Micro-Propulsion Devices in Low Temperature Co-Fired Ceramics

Abstract

Three supersonic nozzle configurations were developed and tested using the LTCC materials system. An isentropic model was generated to determine the overall size of each nozzle and the nozzle curvature was defined using a Method of Characteristics approach. Each nozzle was tested using a cold gas test stand at several pressures. The experimental thrust measurement was compared to the isentropic model and several 3D CFD models. A schlieren visualization system was created to further validate the CFD model results.. A hydrogen peroxide catalyst chamber was modeled and constructed. Four configurations were developed to determine the effect on reactor performance. The device inlet pressure and surface temperature were measured during a constant inlet mass flow rate of hydrogen peroxide propellant. The performance of the LTCC catalyst chamber and nozzle indicates that this technology can be used as a feasible micro-propulsion device.

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Document Details

Document Type
Technical Report
Publication Date
Feb 27, 2009
Accession Number
ADA495405

Entities

People

  • Amy J. Moll
  • Donald G. Plumlee
  • Judi Steciak

Organizations

  • Boise State University

Tags

Communities of Interest

  • Advanced Electronics
  • Biomedical
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Cold Gases
  • Computational Fluid Dynamics
  • Fabrication
  • Flow
  • Flow Rate
  • Geometry
  • Low Temperature
  • Mass Flow
  • Materials
  • Measurement
  • Microelectromechanical Systems
  • Propellants
  • Propulsion Systems
  • Rocket Oxidizers
  • Surface Temperature
  • Test Stands

Fields of Study

  • Engineering

Readers

  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.
  • Rocket Propulsion.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow