Thermodynamic and thermo chemical calculation of rockets propellants 

Program TCPSP (Thermo-Chemical Properties Solid Propellant) should enable:

• Program which calculates chemical equilibrium product concentrations from any set of reactants and determines thermodynamic and transport properties for the product mixture.
• Applied algorithm enables calculation of theoretical performances for composite and double-base rocket propellants for frozen and equilibrium expansion.
• Calculation of theoretical performances of rocket motors is based on assumption of the Infinite-area combustion chamber (IAC) model:
• Expansion to given Mach number (condition for throat area)
• Expansion to given pressure at the nozzle exit
• Expansion to given expansion ratio (program enables calculation expansion for 3 different expansion ratio)

Input

The base of combustion products (termo.dat)

• 17 chemical elements (Al, C, Ca, H, K, Mg, N, Na, O, P, S, Si, Ti, F, Fe, Cl, Pb)
• 156 gaseous combustion products
• 39 phase-condensed combustion products

The data-base consisting of 62 propellant ingredients (based on available data published by MARTIN MARIETA and STANAG 4400)

This bases are open for update

Comparative analysis of some properties for solid propellant BUTALANE 82/4 in case of „shifting"
equilibrium expansion when compared to results from Ophelia version 3

Comparative analysis of some properties in the combustion
chamber for the solid propellant AP/CHOS-Binder/ Al/MgO/H2O

Note: CEA - Chemical Equlibrium with Applications; Gordon S. and McBride B.: Computer Program for Calculation of Complex Chemical Equlibrium Composition ond Applications, I i II, NASA RP 1311