Progress on Pulsed Detonation Rocket Propulsion at AFRL: Constant-Volume Limit Studies and LOX Spray Detonations

Abstract

Progress and plans for research at AFRL on pulsed-detonation rocket engines are described. Analytical studies of the constant-volume limit of pulsed-propulsion have been completed and have shown that the specific impulse penalty of using a fixed area ratio nozzle is less than 3%. Numerical studies of pulsed combustors have elucidated the importance of characteristic times for heat release, chamber blowdown and injector pulsing period. Experimental studies are under way to demonstrate the feasibility of the concept and provide anchoring data for the model. Plans for LOX spray detonation studies are described.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 05, 2000
Accession Number
ADA410112

Entities

People

  • Douglas G. Talley
  • E. B. Coy

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Burning Rate
  • Chambers
  • Combustion
  • Combustors
  • Engines
  • Fuel Injectors
  • Liquid Oxygen
  • Materials Laboratories
  • Measurement
  • Military Research
  • Physical Properties
  • Propellants
  • Propulsion Systems
  • Rocket Engines
  • Rocket Propulsion

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Systems Analysis and Design