SUAVE.Components.Energy.Networks.Liquid_Rocket.Liquid_Rocket Class Reference

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

Public Member Functions
def	__defaults__ (self)
def	evaluate_thrust (self, state)
def	size (self, state)

Public Attributes
	tag
	number_of_engines
	engine_length
	areas
	internal
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 sets up the equations for a liquid rocket.

    Assumptions:
    Quasi 1-D flow
    Adiabatic Nozzles
    Throat Always Choked

    Source:
    Chapter 7
    https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Networks.Liquid_Rocket.Liquid_Rocket.__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.

evaluate_thrust()

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

Calculate thrust given the current state of the vehicle

    Assumptions:
    None

    Source:
    N/A

    Inputs:
    state [state()]

    Outputs:
    results.thrust_force_vector                      [newtons]
    results.vehicle_mass_rate                        [kg/s]
    results.specific_impulse                         [s]
    conditions.noise.sources.liquid_rocket:
core:
exit_static_temperature                  [K]
exit_static_pressure                     [K]
exit_stagnation_temperature              [K]
exit_stagnation_pressure                 [Pa]
exit_velocity                            [m/s]

    Properties Used:
    Defaulted values

size()

def SUAVE.Components.Energy.Networks.Liquid_Rocket.Liquid_Rocket.size	(		self,
			state
	)

Size the ramjet

    Assumptions:
    None

    Source:
    N/A

    Inputs:
    State [state()]

    Outputs:
    None

    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/Liquid_Rocket.py