Development and Demonstration of a N2O4/N2H4 Injector

Abstract

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 11, 1969
Accession Number
AD0503092

Entities

People

  • James O. Hartsell

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Energy and Power Technologies
  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Chemical Reactions
  • Combustion
  • Contracts
  • Fabrication
  • Government Procurement
  • Heat Transfer
  • Heat Transfer Coefficients
  • Materials
  • Materials Processing
  • Measurement
  • Physics Laboratories
  • Propellants
  • Reliability
  • Resonant Frequency
  • Rocket Engines

Readers

  • Internal Combustion Engine (ICE) Technology.
  • Software Engineering