SUAVE  2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
SUAVE.Components.Energy.Converters.Rocket_Combustor.Rocket_Combustor Class Reference
Inheritance diagram for SUAVE.Components.Energy.Converters.Rocket_Combustor.Rocket_Combustor:
SUAVE.Components.Energy.Energy_Component.Energy_Component SUAVE.Components.Physical_Component.Physical_Component SUAVE.Components.Component.Component

Public Member Functions

def __defaults__ (self)
 
def compute (self, conditions)
 

Public Attributes

 tag
 
 propellant_data
 
 efficiency
 
- 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

This provides output values for a rocket combustion chamber.
Calling this class calls the compute function.

Assumptions:
None

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

Member Function Documentation

◆ __defaults__()

def SUAVE.Components.Energy.Converters.Rocket_Combustor.Rocket_Combustor.__defaults__ (   self)
This sets the default values for the component to function.

Assumptions:
None

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
None

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

◆ compute()

def SUAVE.Components.Energy.Converters.Rocket_Combustor.Rocket_Combustor.compute (   self,
  conditions 
)
This computes the output values from the input values according to
equations from the source. This function is currently a shell until 
CEA surrogate is include. This functions similiarly to RAM.py at the
moment.

Assumptions:
Combustion happens as M<<<1, assumed to be Mach = 0.
Combustion needs CEA surrogate.

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

Inputs:
self.inputs.
  combustion_pressure           [Pa]

Outputs:
self.outputs.
  combustion_temperature        [K]  
  combustion_pressure           [Pa]
  isentropic_expansion_factor   [-]
  gas_specific_constant         [J/(Kg-K)]

Properties Used:

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