SUAVE.Components.Energy.Processes.Rocket_Thrust.Rocket_Thrust Class Reference

Inheritance diagram for SUAVE.Components.Energy.Processes.Rocket_Thrust.Rocket_Thrust:

Public Member Functions
def	__defaults__ (self)
def	compute (self, conditions)
def	size (self, conditions)

Public Attributes
	tag
	number_of_engines
	mass_flow_rate
	design_thrust
	ISP_design
Public Attributes inherited from SUAVE.Components.Energy.Energy_Component.Energy_Component
	inputs
	outputs
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

A class that handles computation of thrust and ISP for rocket engines

Assumptions:

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

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Processes.Rocket_Thrust.Rocket_Thrust.__defaults__

(

self

)

This sets the default value.

Assumptions:
None

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
N/A

Reimplemented from SUAVE.Components.Energy.Energy_Component.Energy_Component.

compute()

def SUAVE.Components.Energy.Processes.Rocket_Thrust.Rocket_Thrust.compute	(		self,
			conditions
	)

Computes thrust and other properties as below.

Assumptions:
Perfect gas

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

Inputs:
conditions.freestream.
  pressure                           [Pa]
  temperature                        [K]
  gravity                            [-]
conditions.throttle                  [-]
self.inputs.
  propellant_mass_rate               [kg/s]
  combustion_pressure                [Pa]
  expansion_ratio                    [-]
  area_throat                        [m^2]
  exhaust_velocity                   [m/s]
  number_of_engines                  [-]

Outputs:
self.outputs.
  thrust                             [N]
  propellant_mass_flow_rate          [kg/s]
  power                              [W]
  specific_impulse                   [s]
  exhuast_velocity                   [m/s]

Properties Used:

size()

def SUAVE.Components.Energy.Processes.Rocket_Thrust.Rocket_Thrust.size	(		self,
			conditions
	)

Sizes the engine for the design condition.

Assumptions:
Perfect gas

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

Inputs:
conditions.freestream.speed_of_sound [m/s] (conditions is also passed to self.compute(..))
self.inputs.
  bypass_ratio                       [-]
  total_temperature_reference        [K]
  total_pressure_reference           [Pa]
  number_of_engines                  [-]

Outputs:
self.outputs.non_dimensional_thrust  [-]

Properties Used:
self.
  reference_temperature              [K]
  reference_pressure                 [Pa]
  total_design                       [N] - Design thrust

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

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Components/Energy/Processes/Rocket_Thrust.py