#-------------------------------------------------------------------------------
# Imports
#-------------------------------------------------------------------------------
import RCAIDE
from RCAIDE.Framework.Core import Units
from RCAIDE.Framework.Mission.Common import Results
from RCAIDE.Framework.Mission.Segments.Segment import Segment
import numpy as np
# ------------------------------------------------------------------------------
# Propeller Analysis
# ------------------------------------------------------------------------------
[docs]
def propeller_aerodynamic_analysis(propeller,
velocity_range,
angular_velocity = 2500*Units.rpm,
angle_of_attack = 0,
altitude = 0,
delta_isa =0 ):
# design aircract
electric_rotor = RCAIDE.Library.Components.Powertrain.Propulsors.Electric_Rotor()
electric_rotor.rotor = propeller
# operarting states
ctrl_pts = len(velocity_range)
# Find the operating conditions
atmosphere = RCAIDE.Framework.Analyses.Atmospheric.US_Standard_1976()
atmosphere_conditions = atmosphere.compute_values(propeller.cruise.design_altitude)
segment = Segment()
conditions = Results()
conditions.aerodynamics.angle_of_attack = np.array([[angle_of_attack]])
conditions.freestream.density = atmosphere_conditions.density
conditions.freestream.dynamic_viscosity = atmosphere_conditions.dynamic_viscosity
conditions.freestream.speed_of_sound = atmosphere_conditions.speed_of_sound
conditions.freestream.temperature = atmosphere_conditions.temperature
conditions.frames.planet.true_course = np.zeros((ctrl_pts,3,3))
conditions.frames.planet.true_course[:,0,0] = np.cos(0.0),
conditions.frames.planet.true_course[:,0,1] = - np.sin(0.0)
conditions.frames.planet.true_course[:,1,0] = np.sin(0.0)
conditions.frames.planet.true_course[:,1,1] = np.cos(0.0)
conditions.frames.planet.true_course[:,2,2] = 1
conditions.frames.wind.transform_to_inertial = np.zeros((ctrl_pts,3,3))
conditions.frames.wind.transform_to_inertial[:,0,0] = np.cos(0.0)
conditions.frames.wind.transform_to_inertial[:,0,2] = np.sin(0.0)
conditions.frames.wind.transform_to_inertial[:,1,1] = 1
conditions.frames.wind.transform_to_inertial[:,2,0] = -np.sin(0.0)
conditions.frames.wind.transform_to_inertial[:,2,2] = np.cos(0.0)
conditions.frames.body.transform_to_inertial = np.zeros((ctrl_pts,3,3))
conditions.frames.body.transform_to_inertial[:,0,0] = np.cos(angle_of_attack)
conditions.frames.body.transform_to_inertial[:,0,2] = np.sin(angle_of_attack)
conditions.frames.body.transform_to_inertial[:,1,1] = 1
conditions.frames.body.transform_to_inertial[:,2,0] = -np.sin(angle_of_attack)
conditions.frames.body.transform_to_inertial[:,2,2] = np.cos(angle_of_attack)
segment.state.conditions = conditions
electric_rotor.append_operating_conditions(segment)
for tag, item in electric_rotor.items():
if issubclass(type(item), RCAIDE.Library.Components.Component):
item.append_operating_conditions(segment,electric_rotor)
# Run BEMT
segment.state.conditions.expand_rows(ctrl_pts)
conditions.frames.inertial.velocity_vector = velocity_range
conditions.freestream.mach_number = conditions.frames.inertial.velocity_vector / conditions.freestream.speed_of_sound
rotor_conditions = segment.state.conditions.energy[electric_rotor.tag][propeller.tag]
rotor_conditions.omega = angular_velocity
RCAIDE.Library.Methods.Powertrain.Converters.Rotor.compute_rotor_performance(electric_rotor,segment.state)
results = segment.state.conditions.energy[electric_rotor.tag][propeller.tag]
return results
