SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise Class Reference

Inheritance diagram for SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise:

Public Member Functions
def	__defaults__ (self)
def	evaluate_thrust (self, state)
def	unpack_unknowns_transition (self, segment)
def	unpack_unknowns_cruise (self, segment)
def	unpack_unknowns_lift (self, segment)
def	residuals_transition (self, segment)
def	residuals_cruise (self, segment)
def	residuals_lift (self, segment)
def	add_transition_unknowns_and_residuals_to_segment (self, segment, initial_voltage=None, initial_prop_power_coefficient=0.005, initial_lift_rotor_power_coefficient=0.005, initial_throttle_lift=0.9, initial_battery_cell_temperature=283., initial_battery_state_of_charge=0.5, initial_battery_cell_current=5.)
def	add_cruise_unknowns_and_residuals_to_segment (self, segment, initial_voltage=None, initial_prop_power_coefficient=0.005, initial_battery_cell_temperature=283., initial_battery_state_of_charge=0.5, initial_battery_cell_current=5.)
def	add_lift_unknowns_and_residuals_to_segment (self, segment, initial_voltage=None, initial_lift_rotor_power_coefficient=0.005, initial_throttle_lift=0.9, initial_battery_cell_temperature=283., initial_battery_state_of_charge=0.5, initial_battery_cell_current=5.)

Public Attributes
	lift_rotor_motors
	propeller_motors
	lift_rotors
	propellers
	lift_rotor_esc
	propeller_esc
	avionics
	payload
	battery
	lift_rotor_engine_length
	propeller_engine_length
	number_of_lift_rotor_engines
	number_of_propeller_engines
	voltage
	tag
	generative_design_minimum
	identical_propellers
	identical_lift_rotors
Public Attributes inherited from SUAVE.Components.Energy.Networks.Network.Network
	tag
	generative_design_max_per_vehicle
	non_dimensional_origin
	number_of_engines
	engine_length
	wing_mounted
	areas
Public Attributes inherited from SUAVE.Components.Physical_Component.Physical_Component
	tag
	mass_properties
	origin
	symmetric
Public Attributes inherited from SUAVE.Components.Component.Component
	tag
	origin
	generative_design_max_per_vehicle
	generative_design_characteristics
	generative_design_special_parent

Detailed Description

This is a complex version of battery_propeller with a battery powering propellers through
    electric motors. In this case we have 2 sets of motors at different motors that can be controlled seperately
    
    This network adds 2 extra unknowns to the mission. The first is
    a voltage, to calculate the thevenin voltage drop in the pack.
    The second is torque matching between motor and propeller.
    
    We have two inputs, the forward throttle and the lift throttle setting
    Since this is an airplane first and foremost, the "throttle" will be for forward thrust
    The new unknown will be for lift throttle, because of the assumption on throttle something needs to be done...
    Want only 1 residual on voltage

    Assumptions:
    For any segment using this, body angle can't be an unknown.
    
    Source:
    None

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.__defaults__

(

self

)

This sets the default values for the network to function.
    
    Assumptions:
    None
    
    Source:
    N/A
    
    Inputs:
    None
    
    Outputs:
    None
    
    Properties Used:
    N/A

Reimplemented from SUAVE.Components.Energy.Networks.Network.Network.

add_cruise_unknowns_and_residuals_to_segment()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.add_cruise_unknowns_and_residuals_to_segment	(		self,
			segment,
			initial_voltage = None,
			initial_prop_power_coefficient = 0.005,
			initial_battery_cell_temperature = 283.,
			initial_battery_state_of_charge = 0.5,
			initial_battery_cell_current = 5.
	)

This function sets up the information that the mission needs to run a mission segment using this network
    
    Assumptions:
    None
    
    Source:
    N/A
    
    Inputs:
    segment
    initial_voltage                   [v]
    initial_power_coefficient         [float]s
    
