A twelve-month program was conducted to develop and demonstrate an advanced injector to be used with the propellants N2O4/N2H4 at a thrust level of 3000 lbf. Five injectors were tested in 13 unique configurations to establish the parameters necessary to the optimization of performance, dynamic stability, chamber cooling capability, and injector/chamber compatibility. Once established, the optimized parameters were incorporated into a final injector. This last unit was employed in performance and stability demonstration tests and in long-duration durability tests. All contract design goals were met or exceeded by the final optimized injector. (Author)
Development and Demonstration of a N2O4/N2H4 Injector
1969
226 pages
Report
No indication
English
Rocket Propellants , Liquid rocket propellants , Injectors , Injection , Thrust , Optimization , Cooling , Compatibility , Fuel injectors , Fuel injection , Design , Liquid rocket oxidizers , Liquid rocket fuels , Hydrazine , Nitrogen oxides , Tetroxides , Throttling , Hiperthin injectors , Post boost propulsion systems , Nitrogen oxide(N2o4)
NTRS | 1986
|High Performance N2O4/Amine Elements
NTIS | 1976
|High performance N2O4/amine elements
NTRS | 1976
|