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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN Imprimir: 2150-766X
ISSN On-line: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v2.i1-6.230
pages 386-401

COMBUSTION BEHAVIOR OF BORON-BASED SOLID PROPELLANTS IN A DUCTED ROCKET

C. Vigot
Energetics Department, Office National d'Etudes et de Recherches Aerospatiales, France
A. Cochet
Energetics Department, Office National d'Etudes et de Recherches Aerospatiales, France
C. Guin
Energetics Department, Office National d'Etudes et de Recherches Aerospatiales, France

RESUMO

This paper presents results of experimental studies on airbreathing combustion of high boron-loaded solid propellants in connected-pipe ducted rockets at reduced and full-scale motor (chamber diameter: 0.100 m and 0.180 m) . Tests have been performed with lateral-shifted air inlet combustors. Previously, this configuration has been demonstrated more favorably for the ignition and complete burning of boron particles. The boron particle combustion is estimated in terms of total combustion efficiency based on injected mixture equivalent ratio.
At a small scale (D = 0.100 m), the effects on the combustion efficiency of different parameters which are the K ratio (fuel grain area to injection throat area), the chamber pressure and air inlet temperature were studied. To exactly evaluate the capability of boron-ducted rockets, tests have been performed at a larger and more representative scale (D = 0.180 m) in simulated low-altitude flight conditions. Based on the results from reduced scale studies, the full-scale engine tests have been defined. The obtained results from investigations on choked and unchoked gas generator configurations are given. Finally, both configurations are also compared with an integrated ducted rocket without boron.


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