# RCAIDE/Methods/Energy/Propulsors/Rotor_Design/optimization_setup.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE Imports
import RCAIDE
from RCAIDE.Framework.Core import Units, Data
from RCAIDE.Framework.Optimization.Common import Nexus
from RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.blade_geometry_setup import blade_geometry_setup
from RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.procedure_setup import procedure_setup
# Python package imports
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Optimization Setuo
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def optimization_setup(rotor, number_of_stations, print_iterations):
"""
Sets up rotor optimization problem including design variables, constraints and objective function
using RCAIDE's Nexus optimization framework.
Parameters
----------
rotor : RCAIDE.Library.Components.Powertrain.Converters.Rotor
Rotor component (Lift_Rotor or Prop_Rotor) with optimization parameters
number_of_stations : int
Number of radial stations for blade discretization
print_iterations : bool
Flag to print optimization iterations
Returns
-------
nexus : RCAIDE.Framework.Optimization.Common.Nexus
RCAIDE's optimization framework object with the following attributes:
- optimization_problem : Data
Optimization problem definition
- inputs : numpy.ndarray
Design variables
- objective : numpy.ndarray
Objective function
- constraints : numpy.ndarray
Constraints
- vehicle_configurations : list
List of vehicle configurations for analysis
- procedure : Data
Optimization procedure
- print_iterations : bool
Flag to print optimization iterations
Notes
-----
This function configures a complete optimization problem for rotor blade design by:
1. Creating a Nexus optimization framework
2. Validating the rotor type (must be Lift_Rotor or Prop_Rotor)
3. Setting up design variables with bounds and scaling
4. Defining the objective function
5. Establishing constraints for performance and geometry
6. Creating aliases to link optimization variables to vehicle properties
7. Setting up vehicle configurations using blade_geometry_setup
8. Configuring the optimization procedure
The design variables include:
- chord_r, chord_p, chord_q, chord_t: Parameters defining the chord distribution
- twist_r, twist_p, twist_q, twist_t: Parameters defining the twist distribution
- hover_tip_mach: Tip Mach number in hover
- OEI_tip_mach: Tip Mach number in one-engine-inoperative condition
- OEI_collective_pitch: Collective pitch in one-engine-inoperative condition
- cruise_tip_mach, cruise_collective_pitch: Additional parameters for prop rotors
Constraints ensure:
- Thrust and power requirements are met
- Blade taper is within reasonable bounds (0.3 to 0.9)
- Blade twist is positive
- Maximum sectional lift coefficient is below 0.8
- Chord and twist distribution parameters maintain reasonable ratios
**Major Assumptions**
* Minimum allowable blade taper: 0.3
* Maximum allowable blade taper: 0.9
* Maximum sectional lift coefficient: 0.8
See Also
--------
RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.blade_geometry_setup
RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.procedure_setup
"""
nexus = Nexus()
problem = Data()
nexus.optimization_problem = problem
if type(rotor) != RCAIDE.Library.Components.Powertrain.Converters.Prop_Rotor or type(rotor) != RCAIDE.Library.Components.Powertrain.Converters.Lift_Rotor:
assert('rotor must be of Lift-Rotor or Prop-Rotor class')
if type(rotor) == RCAIDE.Library.Components.Powertrain.Converters.Prop_Rotor:
nexus.prop_rotor_flag = True
else:
nexus.prop_rotor_flag = False
# -------------------------------------------------------------------
# Inputs
# -------------------------------------------------------------------
R = rotor.tip_radius
tm_ll_h = rotor.optimization_parameters.tip_mach_range[0]
tm_ul_h = rotor.optimization_parameters.tip_mach_range[1]
tm_0_h = (tm_ul_h + tm_ll_h)/2
if nexus.prop_rotor_flag:
tm_ll_c = rotor.optimization_parameters.tip_mach_range[0]
tm_ul_c = rotor.optimization_parameters.tip_mach_range[1]
inputs = []
inputs.append([ 'chord_r' , 0.1*R , 0.05*R , 0.2*R , 1.0 , 1*Units.less])
inputs.append([ 'chord_p' , 2 , 0.25 , 2.0 , 1.0 , 1*Units.less])
inputs.append([ 'chord_q' , 1 , 0.25 , 1.5 , 1.0 , 1*Units.less])
inputs.append([ 'chord_t' , 0.05*R , 0.02*R , 0.1*R , 1.0 , 1*Units.less])
inputs.append([ 'twist_r' , np.pi/6 , 0 , np.pi/4 , 1.0 , 1*Units.less])
inputs.append([ 'twist_p' , 1 , 0.25 , 2.0 , 1.0 , 1*Units.less])
inputs.append([ 'twist_q' , 0.5 , 0.25 , 1.5 , 1.0 , 1*Units.less])
inputs.append([ 'twist_t' , np.pi/6 , 0 , np.pi/4 , 1.0 , 1*Units.less])
inputs.append([ 'hover_tip_mach' , tm_0_h , tm_ll_h , tm_ul_h , 1.0 , 1*Units.less])
inputs.append([ 'OEI_tip_mach' , tm_0_h , tm_ll_h , 0.85 , 1.0 , 1*Units.less])
inputs.append([ 'OEI_collective_pitch' , np.pi/6 , -np.pi/5 , np.pi/5 , 1.0 , 1*Units.less])
if nexus.prop_rotor_flag:
inputs.append([ 'cruise_tip_mach' , tm_ll_c , tm_ll_c , tm_ul_c , 1.0 , 1*Units.less])
