STORABLE TOROIDAL COMBUSTOR DEMONSTRATION PROGRAM. VOLUME I.
Abstract
Performance and cooling feasibility demonstrations were accomplished at 2000-psia chamber pressure with a 10,000-pound-thrust toroidal combustor using nitrogen tetroxide/50-percent hydrazine-50-percent unsymmetrical dimethyl-hydrazine, N2O4/N2H4-UDMH (50-50), propellants. Injectors, workhorse ablative chambers, and cooled chambers were designed and fabricated to support these demonstrations. A description of the test components and the results of the feasibility demonstration tests are presented. These feasibility demonstrations include injector evaluation testing using the workhorse ablative thrust chambers and cooled thrust chamber evaluation testing. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1966
- Accession Number
- AD0376137
Entities
Organizations
- Rocketdyne