Combustion of NC-TMETN Propellants

The chemical compositions and thermochemical properties of representative NC-NG and NC-TMETN double-base propellants are compared in Table 4.9. Though the NC/NG mass ratio of 0.80 is much smaller than the NC/TMETM mass ratio of 1.38, the combustion performance in terms of Tf and Mg is seen to be similar, and 0 is 109 kmol K kg for both propellants. In the case of rocket motor operation, Igp and pj, are also approximately equivalent for both propellants. 

Though the major components of double-base propellants are NC-NG or NC-TMETN, various additives such as plasticizers, burning rate modifiers, and combustion instability suppressants are also needed. Table 4-15 shows the materials used to formulate double-base propellants. 

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