Source code for RCAIDE.Library.Attributes.Propellants.Gaseous_Hydrogen
# RCAIDE/Library/Attributes/Propellants/Gaseous_Hydrogen.py
#
#
# Created: Mar 2024, M. Clarke
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# Imports
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from .Propellant import Propellant
from RCAIDE.Framework.Core import Data
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# Gaseous_Hydrogen Class
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[docs]
class Gaseous_Hydrogen(Propellant):
"""
A class representing gaseous hydrogen (H2) fuel properties for propulsion applications.
Attributes
----------
tag : str
Identifier for the propellant ('hydrogen_gas')
reactant : str
Oxidizer used for combustion ('O2')
specific_energy : float
Specific energy content in J/kg (141.86e6)
energy_density : float
Energy density in J/m³ (5591.13e6)
max_mass_fraction : Data
Maximum fuel-to-oxidizer mass ratios
- Air : float
Maximum mass fraction with air (0.013197)
- O2 : float
Maximum mass fraction with pure oxygen (0.0630)
molecular_mass : float
Molar mass in kg/kmol (2.016)
gas_constant : float
Specific gas constant in J/kg-K (4124.0)
pressure : float
Storage pressure in Pa (700e5)
temperature : float
Reference temperature in K (293.0)
compressibility_factor : float
Gas compressibility factor (1.4699)
density : float
Gas density at reference conditions in kg/m³ (39.4116)
Notes
-----
This class implements properties for gaseous hydrogen fuel at high pressure
storage conditions. Properties account for real gas behavior through the
compressibility factor.
**Definitions**
'Compressibility Factor'
Correction factor for real gas behavior deviation from ideal gas law
'Specific Energy'
Energy content per unit mass, significantly higher than hydrocarbon fuels
'Max Mass Fraction'
Maximum fuel fraction for stoichiometric combustion with different oxidizers
**Major Assumptions**
* Real gas behavior is accounted for via compressibility factor
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
None
"""
self.tag = 'hydrogen_gas'
self.reactant = 'O2'
self.specific_energy = 141.86e6 # J/kg
self.energy_density = 5591.13e6 # J/m^3
self.max_mass_fraction = Data({'Air' : 0.013197, 'O2' : 0.0630}) # kg propellant / kg oxidizer
# gas properties
self.molecular_mass = 2.016 # kg/kmol
self.gas_constant = 4124.0 # J/kg-K
self.pressure = 700e5 # Pa
self.temperature = 293.0 # K
self.compressibility_factor = 1.4699 # compressibility factor
self.density = 39.4116 # kg/m^3
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 = ''