inputs.append([ 'cuise_collective_pitch' , np.pi/8 , -np.pi/5 , np.pi/5 , 1.0 , 1*Units.less])
problem.inputs = np.array(inputs,dtype=object)
# -------------------------------------------------------------------
# Objective
# -------------------------------------------------------------------
problem.objective = np.array([
[ 'objective' , 1.0 , 1*Units.less]
],dtype=object)
# -------------------------------------------------------------------
# Constraints
# -------------------------------------------------------------------
constraints = []
constraints.append([ 'hover_thrust_pow_res' , '<' , 1E-3 , 1.0 , 1*Units.less])
constraints.append([ 'blade_taper_constraint_1' , '>' , 0.3 , 1.0 , 1*Units.less])
constraints.append([ 'blade_taper_constraint_2' , '<' , 0.9 , 1.0 , 1*Units.less])
constraints.append([ 'blade_twist_constraint' , '>' , 0.0 , 1.0 , 1*Units.less])
constraints.append([ 'max_sectional_cl_hov' , '<' , 0.8 , 1.0 , 1*Units.less])
constraints.append([ 'chord_p_to_q_ratio' , '>' , 0.5 , 1.0 , 1*Units.less])
constraints.append([ 'twist_p_to_q_ratio' , '>' , 0.5 , 1.0 , 1*Units.less])
constraints.append([ 'OEI_hov_thrust_pow_res' , '<' , 1E-3 , 1.0 , 1*Units.less])
if nexus.prop_rotor_flag:
constraints.append([ 'cruise_thrust_pow_res' , '<' , 1E-3 , 1.0 , 1*Units.less])
constraints.append([ 'max_sectional_cl_cruise' , '<' , 0.8 , 1.0 , 1*Units.less])
problem.constraints = np.array(constraints,dtype=object)
# -------------------------------------------------------------------
# Aliases
# -------------------------------------------------------------------
aliases = []
aliases.append([ 'chord_r' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.chord_r' ])
aliases.append([ 'chord_p' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.chord_p' ])
aliases.append([ 'chord_q' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.chord_q' ])
aliases.append([ 'chord_t' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.chord_t' ])
aliases.append([ 'twist_r' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.twist_r' ])
aliases.append([ 'twist_p' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.twist_p' ])
aliases.append([ 'twist_q' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.twist_q' ])
aliases.append([ 'twist_t' , 'vehicle_configurations.*.networks.electric.propulsors.electric_rotor.rotor.twist_t' ])
aliases.append([ 'hover_tip_mach' , 'vehicle_configurations.hover.networks.electric.propulsors.electric_rotor.rotor.hover.design_tip_mach' ])
aliases.append([ 'objective' , 'summary.objective' ])
aliases.append([ 'hover_thrust_pow_res' , 'summary.hover_thrust_power_residual' ])
aliases.append([ 'blade_taper_constraint_1' , 'summary.blade_taper_constraint_1'])
aliases.append([ 'blade_taper_constraint_2' , 'summary.blade_taper_constraint_2'])
aliases.append([ 'blade_twist_constraint' , 'summary.blade_twist_constraint'])
aliases.append([ 'max_sectional_cl_hov' , 'summary.max_sectional_cl_hover'])
aliases.append([ 'chord_p_to_q_ratio' , 'summary.chord_p_to_q_ratio' ])
aliases.append([ 'twist_p_to_q_ratio' , 'summary.twist_p_to_q_ratio' ])
aliases.append([ 'OEI_hov_thrust_pow_res' , 'summary.oei_thrust_power_residual' ])
aliases.append([ 'OEI_collective_pitch' , 'vehicle_configurations.oei.networks.electric.propulsors.electric_rotor.rotor.oei.design_blade_pitch_command' ])
aliases.append([ 'OEI_tip_mach' , 'vehicle_configurations.oei.networks.electric.propulsors.electric_rotor.rotor.oei.design_tip_mach' ])
if nexus.prop_rotor_flag:
aliases.append([ 'cruise_tip_mach' , 'vehicle_configurations.cruise.networks.electric.propulsors.electric_rotor.rotor.cruise.design_tip_mach' ])
aliases.append([ 'cuise_collective_pitch' , 'vehicle_configurations.cruise.networks.electric.propulsors.electric_rotor.rotor.cruise.design_blade_pitch_command' ])
aliases.append([ 'cruise_thrust_pow_res' , 'summary.cruise_thrust_power_residual' ])
aliases.append([ 'max_sectional_cl_cruise', 'summary.max_sectional_cl_cruise'])
problem.aliases = aliases
# -------------------------------------------------------------------
# Vehicles
# -------------------------------------------------------------------
nexus.vehicle_configurations = blade_geometry_setup(rotor,number_of_stations)
# -------------------------------------------------------------------
# Analyses
# -------------------------------------------------------------------
nexus.analyses = None
# -------------------------------------------------------------------
# Missions
# -------------------------------------------------------------------
nexus.missions = None
# -------------------------------------------------------------------
# Procedure
# -------------------------------------------------------------------
nexus.print_iterations = print_iterations
nexus.procedure = procedure_setup()
# -------------------------------------------------------------------
# Summary
# -------------------------------------------------------------------
nexus.summary = Data()
nexus.results.hover = Data()
nexus.results.cruise = Data()
nexus.results.oei = Data()
return nexus
