Recent ASI Progress in Pulse Detonation Rocket Engine (PDRE) Hardware Development

Abstract

This paper presents a brief overview of Adroit Systems, Inc. (ASI) experimental Pulse Detonation Rocket Engine (PDRE) development efforts and accompanying numerical modeling efforts. Test results for thirty-second firings of a H2/O2 fueled combustor at firing frequencies of up to 95 Hz are presented for a range of propellant mixture ratios. These experimental results were then used to validate a single-combustor computational model. The necessity of elevated operating pressure to engine performance is outlined. ASI efforts to obtain these elevated operating pressures are then briefly presented.

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Document Details

Document Type
Technical Report
Publication Date
Jun 11, 1999
Accession Number
ADA405512

Entities

People

  • D. C. Mueller
  • J. T. Williams
  • K. Lupkes
  • Stephen M. Henderson
  • T. E. Bratkovich

Tags

Communities of Interest

  • Biomedical
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Combustion
  • Combustion Chambers
  • Combustors
  • Computational Fluid Dynamics
  • Detonation Waves
  • Engine Components
  • Fluid Dynamics
  • Frequency
  • Geometry
  • Heat Transfer
  • Mach Number
  • Mass Flow
  • Propulsion Systems
  • Rocket Engines
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computer Science/Computer Engineering/Data Science/Digital Signal Processing.
  • Optical Fiber Sensing and Electromagnetic Propagation.
  • Rocket Propulsion.