RCAIDE.Library.Components.Powertrain.Propulsors.Electric_Rotor

Electric_Rotor#

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

Bases: Propulsor

A propulsion system class that combines an electric motor with a rotor for vertical and forward flight.

tag#

Identifier for the propulsion system, defaults to ‘electric_rotor’

Type:

str

motor#

The electric motor component that provides rotational power

Type:

None or Motor

rotor#

The rotor component that generates lift and thrust

Type:

None or Rotor

electronic_speed_controller#

The electronic speed controller that regulates power to the motor

Type:

None or ESC

active_crypgenic_tanks_tanks#

Collection of active cryogenoc tanks. Default is None.

Type:

None or list

Notes

This class models an electric propulsion system where an electric motor drives a rotor to generate lift and thrust. The system includes an electronic speed controller (ESC) to regulate power delivery from the electrical system to the motor.

The class provides methods for:

  • Computing rotor performance (thrust, moment, power)

  • Managing operating conditions

  • Handling system states and residuals

  • Reusing stored performance data for computational efficiency

This propulsor type is commonly used in:

  • Multicopters

  • eVTOL aircraft

  • Hybrid helicopters

Definitions

‘Rotor’

A rotating assembly of airfoils (blades) that generates lift and thrust through aerodynamic forces

‘Electronic Speed Controller (ESC)’

Device that controls the speed of the electric motor by regulating power delivery based on input commands

See also

RCAIDE.Library.Components.Powertrain.Propulsors.Propulsor, RCAIDE.Library.Components.Powertrain.Propulsors.Electric_Ducted_Fan, RCAIDE.Library.Components.Powertrain.Propulsors.Constant_Speed_ICE_Propeller

append_operating_conditions(segment, energy_conditions, noise_conditions=None)[source]#

Appends operating conditions to the segment.

append_propulsor_unknowns_and_residuals(segment)[source]#

Appends propulsor unknowns and residuals to the segment.

unpack_propulsor_unknowns(segment)[source]#

Unpacks propulsor unknowns from the segment.

pack_propulsor_residuals(segment)[source]#

Packs propulsor residuals into the segment.

compute_performance(state, center_of_gravity=[[0, 0, 0]])[source]#

Computes propulsor performance including thrust, moment, and power.

reuse_stored_data(state, network, stored_propulsor_tag=None, center_of_gravity=[[0, 0, 0]])[source]#

Reuses stored propulsor data for performance calculations.