RCAIDE.Library.Methods.Powertrain.Propulsors.Internal_Combustion_Engine.compute_internal_combustion_engine_performance

compute_internal_combustion_engine_performance#

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

Computes the performance of an internal combustion engine propulsion system.

Parameters:

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

    Internal combustion engine propulsor component with the following attributes:
    • tagstr

      Identifier for the propulsor

    • engineData
      Engine component
      • tagstr

        Identifier for the engine

    • propellerData
      Propeller component
      • tagstr

        Identifier for the propeller

      • originlist of lists

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

  • 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

    • 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] (zero for non-hybrid engines)

  • 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 internal combustion engine propulsion system by linking the engine to the propeller. It performs the following steps:

  • Sets the engine throttle based on the propulsor throttle

  • Computes the engine power output using the throttle setting

  • Transfers the engine’s angular velocity and throttle to the propeller

  • Computes the propeller performance

  • Calculates the moment generated by the propeller thrust

  • Stores the results in the conditions data structure

The function assumes a direct mechanical connection between the engine and propeller, with no electrical power generation or consumption (non-hybrid configuration).

Major Assumptions

  • Direct mechanical connection between engine and propeller

  • No electrical power generation or consumption

See also

RCAIDE.Library.Methods.Powertrain.Converters.Engine.compute_power_from_throttle, RCAIDE.Library.Methods.Powertrain.Converters.Rotor.compute_rotor_performance

reuse_stored_internal_combustion_engine_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 [-] fuel_line - fuel line [-] propulsor - propulsor data structure [-] total_thrust - thrust of propulsor group [N] total_power - power of propulsor group [W]

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

Properties Used: N.A.