A number of composite propellant compositions based on various burn rate suppressants were formulated and studied with the aim to select a suitable burn rate suppressant for reducing the burn rate of the basic propellant composition. Theoretical properties of the compositions were computed by using NASA CEC-71 program and the burn rate performance was evaluated. In addition, sensitivity, thermal, and mechanical properties of the compositions were also evaluated. The composition containing 60% AR 10% Al. 20% binder, and 10% burn rate suppressant (melamine) was insensitive to friction and impact (28.8 kg and 0.56 m) and showed 90% weight loss. The formulation was found to be relatively superior.