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 | |
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/
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.
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: