Python Data.energies方法代码示例

# 需要导入模块: from SUAVE.Structure import Data [as 别名]
# 或者: from SUAVE.Structure.Data import energies [as 别名]
    def __defaults__(self):
        self.tag = 'Base_Segment'
        
        # --- Segment Inputs
        
        # these are the inputs the user will define in the input script
        
        # an example
        ##self.mach_number = 0.7
        #self.mass_initial     = 'previous_segment' ??
        #self.time_initial     = 'previous_segment'
        #self.position_initial = 'previous_segment'
        
        # --- Vehicle Configuration
        
        # a linked copy of the vehicle
        
        self.config = Data()
        
        
        # --- Conditions and Unknowns
        
        # user shouldn't change these in an input script
        # only used for processing / post processing
        # they will be shared with analysis modules and meaningful naming is important
        
        # base array column lengths
        # use a trivial operation to copy the array
        ones_1col = np.ones([1,1])
        ones_2col = np.ones([1,2])
        ones_3col = np.ones([1,3])         
        
        
        # --- Conditions 
        
        # setup conditions
        conditions = Data()
        conditions.frames   = Data()
        conditions.weights  = Data()
        conditions.energies = Data()   
        self.conditions = conditions
        
        # inertial conditions
        conditions.frames.inertial = Data()        
        conditions.frames.inertial.position_vector      = ones_3col * 0
        conditions.frames.inertial.velocity_vector      = ones_3col * 0
        conditions.frames.inertial.acceleration_vector  = ones_3col * 0
        conditions.frames.inertial.total_force_vector   = ones_3col * 0
        conditions.frames.inertial.time                 = ones_1col * 0
        
        # body conditions
        conditions.frames.body = Data()        
        conditions.frames.body.inertial_rotations       = ones_3col * 0
        conditions.frames.body.transform_to_inertial    = np.empty([0,0,0])
        
        # weights conditions
        conditions.weights.total_mass            = ones_1col * 0
        conditions.weights.weight_breakdown      = Data()
        
        # energy conditions
        conditions.energies.total_energy         = ones_1col * 0
        conditions.energies.total_efficiency     = ones_1col * 0
        
        # --- Unknowns
        
        # setup unknowns
        unknowns = Data()
        unknowns.states   = Data()
        unknowns.controls = Data()
        unknowns.finals   = Data()
        self.unknowns = unknowns
        
        # an example
        ## unknowns.states.gamma = ones_1col + 0

        
        # --- Residuals
         
        # setup unknowns
        residuals = Data()
        residuals.states   = Data()
        residuals.controls = Data()
        residuals.finals   = Data()
        self.residuals = residuals
        
        
        # --- Initial Conditions
        
        # this data structure will hold a copy of the last
        #    rows from the conditions of the last segment
        
        self.initials = Data()
        
        
        # --- Numerics
        
        self.numerics = Data()
        self.numerics.tag = 'Solution Numerical Setup'
        
        # discretization
#.........这里部分代码省略.........

# 需要导入模块: from SUAVE.Structure import Data [as 别名]
# 或者: from SUAVE.Structure.Data import energies [as 别名]
    def __defaults__(self):
        self.tag = 'Aerodynamic Segment'

        # atmosphere and planet
        self.planet     = None
        self.atmosphere = None
        self.start_time = time.gmtime()


        # --- Conditions and Unknowns

        # user shouldn't change these in an input script
        # only used for processing / post processing
        # they will be shared with analysis modules and meaningful naming is important

        # base matricies
        # use a trivial operation to copy the array
        ones_1col = np.ones([1,1])
        ones_2col = np.ones([1,2])
        ones_3col = np.ones([1,3])


        # --- Conditions

        # setup conditions
        conditions = Data()
        conditions.frames       = Data()
        conditions.freestream   = Data()
        conditions.aerodynamics = Data()
        conditions.propulsion   = Data()
        conditions.weights      = Data()
        conditions.energies     = Data()
        self.conditions = conditions

        # inertial frame conditions
        conditions.frames.inertial = Data()
        conditions.frames.inertial.position_vector      = ones_3col * 0
        conditions.frames.inertial.velocity_vector      = ones_3col * 0
        conditions.frames.inertial.acceleration_vector  = ones_3col * 0
        conditions.frames.inertial.gravity_force_vector = ones_3col * 0
        conditions.frames.inertial.total_force_vector   = ones_3col * 0
        conditions.frames.inertial.time                 = ones_1col * 0

        # wind frame conditions
        conditions.frames.wind = Data()
        conditions.frames.wind.body_rotations           = ones_3col * 0   # rotations in [X,Y,Z] -> [phi,theta,psi]
        conditions.frames.wind.velocity_vector          = ones_3col * 0
        conditions.frames.wind.lift_force_vector        = ones_3col * 0
        conditions.frames.wind.drag_force_vector        = ones_3col * 0
        conditions.frames.wind.transform_to_inertial    = np.empty([0,0,0])

        # body frame conditions
        conditions.frames.body = Data()
        conditions.frames.body.inertial_rotations       = ones_3col * 0    # rotations in [X,Y,Z] -> [phi,theta,psi]
        conditions.frames.body.thrust_force_vector      = ones_3col * 0
        conditions.frames.body.transform_to_inertial    = np.empty([0,0,0])

        # planet frame conditions
        conditions.frames.planet = Data()
        conditions.frames.planet.start_time      = None
        conditions.frames.planet.latitude        = ones_1col * 0
        conditions.frames.planet.longitude       = ones_1col * 0

        # freestream conditions
        conditions.freestream.velocity           = ones_1col * 0
        conditions.freestream.mach_number        = ones_1col * 0
        conditions.freestream.pressure           = ones_1col * 0
        conditions.freestream.temperature        = ones_1col * 0
        conditions.freestream.density            = ones_1col * 0
        conditions.freestream.speed_of_sound     = ones_1col * 0
        conditions.freestream.viscosity          = ones_1col * 0
        conditions.freestream.altitude           = ones_1col * 0
        conditions.freestream.gravity            = ones_1col * 0
        conditions.freestream.reynolds_number    = ones_1col * 0
        conditions.freestream.dynamic_pressure   = ones_1col * 0

        # aerodynamics conditions
        conditions.aerodynamics.angle_of_attack  = ones_1col * 0
        conditions.aerodynamics.side_slip_angle  = ones_1col * 0
        conditions.aerodynamics.roll_angle       = ones_1col * 0
        conditions.aerodynamics.lift_coefficient = ones_1col * 0
        conditions.aerodynamics.drag_coefficient = ones_1col * 0
        conditions.aerodynamics.lift_breakdown   = Data()
        conditions.aerodynamics.drag_breakdown   = Data()

        # propulsion conditions
        conditions.propulsion.throttle           = ones_1col * 0
        conditions.propulsion.fuel_mass_rate     = ones_1col * 0
        conditions.propulsion.battery_energy     = ones_1col * 0
        conditions.propulsion.thrust_breakdown   = Data()

        # weights conditions
        conditions.weights.total_mass            = ones_1col * 0
        conditions.weights.weight_breakdown      = Data()

        # energy conditions
        conditions.energies.total_energy         = ones_1col * 0
        conditions.energies.total_efficiency     = ones_1col * 0
        conditions.energies.gravity_energy       = ones_1col * 0
        conditions.energies.propulsion_power     = ones_1col * 0
#.........这里部分代码省略.........