RCAIDE.Library.Components.Powertrain.Converters.Prop_Rotor

Prop_Rotor#

class Prop_Rotor(*args, **kwarg)[source]#

Bases: Rotor

A prop-rotor component model for tiltrotor and convertible aircraft applications, inheriting from the base Rotor class.

tag#

Identifier for the prop-rotor. Default is ‘prop_rotor’.

Type:

str

orientation_euler_angles#

Vector of angles [rad] defining rotor orientation [θ, φ, ψ]. Default is [0., 0., 0.] for X-direction thrust in vehicle frame.

Type:

list

use_2d_analysis#

Flag for using 2D aerodynamic analysis. Default is False.

Type:

bool

hover#
Hover mode performance parameters
  • design_thrustfloat

    Design point thrust [N]. Default is None.

  • design_torquefloat

    Design point torque [N·m]. Default is None.

  • design_powerfloat

    Design point power [W]. Default is None.

  • design_angular_velocityfloat

    Design point rotational speed [rad/s]. Default is None.

  • design_tip_machfloat

    Design point blade tip Mach number. Default is None.

  • design_acousticsData

    Acoustic characteristics at design point. Default is None.

  • design_performanceData

    Performance metrics at design point. Default is None.

  • design_freestream_velocityfloat

    Design point forward velocity [m/s]. Default is None.

  • design_SPL_dBAfloat

    Design point sound pressure level [dBA]. Default is None.

  • design_blade_pitch_commandfloat

    Design point blade pitch command [rad]. Default is 0.0.

  • design_Clfloat

    Design point lift coefficient. Default is None.

  • design_thrust_coefficientfloat

    Design point thrust coefficient. Default is None.

  • design_power_coefficientfloat

    Design point power coefficient. Default is None.

Type:

Data

cruise#
Cruise mode performance parameters
  • design_thrustfloat

    Design point thrust [N]. Default is None.

  • design_torquefloat

    Design point torque [N·m]. Default is None.

  • design_powerfloat

    Design point power [W]. Default is None.

  • design_angular_velocityfloat

    Design point rotational speed [rad/s]. Default is None.

  • design_tip_machfloat

    Design point blade tip Mach number. Default is None.

  • design_acousticsData

    Acoustic characteristics at design point. Default is None.

  • design_performanceData

    Performance metrics at design point. Default is None.

  • design_SPL_dBAfloat

    Design point sound pressure level [dBA]. Default is None.

  • design_blade_pitch_commandfloat

    Design point blade pitch command [rad]. Default is 0.0.

  • design_Clfloat

    Design point lift coefficient. Default is None.

  • design_thrust_coefficientfloat

    Design point thrust coefficient. Default is None.

  • design_power_coefficientfloat

    Design point power coefficient. Default is None.

Type:

Data

oei#

One engine inoperative performance parameters (Similar structure to hover and cruise attributes)

Type:

Data

optimization_parameters#
  • multiobjective_performance_weightfloat

    Weight factor for multi-objective optimization. Default is 0.5.

Type:

Data

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