Python Data.tip_radius方法代码示例

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import tip_radius [as 别名]
def main():
    
    # This script could fail if either the design or analysis scripts fail,
    # in case of failure check both. The design and analysis powers will 
    # differ because of karman-tsien compressibility corrections in the 
    # analysis scripts
    
    # Design the Propeller
    prop_attributes = Data()
    prop_attributes.number_blades       = 2.0 
    prop_attributes.freestream_velocity = 50.0
    prop_attributes.angular_velocity    = 2000.*(2.*np.pi/60.0)
    prop_attributes.tip_radius          = 1.5
    prop_attributes.hub_radius          = 0.05
    prop_attributes.design_Cl           = 0.7 
    prop_attributes.design_altitude     = 0.0 * Units.km
    prop_attributes.design_thrust       = 0.0
    prop_attributes.design_power        = 7000.
    prop_attributes                     = propeller_design(prop_attributes)    

    # Find the operating conditions
    atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
    atmosphere_conditions =  atmosphere.compute_values(prop_attributes.design_altitude)
    
    V = prop_attributes.freestream_velocity
    
    conditions = Data()
    conditions.freestream = Data()
    conditions.propulsion = Data()
    conditions.freestream.update(atmosphere_conditions)
    conditions.freestream.dynamic_viscosity = atmosphere_conditions.dynamic_viscosity
    conditions.freestream.velocity = np.array([[V]])
    conditions.propulsion.throttle = np.array([[1.0]])
    
    # Create and attach this propeller
    prop                 = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes = prop_attributes    
    prop.inputs.omega    = prop_attributes.angular_velocity
    
    F, Q, P, Cplast = prop.spin(conditions)
    
    # Truth values
    F_truth      = 166.41590262
    Q_truth      = 45.21732911
    P_truth      = 9470.2952633 # Over 9000!
    Cplast_truth = 0.00085898
    
    error = Data()
    error.Thrust  = np.max(np.abs(F-F_truth))
    error.Power   = np.max(np.abs(P-P_truth))
    error.Torque  = np.max(np.abs(Q-Q_truth))
    error.Cp      = np.max(np.abs(Cplast-Cplast_truth))   
    
    print 'Errors:'
    print  error
    
    for k,v in error.items():
        assert(np.abs(v)<0.001)
     
    return

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import tip_radius [as 别名]

#.........这里部分代码省略.........
    wing.twists.tip              = 0.0 * Units.degrees  
    wing.origin                  = [10.,0.0,0.0] # meters
    wing.aerodynamic_center      = [0.5,0.0,0.0] # meters
    wing.symmetric               = True          
    wing.vertical                = True 
    wing.t_tail                  = False
    wing.dynamic_pressure_ratio  = 1.0
    wing.number_ribs             = 5.
  
    # add to vehicle
    vehicle.append_component(wing)  
    
    #------------------------------------------------------------------
    # Propulsor
    #------------------------------------------------------------------
    
    # build network
    net = Solar()
    net.number_of_engines = 1.
    net.nacelle_diameter  = 0.2 * Units.meters
    net.engine_length     = 0.01 * Units.meters
    net.areas             = Data()
    net.areas.wetted      = 0.01*(2*np.pi*0.01/2.)
    
    # Component 1 the Sun?
    sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
    net.solar_flux = sun
    
    # Component 2 the solar panels
    panel = SUAVE.Components.Energy.Converters.Solar_Panel()
    panel.area                 = vehicle.reference_area * 0.9
    panel.efficiency           = 0.25
    panel.mass_properties.mass = panel.area*(0.60 * Units.kg)
    net.solar_panel            = panel
    
    # Component 3 the ESC
    esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
    esc.efficiency = 0.95 # Gundlach for brushless motors
    net.esc        = esc
    
    # Component 5 the Propeller
    # Design the Propeller
    prop_attributes = Data()
    prop_attributes.number_blades       = 2.0
    prop_attributes.freestream_velocity = 40.0 * Units['m/s']# freestream
    prop_attributes.angular_velocity    = 150. * Units['rpm']
    prop_attributes.tip_radius          = 4.25 * Units.meters
    prop_attributes.hub_radius          = 0.05 * Units.meters
    prop_attributes.design_Cl           = 0.7
    prop_attributes.design_altitude     = 14.0 * Units.km
    prop_attributes.design_thrust       = 0.0 
    prop_attributes.design_power        = 3500.0 * Units.watts
    prop_attributes                     = propeller_design(prop_attributes)
    
    prop = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes = prop_attributes
    net.propeller        = prop

    # Component 4 the Motor
    motor = SUAVE.Components.Energy.Converters.Motor()
    motor.resistance           = 0.008
    motor.no_load_current      = 4.5  * Units.ampere
    motor.speed_constant       = 120. * Units['rpm'] # RPM/volt converted to (rad/s)/volt    
    motor.propeller_radius     = prop.prop_attributes.tip_radius
    motor.propeller_Cp         = prop.prop_attributes.Cp
    motor.gear_ratio           = 12. # Gear ratio
    motor.gearbox_efficiency   = .98 # Gear box efficiency
    motor.expected_current     = 160. # Expected current
    motor.mass_properties.mass = 2.0  * Units.kg
    net.motor                  = motor    
    
    # Component 6 the Payload
    payload = SUAVE.Components.Energy.Peripherals.Payload()
    payload.power_draw           = 50. * Units.watts 
    payload.mass_properties.mass = 5.0 * Units.kg
    net.payload                  = payload
    
    # Component 7 the Avionics
    avionics = SUAVE.Components.Energy.Peripherals.Avionics()
    avionics.power_draw = 50. * Units.watts
    net.avionics        = avionics      

    # Component 8 the Battery
    bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
    bat.mass_properties.mass = 55.0 * Units.kg
    bat.specific_energy      = 450. * Units.Wh/Units.kg
    bat.resistance           = 0.05
    initialize_from_mass(bat,bat.mass_properties.mass)
    net.battery              = bat
   
    #Component 9 the system logic controller and MPPT
    logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
    logic.system_voltage  = 40.0
    logic.MPPT_efficiency = 0.95
    net.solar_logic       = logic
    
    # add the solar network to the vehicle
    vehicle.append_component(net)  

    return vehicle

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import tip_radius [as 别名]
def main():

    # ------------------------------------------------------------------
    #   Propulsor
    # ------------------------------------------------------------------
    
    # build network
    net = Solar()
    net.number_of_engines = 1.
    net.nacelle_dia       = 0.2
    
    # Component 1 the Sun?
    sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
    net.solar_flux = sun
    
    # Component 2 the solar panels
    panel = SUAVE.Components.Energy.Converters.Solar_Panel()
    panel.area                 = 100 * Units.m
    panel.efficiency           = 0.18
    panel.mass_properties.mass = panel.area*.600
    net.solar_panel            = panel
    
    # Component 3 the ESC
    esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
    esc.efficiency = 0.95 # Gundlach for brushless motors
    net.esc       = esc
    
    # Component 5 the Propeller
    
    # Propeller design specs
    design_altitude = 0.0 * Units.km
    Velocity        = 10.0  # freestream m/s
    RPM             = 5887
    Blades          = 2.0
    Radius          = .4064
    Hub_Radius      = 0.05
    Design_Cl       = 0.7
    Thrust          = 0.0 #Specify either thrust or power to design for
    Power           = 7500.  #Specify either thrust or power to design for
    
    # Design the Propeller
    prop_attributes = Data()
    prop_attributes.number_blades       = Blades 
    prop_attributes.freestream_velocity = Velocity
    prop_attributes.angular_velocity    = RPM*(2.*np.pi/60.0)
    prop_attributes.tip_radius          = Radius
    prop_attributes.hub_radius          = Hub_Radius
    prop_attributes.design_Cl           = Design_Cl 
    prop_attributes.design_altitude     = design_altitude
    prop_attributes.design_thrust       = Thrust
    prop_attributes.design_power        = Power
    prop_attributes                     = propeller_design(prop_attributes)
    
    # Create and attach this propeller
    prop                 = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes = prop_attributes
    net.propeller        = prop
    
    # Component 4 the Motor
    motor = SUAVE.Components.Energy.Converters.Motor()
    motor.resistance           = 0.01
    motor.no_load_current      = 8.0
    motor.speed_constant       = 140.*(2.*np.pi/60.) # RPM/volt converted to rad/s     
    motor.propeller_radius     = prop.prop_attributes.tip_radius
    #motor.propeller_Cp         = prop.prop_attributes.Cp
    motor.gear_ratio           = 1.
    motor.gearbox_efficiency   = 1.
    motor.expected_current     = 260.
    motor.mass_properties.mass = 2.0
    net.motor                  = motor   
    
    # Component 6 the Payload
    payload = SUAVE.Components.Energy.Peripherals.Payload()
    payload.power_draw           = 0. #Watts 
    payload.mass_properties.mass = 0. * Units.kg
    net.payload                  = payload
    
    # Component 7 the Avionics
    avionics = SUAVE.Components.Energy.Peripherals.Avionics()
    avionics.power_draw = 0. #Watts  
    net.avionics        = avionics      
    
    # Component 8 the Battery
    bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
    batterymass = 50.  #kg
    bat.type = 'Li-Ion'
    bat.resistance = 0.0
    bat.energy_density = 250.
    initialize_from_mass(bat,batterymass)
    bat.current_energy = bat.max_energy
    net.battery = bat
    
    #Component 9 the system logic controller and MPPT
    logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
    logic.system_voltage  = 50.0
    logic.MPPT_efficiency = 0.95
    net.solar_logic       = logic
    
    # Setup the conditions to run the network
    state            = Data()
#.........这里部分代码省略.........

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import tip_radius [as 别名]
def configs_setup(vehicle):
    
    #---------------------------------------------------------------------------
    # Initialize Configurations
    #---------------------------------------------------------------------------
    
    configs = SUAVE.Components.Configs.Config.Container()
    
    base_config = SUAVE.Components.Configs.Config(vehicle)
    base_config.tag = 'base'
    configs.append(base_config)
    
    #---------------------------------------------------------------------------
    # Electric Helicopter Configuration
    #---------------------------------------------------------------------------
    
    config = SUAVE.Components.Configs.Config(base_config)
    config.tag = 'electric_helicopter'
    
    config.propulsors.network.number_of_engines = 1
    
    prop_attributes = Data()
    prop_attributes.number_blades       = 4.0
    prop_attributes.freestream_velocity = 150.  * Units['meter/second']
    prop_attributes.angular_velocity    = 3500. * Units['rpm']
    prop_attributes.tip_radius          = 3800. * Units.mm
    prop_attributes.hub_radius          = 500.  * Units.mm
    prop_attributes.design_Cl           = 0.7
    prop_attributes.design_altitude     = 1.    * Units.km
    prop_attributes.design_thrust       = 1600. * 9.81 * Units.newtons
    prop_attributes.design_power        = 0.    * Units.watts
    prop_attributes                     = propeller_design(prop_attributes)
       
    prop = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes    = prop_attributes
    prop.origin             = [0.,0.,0.]
    config.propulsors.network.propeller    = prop
    
    configs.append(config)
    
    #---------------------------------------------------------------------------
    # Electric Stopped Rotor Configuration
    #---------------------------------------------------------------------------
    
    config = SUAVE.Components.Configs.Config(base_config)
    config.tag = 'electric_stopped_rotor'
    
    config.propulsors.network.number_of_engines = 8
    
    prop_attributes = Data()
    prop_attributes.number_blades       = 4.0
    prop_attributes.freestream_velocity = 150.  * Units['meter/second']
    prop_attributes.angular_velocity    = 3500. * Units['rpm']
    prop_attributes.tip_radius          = 800.  * Units.mm #608
    prop_attributes.hub_radius          = 150. * Units.mm
    prop_attributes.design_Cl           = 0.7
    prop_attributes.design_altitude     = 1. * Units.km
    prop_attributes.design_thrust       = 200. * 9.81 * Units.newtons
    prop_attributes.design_power        = 0. * Units.watts
    prop_attributes                     = propeller_design(prop_attributes)
       
    prop = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes    = prop_attributes
    prop.origin             = [0.,0.,0.]
    config.propulsors.network.propeller    = prop
    
    thrust_prop_attributes = cp.deepcopy(prop_attributes)
    thrust_prop_attributes.number_blades = 2.0
    thrust_prop = SUAVE.Components.Energy.Converters.Propeller()
    thrust_prop.prop_attributes = thrust_prop_attributes
    config.propulsors.network.thrust_propeller = thrust_prop
    
    configs.append(config)

    #---------------------------------------------------------------------------
    # Electric Tiltrotor Configuration
    #---------------------------------------------------------------------------
    
    config = SUAVE.Components.Configs.Config(base_config)
    config.tag = 'electric_tiltrotor'
    
    config.propulsors.network.number_of_engines = 8
    
    prop_attributes = Data()
    prop_attributes.number_blades       = 4.0
    prop_attributes.freestream_velocity = 150.  * Units['meter/second']
    prop_attributes.angular_velocity    = 3500. * Units['rpm']
    prop_attributes.tip_radius          = 800.  * Units.mm #608
    prop_attributes.hub_radius          = 150.  * Units.mm
    prop_attributes.design_Cl           = 0.7
    prop_attributes.design_altitude     = 1.    * Units.km
    prop_attributes.design_thrust       = 200.  * 9.81 * Units.newtons
    prop_attributes.design_power        = 0.    * Units.watts
    prop_attributes                     = propeller_design(prop_attributes)    
       
    prop = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes    = prop_attributes
    prop.origin             = [0.,0.,0.]
    config.propulsors.network.propeller    = prop
    
#.........这里部分代码省略.........

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import tip_radius [as 别名]

#.........这里部分代码省略.........
    
    #------------------------------------------------------------------
    # Propulsor
    #------------------------------------------------------------------
    
    # build network
    net = Solar_Network()
    net.number_motors    = 1.
    net.nacelle_diameter = 0.2
    
    # Component 1 the Sun?
    sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
    net.solar_flux = sun
    
    # Component 2 the solar panels
    panel = SUAVE.Components.Energy.Converters.Solar_Panel()
    panel.area                 = vehicle.reference_area
    panel.efficiency           = 0.2
    panel.mass_properties.mass = panel.area*0.6
    net.solar_panel            = panel
    
    # Component 3 the ESC
    esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
    esc.efficiency = 0.95 # Gundlach for brushless motors
    net.esc       = esc
    
    # Component 5 the Propeller
    
    # Design the Propeller
    prop_attributes = Data()
    prop_attributes.number_blades       = 2.0
    prop_attributes.freestream_velocity = 50.0 # freestream m/s
    prop_attributes.angular_velocity    = 300.*(2.*np.pi/60.0)
    prop_attributes.tip_radius          = 4.25
    prop_attributes.hub_radius          = 0.0508
    prop_attributes.design_Cl           = 0.7
    prop_attributes.design_altitude     = 23.0 * Units.km
    prop_attributes.design_thrust       = 0.0
    prop_attributes.design_power        = 10000.0
    prop_attributes                     = propeller_design(prop_attributes)
    
    prop = SUAVE.Components.Energy.Converters.Propeller()
    prop.prop_attributes = prop_attributes
    net.propeller        = prop

    # Component 4 the Motor
    motor = SUAVE.Components.Energy.Converters.Motor()
    motor.resistance           = 0.008
    motor.no_load_current      = 4.5
    motor.speed_constant       = 120.*(2.*np.pi/60.) # RPM/volt converted to rad/s     
    motor.propeller_radius     = prop.prop_attributes.tip_radius
    motor.propeller_Cp         = prop.prop_attributes.Cp
    motor.gear_ratio           = 20. # Gear ratio
    motor.gearbox_efficiency   = .98 # Gear box efficiency
    motor.expected_current     = 160. # Expected current
    motor.mass_properties.mass = 2.0
    net.motor                  = motor    
    
    # Component 6 the Payload
    payload = SUAVE.Components.Energy.Peripherals.Payload()
    payload.power_draw           = 100. #Watts 
    payload.mass_properties.mass = 25.0 * Units.kg
    net.payload                  = payload
    
    # Component 7 the Avionics
    avionics = SUAVE.Components.Energy.Peripherals.Avionics()