Double base propellants are among the most powerful solid propellants and due to their high energy, specific impulse and large range of burning velocities are used very frequently and are preferred to many composite propellants. For the increase of rocket travel range the increase of specific impulse is very important in such a way that a 5% increase in this parameter results in a 45% increase in the range of travel.
In this work production of double base propellants on laboratory scale has been carried out in order to reaching a specific impulse of minimum 240 Sec for a combustion pressure of 1000 Psi and exit gas pressure of 14.7 Psi. High energy double base propellant contains material such as Cyclotrimethylen tetranitroamine (HMX), Cyclotrimethylen trinitroamine (RDX), Amonium perchlorate (AP) and Aluminum (Al) which can be produced by both extrusion and casting.
High energy double base propellants used in this investigation have been AP and Al which have been produced by the in solution extrusion method. In this study the software CEC is used to calculate the specific impulse and other parameter of the twelve samples and formulations produced in the laboratory.
After optimization of various parameters in the mixture and checking the physical and chemical properties as well as the results of the static test using a laboratory rocket motor, a formulation is found which results in theoretical specific impulse of 260 Sec. This theoretical value corresponds to a practical standard value of 254 second which is a considerable increase in the present specific impulse of current double base propellants.
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