RCAIDE.Library.Methods.Powertrain.Converters.Rotor.Design.optimization_setup

optimization_setup

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’s optimization framework object with the following attributes:

• optimization_problemData

  Optimization problem definition

  • inputsnumpy.ndarray

    Design variables

  • objectivenumpy.ndarray

    Objective function

  • constraintsnumpy.ndarray

    Constraints

• vehicle_configurationslist

  List of vehicle configurations for analysis

• procedureData

  Optimization procedure

• print_iterationsbool

  Flag to print optimization iterations

Return type:

RCAIDE.Framework.Optimization.Common.Nexus

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