Accession Number:

AD0367583

Title:

DEMONSTRATION OF AN ADVANCED SOLID PROPELLANT

Descriptive Note:

Quarterly progress rept. no. 2, 1 Aug-31 Oct 1965

Corporate Author:

UNITED TECHNOLOGY CENTER SUNNYVALE CA

Personal Author(s):

Report Date:

1965-11-01

Pagination or Media Count:

81.0

Abstract:

A series of 4-lb motors have been tested containing aluminum hydride aluminum combinations representing the most dense formulations with a theoretical performance in excess of 280 sec and the most dense formulation with a theoretical performance in excess of 274 sec. Propellant UTP 6825 has a theoretical Isp of 280.1 sec, and a theoretical density of 0.0604 lbcu in. Propellant UTP 6825 has a theoretical Isp of 275.0 sec and a theoretical density of 0.0627cu in. A study to determine the effect of propellant formulation parameters on burning rates has been essentially completed. An end-burning micromotor was utilized for these tests. It was found tha the oxidizer-to-fuel OF ratio, AP concentration, and AP particle size distribution were the most critical parameters. Binder concentration and plasticizer level were found to be less significant. Efforts to minimize the handling hazards of aluminum hydride by increasing the electrical conductivity of the particles have been partially successful. A 1 coating of an antistatic agent reduced the electrical resistance of a 1 in. by 1 in. by 14 in. bed of particles from 1000 megohms for uncoated hydride to 40 to 70 megohms for the treated material. Propellant density studies indicate that in addition to the extensive drying of ingredients, propellant density can also be increased by sustained vibration and vacuum applied to the cast propellant.

Subject Categories:

  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE