Source code for RCAIDE.Library.Attributes.Propellants.Liquid_Hydrogen
# RCAIDE/Library/Attributes/Liquid_Hydrogen.py
#
#
# Created: Sep 2023, M. Clarke
# Modified:
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# IMPORT
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from .Propellant import Propellant
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# Liquid Hydrogen
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[docs]
class Liquid_Hydrogen(Propellant):
"""
A class representing liquid hydrogen (LH2) fuel properties for aviation applications.
Attributes
----------
tag : str
Identifier for the propellant ('Liquid_H2')
reactant : str
Oxidizer used for combustion ('O2')
density : float
Fuel density in kg/m³ (59.9)
specific_energy : float
Specific energy content in J/kg (141.86e6)
energy_density : float
Energy density in J/m³ (8491.0e6)
stoichiometric_fuel_to_air : float
Stoichiometric fuel-to-air ratio (0.0291)
temperatures : Data
Critical temperatures
- autoignition : float
Autoignition temperature in K (845.15)
Notes
-----
Liquid hydrogen represents a zero-carbon aviation fuel option with the highest
specific energy of any fuel, but requires cryogenic storage at extremely low
temperatures (-253°C).
**Definitions**
'Specific Energy'
Energy content per unit mass, approximately 3 times higher than kerosene
'Energy Density'
Energy content per unit volume, lower than conventional fuels due to low density
'Stoichiometric Fuel-to-Air Ratio'
Ideal fuel-to-air mass ratio for complete combustion to H2O
**Major Assumptions**
* Properties are for liquid hydrogen
* No consideration of boil-off losses
References
----------
[1] Roberts, K. (2008). ANALYSIS AND DESIGN OF A HYPERSONIC SCRAMJET ENGINE WITH A STARTING MACH NUMBER OF 4.00 (thesis). UTA. University of Texas at Austin. Retrieved December 30, 2024, from https://arc.uta.edu/publications/td_files/Kristen%20Roberts%20MS.pdf.
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
http://arc.uta.edu/publications/td_files/Kristen%20Roberts%20MS.pdf
"""
self.tag = 'Liquid_H2'
self.reactant = 'O2'
self.density = 70.85 # [kg/m^3]
self.specific_energy = 141.86e6 # [J/kg]
self.energy_density = 8491.0e6 # [J/m^3]
self.temperatures.autoignition = 845.15 # [K]
self.stoichiometric_fuel_air_ratio = 0.029411 # [-] 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 = ''