    Outputs:
    segment.state.unknowns.battery_voltage_under_load
    segment.state.unknowns.propeller_power_coefficient
    segment.state.conditions.propulsion.propeller_motor_torque
    segment.state.conditions.propulsion.propeller_torque   
    
    Properties Used:
    N/A

add_lift_unknowns_and_residuals_to_segment()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.add_lift_unknowns_and_residuals_to_segment	(		self,
			segment,
			initial_voltage = None,
			initial_lift_rotor_power_coefficient = 0.005,
			initial_throttle_lift = 0.9,
			initial_battery_cell_temperature = 283.,
			initial_battery_state_of_charge = 0.5,
			initial_battery_cell_current = 5.
	)

This function sets up the information that the mission needs to run a mission segment using this network

    Assumptions:
    None

    Source:
    N/A

    Inputs:
    segment
    initial_voltage                   [v]
    initial_power_coefficient         [float]s

    Outputs:
    segment.state.unknowns.battery_voltage_under_load
    segment.state.unknowns.propeller_power_coefficient
    segment.state.conditions.propulsion.propeller_motor_torque
    segment.state.conditions.propulsion.propeller_torque   

    Properties Used:
    N/A

add_transition_unknowns_and_residuals_to_segment()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.add_transition_unknowns_and_residuals_to_segment	(		self,
			segment,
			initial_voltage = None,
			initial_prop_power_coefficient = 0.005,
			initial_lift_rotor_power_coefficient = 0.005,
			initial_throttle_lift = 0.9,
			initial_battery_cell_temperature = 283.,
			initial_battery_state_of_charge = 0.5,
			initial_battery_cell_current = 5.
	)

This function sets up the information that the mission needs to run a mission segment using this network
    
    Assumptions:
    None
    
    Source:
    N/A
    
    Inputs:
    segment
    initial_voltage                   [v]
    initial_power_coefficient         [float]s
    
    Outputs:
    segment.state.unknowns.battery_voltage_under_load
    segment.state.unknowns.propeller_power_coefficient
    segment.state.conditions.propulsion.propeller_motor_torque
    segment.state.conditions.propulsion.propeller_torque   
    
    Properties Used:
    N/A

evaluate_thrust()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.evaluate_thrust	(		self,
			state
	)

Calculate thrust given the current state of the vehicle
    
    Assumptions:
    Caps the throttle at 110% and linearly interpolates thrust off that
    
    Source:
    N/A
    
    Inputs:
    state [state()]
    
    Outputs:
    results.thrust_force_vector       [Newtons]
    results.vehicle_mass_rate         [kg/s]
    conditions.propulsion:
lift_rotor_rpm                [radians/sec]
rpm _forward                  [radians/sec]
lift_rotor_current_draw       [amps]
propeller_current_draw        [amps]
battery_power_draw            [watts]
battery_energy                [joules]
voltage_open_circuit          [volts]
voltage_under_load            [volts]
lift_rotor_motor_torque       [N-M]
propeller_motor_torque        [N-M]
lift_rotor_thrust             [N]
propeller_thrust              [N]
lift_rotor_torque             [N-M]
propeller_torque              [N-M]
    
    Properties Used:
    Defaulted values

residuals_cruise()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.residuals_cruise	(		self,
			segment
	)

This packs the residuals to be sent to the mission solver.
    Use this if only the forward motors are operational
    
    Assumptions:
    Only the forward motors are operational
    
    Source:
    N/A
    
    Inputs:
    state.conditions.propulsion:
propeller_motor_torque                [N-m]
lift_rotor_motor_torque               [N-m]
propeller_torque                      [N-m]
lift_rotor_torque                     [N-m]
voltage_under_load                    [volts]
    state.unknowns.battery_voltage_under_load [volts]
    
    Outputs:
    None
    
    Properties Used:
    self.voltage                              [volts]

residuals_lift()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.residuals_lift	(		self,
			segment
	)

This packs the residuals to be sent to the mission solver.
    Only the lift motors are operational
    
    Assumptions:
    The lift motors are operational
    
    Source:
    N/A
    
    Inputs:
    state.conditions.propulsion:
propeller_motor_torque                [N-m]
lift_rotor_motor_torque               [N-m]
propeller_torque                      [N-m]
lift_rotor_torque                     [N-m]
voltage_under_load                    [volts]
    state.unknowns.battery_voltage_under_load [volts]
    
    Outputs:
    None
    
    Properties Used:
    self.voltage                              [volts]

residuals_transition()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.residuals_transition	(		self,
			segment
	)

This packs the residuals to be sent to the mission solver.
    Use this if all motors are operational
    
    Assumptions:
    All motors are operational
    
    Source:
    N/A
    
    Inputs:
    state.conditions.propulsion:
propeller_motor_torque                [N-m]
lift_rotor_motor_torque               [N-m]
propeller_torque                      [N-m]
lift_rotor_torque                     [N-m]
voltage_under_load                    [volts]
    state.unknowns.battery_voltage_under_load [volts]
    
    Outputs:
    None
    
    Properties Used:
    self.voltage                              [volts]

unpack_unknowns_cruise()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.unpack_unknowns_cruise	(		self,
			segment
	)

This is an extra set of unknowns which are unpacked from the mission solver and send to the network.
    This uses only the forward motors and turns the rest off.
    
    Assumptions:
    Only the forward motors and turns the rest off.
    
    Source:
    N/A
    
    Inputs:
    state.unknowns.propeller_power_coefficient [None]
    state.unknowns.battery_voltage_under_load  [volts]
    state.unknowns.throttle_lift               [0-1]
    state.unknowns.throttle                    [0-1]
    
    Outputs:
    state.conditions.propulsion.propeller_power_coefficient [None]
    state.conditions.propulsion.battery_voltage_under_load  [volts]
    state.conditions.propulsion.throttle_lift               [0-1]
    state.conditions.propulsion.throttle                    [0-1]
    
    Properties Used:
    N/A

unpack_unknowns_lift()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.unpack_unknowns_lift	(		self,
			segment
	)

This is an extra set of unknowns which are unpacked from the mission solver and send to the network.
    This uses only the lift motors.
    
    Assumptions:
    Only the lift motors.
    
    Source:
    N/A
    
    Inputs:
    state.unknowns.propeller_power_coefficient [None]
    state.unknowns.battery_voltage_under_load  [volts]
    state.unknowns.throttle_lift               [0-1]
    state.unknowns.throttle                    [0-1]
    
    Outputs:
    state.conditions.propulsion.propeller_power_coefficient [None]
    state.conditions.propulsion.battery_voltage_under_load  [volts]
    state.conditions.propulsion.throttle_lift               [0-1]
    state.conditions.propulsion.throttle                    [0-1]
    
    Properties Used:
    N/A

unpack_unknowns_transition()

def SUAVE.Components.Energy.Networks.Lift_Cruise.Lift_Cruise.unpack_unknowns_transition	(		self,
			segment
	)

This is an extra set of unknowns which are unpacked from the mission solver and sent to the network.
    This uses all the motors.
    
    Assumptions:
    None
    
    Source:
    N/A
    
    Inputs:
    state.unknowns.lift_rotor_power_coefficient [None]
    state.unknowns.propeller_power_coefficient  [None]
    state.unknowns.battery_voltage_under_load   [volts]
    state.unknowns.throttle_lift                [0-1]
    state.unknowns.throttle                     [0-1]
    
    Outputs:
    state.conditions.propulsion.lift_rotor_power_coefficient [None]
    state.conditions.propulsion.propeller_power_coefficient  [None]
    state.conditions.propulsion.battery_voltage_under_load   [volts]
    state.conditions.propulsion.throttle_lift                [0-1]
    state.conditions.propulsion.throttle                     [0-1]
    
    Properties Used:
    N/A

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The documentation for this class was generated from the following file:

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Components/Energy/Networks/Lift_Cruise.py