RCAIDE.Library.Methods.Powertrain.Propulsors.Electric_Ducted_Fan.compute_electric_ducted_fan_performance

compute_electric_ducted_fan_performance#

compute_electric_ducted_fan_performance(propulsor, state, center_of_gravity=[[0.0, 0.0, 0.0]])[source]#

Computes the performance of an electric ducted fan propulsion system.

Parameters:

  • propulsor (RCAIDE.Library.Components.Propulsors.Electric_Ducted_Fan) –

    Electric ducted fan propulsor component with the following attributes:
    • tagstr

      Identifier for the propulsor

    • motorData
      Electric motor component
      • tagstr

        Identifier for the motor

    • ducted_fanData
      Ducted fan component
      • tagstr

        Identifier for the ducted fan

      • originlist of lists

        Origin coordinates [[x, y, z]] [m]

      • tip_radiusfloat

        Tip radius of the ducted fan [m]

    • electronic_speed_controllerData
      ESC component
      • tagstr

        Identifier for the ESC

  • state (RCAIDE.Framework.Mission.Common.State) –

    State object containing:
    • conditionsData
      Flight conditions
      • freestreamData
        Freestream properties
        • speed_of_soundnumpy.ndarray

          Speed of sound [m/s]

      • energyData
        Energy conditions
        • propulsorsdict

          Propulsor energy conditions indexed by tag

        • convertersdict

          Converter energy conditions indexed by tag

        • modulatorsdict

          Modulator energy conditions indexed by tag

    • ones_rowfunction

      Function to create array of ones with specified length

  • center_of_gravity (list of lists, optional) – Center of gravity coordinates [[x, y, z]] [m] Default: [[0.0, 0.0, 0.0]]

Returns:

  • thrust (numpy.ndarray) – Thrust force vector [N]

  • moment (numpy.ndarray) – Moment vector [N·m]

  • power (numpy.ndarray) – Mechanical power [W]

  • power_elec (numpy.ndarray) – Electrical power [W]

  • stored_results_flag (bool) – Flag indicating if results are stored

  • stored_propulsor_tag (str) – Tag of the propulsor with stored results

Notes

This function computes the performance of an electric ducted fan propulsion system by linking the electronic speed controller (ESC), motor, and ducted fan. It performs the following steps:

  • Sets the ESC throttle based on the propulsor throttle

  • Computes the ESC output voltage

  • Transfers the ESC output voltage to the motor

  • Computes the motor performance (angular velocity and torque)

  • Transfers the motor angular velocity to the ducted fan

  • Calculates the ducted fan tip Mach number

  • Transfers the propulsor thrust vector angle to the ducted fan

  • Computes the ducted fan performance

  • Calculates the moment generated by the ducted fan thrust

  • Computes the ESC input current

  • Stores the results in the conditions data structure

Major Assumptions

  • The ESC throttle directly controls the output voltage

  • The motor angular velocity directly drives the ducted fan

  • Moment is calculated relative to the aircraft center of gravity

See also

RCAIDE.Library.Methods.Powertrain.Converters.Motor.compute_motor_performance, RCAIDE.Library.Methods.Powertrain.Converters.Ducted_Fan.compute_ducted_fan_performance, RCAIDE.Library.Methods.Powertrain.Modulators.Electronic_Speed_Controller

reuse_stored_electric_ducted_fan_data(propulsor, state, network, stored_propulsor_tag, center_of_gravity=[[0.0, 0.0, 0.0]])[source]#

Reuses results from one propulsor for identical propulsors

Assumptions: N/A

Source: N/A

Inputs: conditions - operating conditions data structure [-] voltage - system voltage [V] bus - bus [-] propulsors - propulsor data structure [-] total_thrust - thrust of propulsor group [N] total_power - power of propulsor group [W] total_current - current of propulsor group [A]

Outputs: total_thrust - thrust of propulsor group [N] total_power - power of propulsor group [W] total_current - current of propulsor group [A]

Properties Used: N.A.