Source code for RCAIDE.Framework.Analyses.Stability.Vortex_Lattice_Method
# RCAIDE/Framework/Analyses/Stability/Vortex_Lattice_Method.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from RCAIDE.Framework.Core import Data, Units
from RCAIDE.Framework.Analyses import Process
from RCAIDE.Library.Methods.Aerodynamics import Common
from .Stability import Stability
from RCAIDE.Framework.Analyses.Common.Process_Geometry import Process_Geometry
from RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method import *
# package imports
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Vortex_Lattice_Method
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Vortex_Lattice_Method(Stability):
"""This is a subsonic aerodynamic buildup analysis based on the vortex lattice method
Assumptions:
Stall effects are negligible
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
def __defaults__(self):
"""This sets the default values and methods for the analysis.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.tag = 'Vortex_Lattice_Method'
self.vehicle = Data()
self.process = Process()
self.process.initialize = Process()
# correction factors
self.settings.fuselage_lift_correction = 1.14
self.settings.trim_drag_correction_factor = 1.1
self.settings.wing_parasite_drag_form_factor = 1.2
self.settings.fuselage_parasite_drag_form_factor = 2.4
self.settings.drag_reduction_factors = Data()
self.settings.drag_reduction_factors.parasite_drag = 0.0 # Reduction factors are proportional (.1 is a 10% weight reduction)
self.settings.drag_reduction_factors.induced_drag = 0.0 # Reduction factors are proportional (.1 is a 10% weight reduction)
self.settings.drag_reduction_factors.compressibility_drag = 0.0 # Reduction factors are proportional (.1 is a 10% weight reduction)
self.settings.maximum_lift_coefficient_factor = 1.0
self.settings.lift_to_drag_adjustment = 0.0
self.settings.oswald_efficiency_factor = None
self.settings.span_efficiency = None
self.settings.viscous_lift_dependent_drag_factor = 0.38
self.settings.drag_coefficient_increment = 0.0
self.settings.spoiler_drag_increment = 0.0
self.settings.maximum_lift_coefficient = np.inf
self.settings.use_surrogate = True
self.settings.recalculate_total_wetted_area = False
self.settings.propeller_wake_model = False
self.settings.discretize_control_surfaces = True
self.settings.model_fuselage = False
self.settings.trim_aircraft = True
self.settings.aileron_flag = False
self.settings.rudder_flag = False
self.settings.flap_flag = False
self.settings.elevator_flag = False
self.settings.slat_flag = False
# correction factors
self.settings.supersonic = Data()
self.settings.supersonic.peak_mach_number = 1.04
self.settings.supersonic.begin_drag_rise_mach_number = 0.95
self.settings.supersonic.end_drag_rise_mach_number = 1.2
self.settings.supersonic.transonic_drag_multiplier = 1.25
self.settings.supersonic.volume_wave_drag_scaling = 3.2
self.settings.supersonic.fuselage_parasite_drag_begin_blend_mach = 0.91
self.settings.supersonic.fuselage_parasite_drag_end_blend_mach = 0.99
self.settings.supersonic.cross_sectional_area_calculation_type = 'Fixed'
self.settings.supersonic.wave_drag_type = 'Raymer'
self.settings.number_of_spanwise_vortices = 15
self.settings.number_of_chordwise_vortices = 5
self.settings.wing_spanwise_vortices = None
self.settings.wing_chordwise_vortices = None
self.settings.fuselage_spanwise_vortices = None
self.settings.fuselage_chordwise_vortices = None
self.settings.spanwise_cosine_spacing = True
self.settings.vortex_distribution = Data()
self.settings.leading_edge_suction_multiplier = 1.0
self.settings.use_VORLAX_matrix_calculation = False
self.settings.floating_point_precision = np.float32
# conditions table, used for surrogate model training
self.training = Data()
self.training.angle_of_attack = np.array([-5., -2. , 1E-20 , 2.0, 5.0, 8.0, 12., 45., 75.]) * Units.deg
