AN INTEGRATED RESEARCH EFFORT ON HIGH-ENERGY HYBRID PROPELLANTS.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1965
- Accession Number
- AD0367584
Entities
People
- C. W. Vickland