Python Data.landing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 landing [as 别名]
def shevell(weight_landing, number_of_engines, thrust_sea_level, thrust_landing):

    #process
    baseline_noise    = 101. 
    thrust_percentage = (thrust_sea_level/ Units.force_pound)/25000 * 100.
    thrust_reduction  = thrust_landing/thrust_sea_level * 100.
    
    noise_increase_due_to_thrust = - 0.0002193 * thrust_percentage ** 2. + 0.09454 * thrust_percentage - 7.30116 
    noise_landing                = - 0.0015766 * thrust_reduction ** 2. + 0.34882 * thrust_reduction -19.2569
    
    takeoff_distance_noise  = -4.  # 1500 ft altitude at 6500m from start of take-off
    sideline_distance_noise = -6.5 # 1476 ft (450m) from centerline (effective distance = 1476*1.25 = 1845ft)
    landing_distance_noise  = 9.1  # 370 ft altitude at 6562 ft (2000m) from runway    
    
    takeoff   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. \
        + takeoff_distance_noise + noise_increase_due_to_thrust
    side_line = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. \
        + sideline_distance_noise + noise_increase_due_to_thrust
    landing   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 5. \
        + landing_distance_noise + noise_increase_due_to_thrust + noise_landing
    airframe  = 40. + 10. * np.log10(weight_landing / Units.lbs)
    
    output = Data()
    output.takeoff   = takeoff
    output.side_line = side_line
    output.landing   = 10. * np.log10(10. ** (airframe/10.) + 10. ** (landing/10.))
    
    return output

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import landing [as 别名]
def shevell(weight_landing, number_of_engines, thrust_sea_level, thrust_landing):
    """ This uses correlations from Shevell, also used in AA241A/B, to calculate the sources for noise

    Assumptions:
    None

    Source:
    Stanford AA 241A/B Notes

    Inputs:
    weight_landing     [newtons]
    number_of_engines  [int]
    thrust_sea_level   [newtons]
    thrust_landing     [newtons]
    
    Outputs:
    output.
        takeoff        [float]
        side_line      [float]
        landing        [float]

    Properties Used:
    baseline noise = 101.
    various tuned correlations
    """         
    
    

    #process
    baseline_noise    = 101. 
    thrust_percentage = (thrust_sea_level/ Units.force_pound)/25000 * 100.
    thrust_reduction  = thrust_landing/thrust_sea_level * 100.
    
    noise_increase_due_to_thrust = - 0.0002193 * thrust_percentage ** 2. + 0.09454 * thrust_percentage - 7.30116 
    noise_landing                = - 0.0015766 * thrust_reduction ** 2. + 0.34882 * thrust_reduction -19.2569
    
    takeoff_distance_noise  = -4.  # 1500 ft altitude at 6500m from start of take-off
    sideline_distance_noise = -6.5 # 1476 ft (450m) from centerline (effective distance = 1476*1.25 = 1845ft)
    landing_distance_noise  = 9.1  # 370 ft altitude at 6562 ft (2000m) from runway    
    
    takeoff   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. \
        + takeoff_distance_noise + noise_increase_due_to_thrust
    side_line = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. \
        + sideline_distance_noise + noise_increase_due_to_thrust
    landing   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 5. \
        + landing_distance_noise + noise_increase_due_to_thrust + noise_landing
    airframe  = 40. + 10. * np.log10(weight_landing / Units.lbs)
    
    output = Data()
    output.takeoff   = takeoff
    output.side_line = side_line
    output.landing   = 10. * np.log10(10. ** (airframe/10.) + 10. ** (landing/10.))
    
    return output

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

    weight_landing    = 300000 * Units.lbs
    number_of_engines = 3.
    thrust_sea_level  = 40000 * Units.force_pounds
    thrust_landing    = 0.45 * thrust_sea_level
    
    noise = Correlations.shevell(weight_landing, number_of_engines, thrust_sea_level, thrust_landing)
    
    actual = Data()
    actual.takeoff = 99.7
    actual.side_line = 97.2
    actual.landing = 105.2
    
    error = Data()
    error.takeoff = (actual.takeoff - noise.takeoff)/actual.takeoff
    error.side_line = (actual.side_line - noise.side_line)/actual.side_line
    error.landing = (actual.landing - noise.landing)/actual.landing
    
    for k,v in error.items():
        assert(np.abs(v)<0.005)
        
    return

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import landing [as 别名]
def shevell(weight_landing, number_of_engines, thrust_sea_level, thrust_landing):
    """ weight = SUAVE.Methods.Noise.Correlations.shevell(weight_landing, number_of_engines, thrust_sea_level, thrust_landing)
                
        Inputs: 
            weight_landing - Landing weight of the aircraft [kilograms]
            number of engines - Number of engines installed on the aircraft [Dimensionless]
            thrust_sea_level - Sea Level Thrust of the Engine [Newtons]
            thrust_landing - Thrust of the aircraft coming in for landing [Newtons]
        
