Source code for RCAIDE.Library.Attributes.Propellants.Rocket_LH2
# RCAIDE/Library/Attributes/LH2.py
#
#
# Created: Sep 2023, M. Clarke
# Modified:
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# IMPORT
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from .Propellant import Propellant
from RCAIDE.Framework.Core import Units
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# Rocket_LH2
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[docs]
class Rocket_LH2(Propellant):
"""
A class representing liquid hydrogen (LH2) fuel properties specifically for rocket
propulsion applications. Optimized for high-performance rocket engines with
oxygen as oxidizer.
Attributes
----------
tag : str
Identifier for the propellant ('Rocket_LH2')
molecular_weight : float
Molecular weight in kg/kmol (12.644)
isentropic_expansion_factor : float
Ratio of specific heats (1.145)
combustion_temperature : float
Adiabatic flame temperature in K (3331.0)
gas_specific_constant : float
Specific gas constant in J/(kg*K) (8314.45986/molecular_weight)
Notes
-----
This class implements properties for rocket-grade liquid hydrogen, focusing on
parameters relevant to high-performance rocket engine applications. Properties
are optimized for use with liquid oxygen in bipropellant rocket engines.
**Definitions**
'Isentropic Expansion Factor'
Ratio of specific heats (cp/cv) for exhaust products
'Combustion Temperature'
Theoretical maximum temperature achieved in the combustion chamber
'Gas Specific Constant'
Individual gas constant for combustion products
**Major Assumptions**
* Properties are for rocket engine operating conditions
* O/F ratio of 5.50 (oxygen to fuel mass ratio)
References
----------
[1] Sutton, G. P., & Biblarz, O. (2017). Rocket Propulsion Elements. John Wiley & Sons Inc.
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
Assujmes an O/F ratio 5.50
Source:
Sutton, Rocket Propulsion Elements Using CEA
"""
self.tag = 'Rocket_LH2'
self.molecular_weight = 12.644 # [kg/kmol]
self.isentropic_expansion_factor = 1.145
self.combustion_temperature = 3331.0*Units.kelvin # [K]
self.gas_specific_constant = (8314.45986/self.molecular_weight)*Units['J/(kg*K)'] # [J/(kg-K)]
self.stoichiometric_fuel_air_ratio = 0 # [-] Stoichiometric Fuel to Air ratio
self.heat_of_vaporization = 0 # [J/kg] Heat of vaporization at standard conditions
self.temperature = 0 # [K] Temperature of fuel
self.pressure = 0 # [Pa] Pressure of fuel
self.fuel_surrogate_S1 = {} # [-] Mole fractions of fuel surrogate species
self.kinetic_mechanism = '' # [-] Kinetic mechanism for fuel surrogate species
self.oxidizer = ''
