PCDE Propellant Studies

Abstract : A PCDE-TMETN propellant has been developed and made in six 1-gal and three 5-gal batches. The formulation which consists of 40.5 wt% HMX, 20.5 wt% AP, and 18 wt% AL, and a binder based on equal parts of PCDE and TMETN is calculated to have a theoretical specific impulse of 271.2 of which 256.5 will be delivered in the Aerojet 10KS2500 motor. The propellant density is 0.06842 lb/cu in. At 125 F, the processing temperature, the propellant is Aerojet Type 3 and does not require remote handling. The burning rate of the propellant is 0. 466 in./sec at 1000 psia with a pressure exponent of 0.60. The pi sub k is 0.2%/deg F between -65 F and 150 F. In R and H 2C1.5-4 motors fired at AFRPL the burning rate was 0.49 in./sec at 1000 psia with a pressure exponent of 0.53. The propellant ages poorly at 150 F, but maintains adequate mechanical, safety, and ballistic properties at 110 F and 77 F for more than eight weeks. Currently being developed is a PCDE-BDNPA/F propellant.