Journal of Chinese Society of Astronautics (Selected Articles),

Abstract

In this paper, a numerical solution of basic equation for one dimensional two-phase nonequilibrium flow in a combustion chamber of solid propellant rocket motors is discussed in detail, the effect of particle size on flow field in combustion chamber and pressure-time curves is analyzed, and some useful conclusions are obtained in comparison with results of one dimensional two-phase constant lag flow in combustion chamber. It is useful for predicting pressure-time curves accurately and providing accurate boundary conditions for the calculation of two-phase flow through the nozzle. (China, Chinese language, Translations).

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Document Details

Document Type
Technical Report
Publication Date
Apr 06, 1987
Accession Number
ADA179690

Entities

People

  • Shi-xue Yang
  • Weng-an Xu
  • Xianqi Chang

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Burning Rate
  • Chambers
  • Coefficients
  • Combustion
  • Combustion Chambers
  • Equations
  • Flow Fields
  • Flow Rate
  • Lepidoptera
  • Mass Flow
  • Measurement
  • Nonequilibrium Flow
  • Particle Size
  • Rocket Engines
  • Solid Propellants
  • Specific Heat
  • Two Phase Flow

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Electromagnetic Wave Scattering and Antenna Radiation Engineering
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster