Demonstration of Ambient Temperature Cure.
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 ZnO/linoleic acid and ZnO/Fe(AA)3/benzilic acid/HAA. Of these two, the ZnO/linoleic 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 ZnO/dibutyltin dilaurate/benzilic acid and ZnO/Fe(AA)3/benzilic acid/HAA. 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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1972
- Accession Number
- AD0905526
Entities
People
- Edmond J. Mastrolia
- H. J. Michigian
Organizations
- Aerojet Rocketdyne Holdings