        Outputs:
            output() - Data Class
                takeoff - Noise of the aircraft at takeoff directly along the runway centerline  (500 ft altitude at 6500m from start of take-off) [dB]
                side_line - Noise of the aircraft at takeoff at the sideline measurement station (1,476 ft (450m) from centerline (effective distance = 1476*1.25 = 1845ft)[dB]
                landing - Noise of the aircraft at landing directly along the trajectory (370 ft altitude at 6562 ft (2000m) from runway) [dB]
            
        Assumptions:
        The baseline case used is 101 PNdb, 25,000 lb thrust, 1 engine, 1000ft
        The noise_increase_due_to_thrust and noise_landing are equation extracted from images. 
        This is only meant to give a rough estimate compared to a DC-10 aircraft. As the aircraft configuration varies from this configuration, the validity of the method will also degrade.     
    """ 
    
    #process
    baseline_noise  = 101 
    thrust_percentage = (thrust_sea_level/ Units.force_pound)/25000 * 100.
    thrust_reduction  = thrust_landing/thrust_sea_level * 100.
    noise_increase_due_to_thrust = -0.0002193 * thrust_percentage ** 2. + 0.09454 * thrust_percentage - 7.30116 
    noise_landing = - 0.0015766 * thrust_reduction ** 2. + 0.34882 * thrust_reduction -19.2569
    takeoff_distance_noise = -4. # 1500 ft altitude at 6500m from start of take-off
    sideline_distance_noise = -6.5 #1 476 ft (450m) from centerline (effective distance = 1476*1.25 = 1845ft)
    landing_distance_noise = 9.1 # 370 ft altitude at 6562 ft (2000m) from runway    
    
    takeoff   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. + takeoff_distance_noise + noise_increase_due_to_thrust
    side_line = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. + sideline_distance_noise + noise_increase_due_to_thrust
    landing   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 5. + landing_distance_noise + noise_increase_due_to_thrust + noise_landing
    airframe  = 40. + 10. * np.log10(weight_landing / Units.lbs)
    
    output = Data()
    output.takeoff   = takeoff
    output.side_line = side_line
    output.landing   = 10. * np.log10(10. ** (airframe/10.) + 10. ** (landing/10.))
    
    return output

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import landing [as 别名]
def evaluate_field_length(vehicle,mission,results):
    
    # unpack
    airport = mission.airport
    
    takeoff_config = vehicle.configs.takeoff
    landing_config = vehicle.configs.landing
    
    from SUAVE.Methods.Performance import estimate_take_off_field_length
    from SUAVE.Methods.Performance import estimate_landing_field_length    
    
    # evaluate
    TOFL = estimate_take_off_field_length(vehicle,takeoff_config,airport)
    LFL = estimate_landing_field_length(vehicle,landing_config,airport)
    
    # pack
    field_length = Data()
    field_length.takeoff = TOFL[0]
    field_length.landing = LFL[0]
    
    results.field_length = field_length
    
    return results

# 需要导入模块: from SUAVE.Core import Data [as 别名]
# 或者: from SUAVE.Core.Data import landing [as 别名]
def extrapolation(weight_landing, number_of_engines, thrust_sea_level, thrust_landing):
    """ weight = SUAVE.Methods.Weights.Correlations.Tube_Wing.landing_gear(TOW)
                
        
        Inputs:
            
        
        Outputs:
            
            
        Assumptions:
        The baseline case is 101 PNdb, 25,000 lb thrust, 1 engine, 1000ft
             
    """ 
    
    #process
    baseline_noise  = 101 
    thrust_percentage = (thrust_sea_level/ Units.force_pound)/25000 * 100.
    thrust_reduction  = thrust_landing/thrust_sea_level * 100.
    noise_increase_due_to_thrust = -0.0002193 * thrust_percentage ** 2. + 0.09454 * thrust_percentage - 7.30116 
    noise_landing = - 0.0015766 * thrust_reduction ** 2. + 0.34882 * thrust_reduction -19.2569
    takeoff_distance_noise = -4. # 1500 ft altitude at 6500m from start of take-off
    sideline_distance_noise = -6.5 #1 476 ft (450m) from centerline (effective distance = 1476*1.25 = 1845ft)
    landing_distance_noise = 9.1 # 370 ft altitude at 6562 ft (2000m) from runway    
    
    takeoff   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. + takeoff_distance_noise + noise_increase_due_to_thrust
    side_line = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 4. + sideline_distance_noise + noise_increase_due_to_thrust
    landing   = 10. * np.log10(10. ** (baseline_noise/10.) * number_of_engines) - 5. + landing_distance_noise + noise_increase_due_to_thrust + noise_landing
    airframe  = 40. + 10. * np.log10(weight_landing)
    
    output = Data()
    output.takeoff   = takeoff
    output.side_line = side_line
    output.landing   = 10. * np.log10(10. ** (airframe/10.) + 10. ** (landing/10.))
    
    return output