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Use in Propellant Systems

Combustion reactions are excessively used in propellant systems. The impulse of the gaseous combustion products is used to propel a payload. For obvious technical reasons, the burning temperature of a rocket engine is of interest. The adiabatic flame temperature of combustion (Tad) is the temperature at which reactants and products do not differ in enthalpy. The enthalpies of the components of the system have to be calculated from their standard enthalpy by adding of the enthalpy caused by heating to Tad. This is where the specific heat capacity Cv comes into play. Unfortunately, the component ratios of the system are functions of the temperature, necessitating the use of iterative calculations of Tad. [Pg.41]

Fischer, N., Iszak, D., Klapotke, T.M. et al. (2012) Nitrogen-rich 5,5 -bistetrazolates and their potential use in propellant systems a comprehensive study. Chemistry - A European Journal, 18, 4051-4062. [Pg.250]


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