Experimental Investigation of the Constant-Volume Pulsed Rocket Concept (POSTPRINT)

Abstract

Constant-volume combustion pulsed rocket systems may offer significant operational advantages over traditional constant-pressure rocket systems, including the reduced weight and complexity of low pressure propellant feed systems. A novel sub-scale facility has been built and tested at AFRL to assess the merits and feasibility of a constant-volume pulsed combustion rocket motor. Initial hotfire testing has been performed and those results are compared with a simple transient numerical model to assess performance. In initial testing with nitromethane based monopropellants, little modulation in chamber pressure has been achieved. Some substantial chamber pressure modulation has been achieved in partially pulsed bi-propellant operation, but this behavior is still significantly below ideal levels. Further modification of test hardware and use of more volatile monopropellants may enable a more operable cycle.

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Document Details

Document Type
Technical Report
Publication Date
Nov 22, 2005
Accession Number
ADA444992

Entities

People

  • E. B. Coy
  • J. M. Watts

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Acquisition
  • Air Force Research Laboratories
  • Back Pressure
  • Combustion
  • Combustion Chambers
  • Combustors
  • Data Acquisition
  • Engines
  • Heat Transfer
  • Ignition
  • Liquid Propellants
  • Military Research
  • Monopropellants
  • Pressurization
  • Propellants
  • Rocket Engines
  • Steady Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.