RCAIDE.Library.Attributes.Propellants.Rocket_LH2

Rocket_LH2#

class Rocket_LH2(*args, **kwarg)[source]#

Bases: Propellant

A class representing liquid hydrogen (LH2) fuel properties specifically for rocket propulsion applications. Optimized for high-performance rocket engines with oxygen as oxidizer.

tag#

Identifier for the propellant (‘Rocket_LH2’)

Type:

str

molecular_weight#

Molecular weight in kg/kmol (12.644)

Type:

float

isentropic_expansion_factor#

Ratio of specific heats (1.145)

Type:

float

combustion_temperature#

Adiabatic flame temperature in K (3331.0)

Type:

float

gas_specific_constant#

Specific gas constant in J/(kg*K) (8314.45986/molecular_weight)

Type:

float

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.