euler_angles = [0.0,np.pi/2,0.0]
configs.append(config)
if type(rotor) == RCAIDE.Library.Components.Powertrain.Converters.Prop_Rotor:
design_thrust_cruise = rotor.cruise.design_thrust
design_power_cruise = rotor.cruise.design_power
if (design_thrust_cruise == None) and (design_power_cruise== None):
raise AssertionError('Specify either design thrust or design power at cruise!')
elif (design_thrust_cruise!= None) and (design_power_cruise!= None):
raise AssertionError('Specify either design thrust or design power at cruise!')
config = RCAIDE.Library.Components.Configs.Config(base_config)
config.tag = 'cruise'
config.networks.electric.propulsors.electric_rotor.rotor.orientation_euler_angles = [0.0,np.pi/2,0.0]
configs.append(config)
return configs
