HMX-CMDB Propellants

Fig. 4.25 Specific impuise and adiabatic flame temperature of HMX-CMDB propellant.

Fig. 8.7 shows the adiabatic flame temperatures and the heats of explosion of HMX-CMDB propellants as a function of KNOj) under conditions of thermal equilibrium. The adiabatic flame temperatures, Tg, and the heats of explosion increase... 

Fig. 8.7 Adiabatic flame temperatures of HMX-CMDB propellants as a function of (N02) or heat of explosion.

Fig.8.9 Burning rates of HMX-CMDB propellants containing different mass fractions of HMX.

Fig. 8.13 Burning rate versus dark zone temperature for an HMX-CMDB propellant at different pressures.

Fig. 8.15 Temperature gradient in fizz zone versus dark zone temperature for an HMX-CMDB propellant at different pressures, showing that the heat flux transferred back to the burning surface increases with increasing dark zone temperature.

The temperature sensitivity, o, as defined in Eq. (3.73), of the HMX-CMDB propellants is shown as a function of hmx in Fig. 8.17. Though of the double-base propellant used as the base matrix decreases with increasing pressure, the values of the HMX-CMDB propellants remain relatively constant when hmx is kept con-... 

Fig. 8.20 Calculated and experimental burning rates for HMX-CMDB propellants, showing that the burning rate decreases with increasing HMX concentration (average HMX particle size = 200 pm).

Aoki, I., and Kubota, N., Combustion Wave Structure of HMX-CMDB Propellants (Eds. Varma, M., and Chatterjee, A. K.), pp. 133-143, Tata McGraw-Hill Publishing Co., Ltd., India (2002). 

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