self.training.Mach = np.array([0.1 ,0.3, 0.5, 0.65 , 0.85 , 0.9, 1.3, 1.35 , 1.5 , 2.0, 2.25 , 2.5 , 3.5])
self.training.subsonic = None
self.training.supersonic = None
self.training.transonic = None
self.training.altitude = 0
self.training.speed_of_sound = 343
self.training.angle_purtubation = 10 * Units.deg
self.training.speed_purtubation = 5
self.training.rate_purtubation = 10 * Units.deg / Units.sec
self.training.control_surface_purtubation = 10 * Units.deg
self.training.sideslip_angle = np.array([10 , 5.0 ]) * Units.deg
self.training.aileron_deflection = np.array([10 , 5.0 ]) * Units.deg
self.training.elevator_deflection = np.array([10 , 5.0 ]) * Units.deg
self.training.rudder_deflection = np.array([10 , 1E-3 ]) * Units.deg
self.training.flap_deflection = np.array([10 , 1E-3 ]) * Units.deg
self.training.slat_deflection = np.array([10 , 1E-3 ]) * Units.deg
self.training.u = np.array([10 , 5 ])
self.training.v = np.array([10 , 5 ])
self.training.w = np.array([10 , 5 ])
self.training.pitch_rate = np.array([3 ,1.5 ]) * Units.deg / Units.sec
self.training.roll_rate = np.array([3 ,1.5 ]) * Units.deg / Units.sec
self.training.yaw_rate = np.array([3 ,1.5 ]) * Units.deg / Units.sec
self.reference_values = Data()
self.reference_values.S_ref = 0
self.reference_values.c_ref = 0
self.reference_values.b_ref = 0
self.reference_values.X_ref = 0
self.reference_values.Y_ref = 0
self.reference_values.Z_ref = 0
# control surface flags
self.aileron_flag = False
self.flap_flag = False
self.rudder_flag = False
self.elevator_flag = False
self.slat_flag = False
# blending function
self.hsub_min = 0.85
self.hsub_max = 0.95
self.hsup_min = 1.05
self.hsup_max = 1.15
# surrogoate models
self.surrogates = Data()
# build the evaluation process
compute = Process()
compute.lift = Process()
compute.lift.inviscid_wings = None
compute.lift.fuselage = Common.Lift.fuselage_correction
compute.drag = Process()
compute.drag.parasite = Process()
compute.drag.parasite.wings = Process_Geometry('wings')
compute.drag.parasite.wings.wing = Common.Drag.parasite_drag_wing
compute.drag.parasite.fuselages = Process_Geometry('fuselages')
compute.drag.parasite.fuselages.fuselage = Common.Drag.parasite_drag_fuselage
compute.drag.parasite.booms = Process_Geometry('booms')
compute.drag.parasite.booms.boom = Common.Drag.parasite_drag_fuselage
compute.drag.parasite.nacelles = Common.Drag.parasite_drag_nacelle
compute.drag.parasite.pylons = Common.Drag.parasite_drag_pylon
compute.drag.parasite.total = Common.Drag.parasite_total
compute.drag.induced = Common.Drag.induced_drag
compute.drag.cooling = Process()
compute.drag.cooling.total = Common.Drag.cooling_drag
compute.drag.compressibility = Process()
compute.drag.compressibility.total = Common.Drag.compressibility_drag
compute.drag.miscellaneous = Common.Drag.miscellaneous_drag
compute.drag.spoiler = Common.Drag.spoiler_drag
compute.drag.total = Common.Drag.total_drag
compute.stability = Process()
compute.stability.dynamic_modes = RCAIDE.Library.Methods.Stability.compute_dynamic_flight_modes
self.process.compute = compute
[docs]
def initialize(self):
use_surrogate = self.settings.use_surrogate
# If we are using the surrogate
if use_surrogate == True:
# sample training data
train_VLM_surrogates(self)
# build surrogate
build_VLM_surrogates(self)
# build the evaluation process
compute = self.process.compute
if use_surrogate == True:
compute.lift.inviscid_wings = evaluate_surrogate
else:
compute.lift.inviscid_wings = evaluate_no_surrogate
return
[docs]
def evaluate(self,state):
"""The default evaluate function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
results <RCAIDE data class>
Properties Used:
self.settings
self.vehicle
"""
settings = self.settings
vehicle = self.vehicle
results = self.process.compute(state,settings,vehicle)
return results
