Development and Demonstration of Passively Cooled Thrust Chamber Assemblies for Fluorinated Propellants.
Abstract
This study was a two-phase development program which evaluated 3000-lb thrust (sea level), passively cooled thrust chambers at chamber pressures of 300 and 500 psia using fluorinated oxidizer and amine fuels. Phase I was a 17-month effort consisting of the design, fabrication, test, and posttest analysis of two thermally instrumented thrust chambers. These were each tested at 300 psia chamber pressure and accumulated 400 sec of operation on a duty cycle that included multiple hot and cold restarts and long-duration firings with two types of propellants: ClF/3 MMH and ClF3/BA-1014. Phase II was a 6-month effort consisting of the design, fabrication, and posttest analysis of one thermally instrumented thrust chamber which was operated at 500 psia chamber pressure using ClF3/M-20 propellant.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1970
- Accession Number
- AD0507622
Entities
People
- James C. Dickson
- Robert C. Schindler
Organizations
- Aerojet Rocketdyne Holdings