SUAVE.Components.Energy.Converters.Rotor.Rotor Class Reference

Inheritance diagram for SUAVE.Components.Energy.Converters.Rotor.Rotor:

Public Member Functions
def	__defaults__ (self)
def	spin (self, conditions)
def	vec_to_vel (self)
def	body_to_prop_vel (self)
def	prop_vel_to_body (self)
def	vec_to_prop_body (self)

Public Attributes
	tag
	number_of_blades
	tip_radius
	hub_radius
	twist_distribution
	sweep_distribution
	chord_distribution
	thickness_to_chord
	blade_solidity
	design_power
	design_thrust
	airfoil_geometry
	airfoil_polars
	airfoil_polar_stations
	radius_distribution
	rotation
	orientation_euler_angles
	ducted
	number_azimuthal_stations
	vtk_airfoil_points
	induced_power_factor
	profile_drag_coefficient
	use_2d_analysis
	nonuniform_freestream
	axial_velocities_2d
	tangential_velocities_2d
	radial_velocities_2d
	start_angle
	variable_pitch
	Wake
	azimuthal_distribution
	outputs
Public Attributes inherited from SUAVE.Components.Energy.Energy_Component.Energy_Component
	inputs
	outputs
Public Attributes inherited from SUAVE.Components.Physical_Component.Physical_Component
	tag
	mass_properties
	origin
	symmetric
Public Attributes inherited from SUAVE.Components.Component.Component
	tag
	origin
	generative_design_max_per_vehicle
	generative_design_characteristics
	generative_design_special_parent

Detailed Description

This is a general rotor component.

Assumptions:
None

Source:
None

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Converters.Rotor.Rotor.__defaults__

(

self

)

This sets the default values for the component to function.

Assumptions:
None

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
None

Reimplemented from SUAVE.Components.Energy.Energy_Component.Energy_Component.

Reimplemented in SUAVE.Components.Energy.Converters.Lift_Rotor.Lift_Rotor, and SUAVE.Components.Energy.Converters.Propeller.Propeller.

body_to_prop_vel()

def SUAVE.Components.Energy.Converters.Rotor.Rotor.body_to_prop_vel

(

self

)

This rotates from the systems body frame to the propellers velocity frame

Assumptions:
There are two propeller frames, the vehicle frame describing the location and the propeller velocity frame
velocity frame is X out the nose, Z towards the ground, and Y out the right wing
vehicle frame is X towards the tail, Z towards the ceiling, and Y out the right wing

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
None

prop_vel_to_body()

def SUAVE.Components.Energy.Converters.Rotor.Rotor.prop_vel_to_body

(

self

)

This rotates from the propeller's velocity frame to the system's body frame

Assumptions:
There are two propeller frames, the vehicle frame describing the location and the propeller velocity frame
velocity frame is X out the nose, Z towards the ground, and Y out the right wing
vehicle frame is X towards the tail, Z towards the ceiling, and Y out the right wing

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
None

spin()

def SUAVE.Components.Energy.Converters.Rotor.Rotor.spin	(		self,
			conditions
	)

Analyzes a general rotor given geometry and operating conditions.

Assumptions:
per source

Source:
Drela, M. "Qprop Formulation", MIT AeroAstro, June 2006
http://web.mit.edu/drela/Public/web/qprop/qprop_theory.pdf

Leishman, Gordon J. Principles of helicopter aerodynamics
Cambridge university press, 2006.

Inputs:
self.inputs.omega                    [radian/s]
conditions.freestream.
  density                            [kg/m^3]
  dynamic_viscosity                  [kg/(m-s)]
  speed_of_sound                     [m/s]
  temperature                        [K]
conditions.frames.
  body.transform_to_inertial         (rotation matrix)
  inertial.velocity_vector           [m/s]
conditions.propulsion.
  throttle                           [-]

Outputs:
conditions.propulsion.outputs.
   number_radial_stations            [-]
   number_azimuthal_stations         [-]
   disc_radial_distribution          [m]
   speed_of_sound                    [m/s]
   density                           [kg/m-3]
   velocity                          [m/s]
   disc_tangential_induced_velocity  [m/s]
   disc_axial_induced_velocity       [m/s]
   disc_tangential_velocity          [m/s]
   disc_axial_velocity               [m/s]
   drag_coefficient                  [-]
   lift_coefficient                  [-]
   omega                             [rad/s]
   disc_circulation                  [-]
   blade_dQ_dR                       [N/m]
   blade_dT_dr                       [N]
   blade_thrust_distribution         [N]
   disc_thrust_distribution          [N]
   thrust_per_blade                  [N]
   thrust_coefficient                [-]
   azimuthal_distribution            [rad]
   disc_azimuthal_distribution       [rad]
   blade_dQ_dR                       [N]
   blade_dQ_dr                       [Nm]
   blade_torque_distribution         [Nm]
   disc_torque_distribution          [Nm]
   torque_per_blade                  [Nm]
   torque_coefficient                [-]
   power                             [W]
   power_coefficient                 [-]

Properties Used:
self.
  number_of_blades                   [-]
  tip_radius                         [m]
  twist_distribution                 [radians]
  chord_distribution                 [m]
  orientation_euler_angles           [rad, rad, rad]

vec_to_vel()

def SUAVE.Components.Energy.Converters.Rotor.Rotor.vec_to_vel

(

self

)

This rotates from the propellers vehicle frame to the propellers velocity frame

Assumptions:
There are two propeller frames, the vehicle frame describing the location and the propeller velocity frame
velocity frame is X out the nose, Z towards the ground, and Y out the right wing
vehicle frame is X towards the tail, Z towards the ceiling, and Y out the right wing

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
None

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The documentation for this class was generated from the following file:

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Components/Energy/Converters/Rotor.py