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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Print: 2150-766X
ISSN Online: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.630
pages 654-658

INVESTIGATION OF SOLID ROCKET PROPELLANT COMBUSTION BY LASER DOPPLER ANEMOMETRY

Angelo Volpi
CNPM- National Research Council, Viale F. Baracca, 69 20068 Peschiera Borromeo, Milano, Italy
Claudio Zanotti
TEMPE - National Research Council Via Cozzi 53, 20125 Milano, Italy

ABSTRACT

The experimental study of solid propellant combustion has been improved by using Laser Doppler Anemometry (LDA), which is able to measure the velocity of the gases coming from the burning propellant surface. This technique provides data which can be used to define the combustion processes because the gas velocity strongly depends on burning rate. [1] Thus, every combustion transient can also be studied analyzing the time evolution of the gas velocity. Despite the hostility of the medium (hot gas with solid particles) LDA actually finds applications ranging from basic studies on propellants combustion to real propulsion systems. [2] This diagnostic provides useful information and an accurate picture of the flame structure. It has been used to test double base (DB) propellants under steady state conditions in the pressure range from 15 to 40 atm and AP composite propellants from the Pressure Deflagration Limit (PDL) up to 5 atm. Self-sustained oscillatory burning, occurring at sub-atmospheric pressure for AP composite propellants, has also been investigated. By using a modulated carbon dioxide laser, and the LDA apparatus, the frequency response of an AP propellant, burning in the sub-atmospheric pressure range, has been studied.


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