Accession Number:

AD0905526

Title:

Demonstration of Ambient Temperature Cure.

Descriptive Note:

Interim rept. 17 Apr-17 Nov 72,

Corporate Author:

AEROJET SOLID PROPULSION CO SACRAMENTO CA

Report Date:

1972-11-01

Pagination or Media Count:

74.0

Abstract:

Four propellants are being optimized for ambient temperature processing and cure. These are 1 an 88 wt solids 0.40 ips at 1000 psia burning rate R-45M propellant, 2 an 88 wt solids 1.70 or - 0.20 ips at 1000 psia burning rate R-45M propellant, 3 an 88 wt solids 0.40 ips at 1000 psia burning rate propellant based on a Li-HTPB binder, and 4 an 86 wt solids 0.40 ips at 1000 psia burning rate propellant based on a Telagen CTPB binder cured with epoxides. Two catalyst systems have been evaluated with the propellants containing the R-45M binder. These were ZnOlinoleic acid and ZnOFeAA3benzilic acidHAA. Of these two, the ZnOlinoleic acid system was selected for the scale up studies. The 0.40 ips at 1000 psia burning rate formulation has been successfully scaled up through 30 gallon mix size. The 1.70 or - 0.20 ips at 1000 psia burning rate propellant has been optimized for ambient temperature cure in one gallon mixes. Two catalyst systems are being optimized for ambient temperature cure and processing in the 88 solids Li-HTPB propellant. These are ZnOdibutyltin dilauratebenzilic acid and ZnOFeAA3benzilic acidHAA. Satisfactory ambient temperature processing and cures have been achieved with the tin catalyst. Satisfactory ambient temperature processing and cures have been achieved with the Telagen CTPB propellant using Cr octoate catalyst. This propellant has been successfully scaled up through 30 gallon mix size. Author

Subject Categories:

  • Fabrication Metallurgy
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE