Rocket module#
In this section, you will find the documentation of the routines implemented to obtain the rocket propellant performance under ideal conditions. There are two models:
IAC: Infinite-Area-Chamber,
FAC: Finite-Area-Chamber.
Note
This module is based on Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
Routines
- compute_FAC(self, mix1, mix2_inj, mix2_c, mix3)#
Compute chemical equilibria at the injector, outlet of the chamber and at the throat using the Finite-Area-Chamber (FAC) model
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
self (
struct
) – Data of the mixture, conditions, and databasesmix1 (
struct
) – Properties of the initial mixturemix2_inj (
struct
) – Properties of the mixture at the injector of the chamber (previous calculation)mix2_c (
struct
) – Properties of the mixture at the outlet of the chamber (previous calculation)mix3 (
struct
) – Properties of the mixture at the throat (previous calculation)
- Returns:
Tuple containing
mix2_inj (struct): Properties of the mixture at the injector of the chamber
mix2_c (struct): Properties of the mixture at the outlet of the chamber
mix3 (struct): Properties of the mixture at the throat
Example
[mix2_inj, mix2_c, mix3] = compute_FAC(self, mix1, mix2_inj, mix2_c, mix3)
- compute_chamber_IAC(self, mix1, mix2)#
Compute chemical equilibria at the exit of the chamber (HP) using the Infinite-Area-Chamber (IAC) model
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
self (
struct
) – Data of the mixture, conditions, and databasesmix1 (
struct
) – Properties of the initial mixturemix2 (
struct
) – Properties of the mixture at the outlet of the chamber (previous calculation)
- Returns:
mix2 (struct) – Properties of the mixture at the outlet of the chamber
Example
mix2 = compute_chamber_IAC(self, mix1, mix2)
- compute_exit(self, mix2, mix3, mix4, Aratio, varargin)#
Compute thermochemical composition for a given Aratio
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
self (
struct
) – Data of the mixture, conditions, and databasesmix2 (
struct
) – Properties of the mixture at the outlet of the chambermix3 (
struct
) – Properties of the mixture at the throatmix4 (
struct
) – Properties of the mixture at the exit (previous calculation)Aratio (
struct
) – Ratio area_exit / area_throat
- Optional Args:
mix2_in (struct): Properties of the mixture at the inlet of the chamber
- Returns:
mix3 (struct) – Properties of the mixture at the throat
Examples
mix4 = compute_exit(self, mix2, mix3, mix4, Aratio)
mix4 = compute_exit(self, mix2, mix3, mix4, Aratio, mix2_in)
- compute_throat_IAC(self, mix2, mix3)#
Compute thermochemical composition for the Infinite-Area-Chamber (IAC) model
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
self (
struct
) – Data of the mixture, conditions, and databasesmix2 (
struct
) – Properties of the mixture at the outlet of the chambermix3 (
struct
) – Properties of the mixture at the throat (previous calculation)
- Returns:
mix3 (struct) – Properties of the mixture at the throat
Example
mix3 = compute_throat_IAC(self, mix2, mix3)
- guess_pressure_IAC_model(mix)#
Compute pressure guess [bar] at the throat considering an Infinite-Area-Chamber (IAC)
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
mix (
struct
) – Properties of the mixture- Returns:
pressure (float) – Pressure at the throat [bar]
Example
pressure = guess_pressure_IAC_model(mix)
- guess_pressure_exit_IAC(mix2, mix3, Aratio, FLAG_SUBSONIC)#
Compute guess logarithm of the ratio pressure_inf / pressure_exit [-] for the given Area ratio [-] and indicanting if the point of interest is in the subsonic area ratios or the supersonic area ratios
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
mix2 (
struct
) – Properties of the mixture at the outlet of the chambermix3 (
struct
) – Properties of the mixture at the throatAratio (
struct
) – Ratio area_exit / area_throatFLAG_SUBSONIC (
bool
) – Flag indicating if the Aratio refer to the subsonic region or the supersonic region
- Returns:
log_P (float) – Log pressure ratio [-]
Example
log_P = guess_pressure_exit_IAC(mix2, mix3, 3, false)
- rocket_parameters(mix2, mix3, gravity, varargin)#
Compute Rocket performance parameters at the throat
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
mix2 (
struct
) – Properties of the mixture at the outlet of the chambermix3 (
struct
) – Properties of the mixture at the throatgravity (
float
) – Gravitational acceleration [m/s2]
- Returns:
mix3 (struct) – Properties of the mixture at the throat
- rocket_performance(self, mix1, varargin)#
Routine that computes the propellant rocket performance
- Methods implemented:
Infinite-Area-Chamber (IAC)
Finite-Area-Chamber (FAC)
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
self (
struct
) – Data of the mixture, conditions, and databasesmix1 (
struct
) – Properties of the initial mixture
- Optional Args:
Aratio (struct): Ratio area_exit / area_throat
mix2_inj (struct): Properties of the mixture at the injector (previous calculation)
mix2_c (struct): Properties of the mixture at the outlet of the chamber (previous calculation)
mix3 (struct): Properties of the mixture at the throat (previous calculation)
mix4 (struct): Properties of the mixture at the given exit points (previous calculation)
- Returns:
Tuple containing
mix1 (struct): Properties of the initial mixture
mix2_inj (struct): Properties of the mixture at the injector
mix2_c (struct): Properties of the mixture at the outlet of the chamber
mix3 (struct): Properties of the mixture at the throat
mix4 (struct): Properties of the mixture at the given exit points
Examples
[mix1, mix2_inj, mix2_c, mix3, mix4] = rocket_performance(self, mix1)
[mix1, mix2_inj, mix2_c, mix3, mix4] = rocket_performance(self, mix1, Aratio)
[mix1, mix2_inj, mix2_c, mix3, mix4] = rocket_performance(self, mix1, Aratio, mix2_inj)
[mix1, mix2_inj, mix2_c, mix3, mix4] = rocket_performance(self, mix1, Aratio, mix2_inj, mix2_c)
[mix1, mix2_inj, mix2_c, mix3, mix4] = rocket_performance(self, mix1, Aratio, mix2_inj, mix2_c, mix3)
[mix1, mix2_inj, mix2_c, mix3, mix4] = rocket_performance(self, mix1, Aratio, mix2_inj, mix2_c, mix3, mix4)
- solve_model_rocket(self, mix1, mix2_inj, mix2_c, mix3, mix4, Aratio)#
Compute chemical equilibria at different points of the rocket depending of the model selected
- Methods implemented:
Infinite-Area-Chamber (IAC)
Finite-Area-Chamber (FAC)
This method is based on the method outlined in Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311.
- Parameters:
self (
struct
) – Data of the mixture, conditions, and databasesmix1 (
struct
) – Properties of the initial mixturemix2_inj (
struct
) – Properties of the mixture at the injector [only FAC] (previous calculation)mix2_c (
struct
) – Properties of the mixture at the outlet of the chamber (previous calculation)mix3 (
struct
) – Properties of the mixture at the throat (previous calculation)mix4 (
struct
) – Properties of the mixture at the given exit points (previous calculation)Aratio (
float
) – Area ratios [-]
- Returns:
Tuple containing
mix2_1 (struct): Properties of the mixture at injector of the chamber (only FAC)
mix2 (struct): Properties of the mixture at the outlet of the chamber
mix3 (struct): Properties of the mixture at the throat
mix4 (struct): Properties of the mixture at the given exit points
Example
[mix2_1, mix2, mix3, mix4] = solve_model_rocket(self, mix1, mix2_1, mix2, mix3, mix4, Aratio)