Accession Number:

AD0367584

Title:

AN INTEGRATED RESEARCH EFFORT ON HIGH-ENERGY HYBRID PROPELLANTS.

Descriptive Note:

Final rept.,

Corporate Author:

UNITED TECHNOLOGY CENTER SUNNYVALE CA

Personal Author(s):

Report Date:

1965-10-01

Pagination or Media Count:

178.0

Abstract:

A lightweight 12-in. hybrid test motor was developed which is capable of delivering 5000-lb thrust for 20-sec and up to 90-sec duration at reduced thrust. The motor consistently delivered a specific impulse in excess of 300 sec. The propellant system, consisting of OF2 and a fuel containing Li. LiH, and a binder demonstrated its suitability to space storable mission requirements. Injector development studies resulted in several injector designs. Fuel system studies were conducted with a fuel containing 50 THA and 50 binder. A thrust control system with a thrust control valve, an oxidizer flow-divider valve, and a control network was designed and successfully tested. Formulations studies resulted in selection of a potential prepackaged hybrid propellant system consisting of ClF5 and a fuel containing triaminoguanidine azide TAZ or tetraformaltrisazine TFTA, B or Al, NH4Cl04, and a binder. This propellant system was selected because it has high theoretical specific and density impulse levels. Fifty-six 3.5-in. motor tests were conducted using ClF3 to evaluate and screen the fuel systems. Forty 5.0-in. motor tests were conducted with 5 fuel blends using the components previously mentioned. A fuel containing 35 TFTA, 20 Al, 15 AP, and 30 binder was used in six 12-in. motor tests, delivering up to 95 of the theoretical specific impulse. Author

Subject Categories:

  • Rocket Engines
  • Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE