RCAIDE.Library.Methods.Powertrain.Propulsors.Electric_Rotor.compute_electric_rotor_performance

compute_electric_rotor_performance#

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

Computes the performance of an electric rotor propulsion system.

Parameters:

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

    Electric rotor propulsor component with the following attributes:
    • tagstr

      Identifier for the propulsor

    • motorData

      Electric motor component - tag : str

      Identifier for the motor

    • rotorData
      Rotor component
      • tagstr

        Identifier for the rotor

      • originlist of lists

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

    • electronic_speed_controllerData
      ESC component
      • tagstr

        Identifier for the ESC

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

    State object containing:
    • conditionsData
      Flight conditions
      • 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 rotor propulsion system by linking the electronic speed controller (ESC), motor, and rotor. 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 rotor

  • Computes the rotor performance

  • Calculates the moment generated by the rotor 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 rotor

  • Moment is calculated relative to the aircraft center of gravity

  • Moment from motor rotation is not included

See also

RCAIDE.Library.Methods.Powertrain.Converters.Motor.compute_motor_performance, RCAIDE.Library.Methods.Powertrain.Converters.Rotor.compute_rotor_performance, RCAIDE.Library.Methods.Powertrain.Modulators.Electronic_Speed_Controller

reuse_stored_electric_rotor_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.