Burning rate measurement of composite propellant using acoustic wave emission in comparison with other techniques

Abstract We study the impact of rotation on the hydrodynamic evolution of convective vortices during stellar collapse. Using linear hydrodynamics equations, we study the evolution of the vortices from their initial radii in convective shells down to smaller radii where they are expected to encounter the supernova shock. We find that the evolution of vortices is mainly governed by two effects: the acceleration of infall and the accompanying speed up of rotation. The former effect leads to the radial stretching of vortices, which limits the vortex velocities. The latter effect leads to the angular deformation of vortices in the direction of rotation, amplifying their non-radial velocity. We show that the radial velocities of the vortices are not significantly affected by rotation. We study acoustic wave emission and find that it is not sensitive to rotation. Finally, we analyze the impact of the corotation point and find that it has a small impact on the overall acoustic wave emission.

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Audible acoustic wave emission in excimer laser interaction with materials

Journal of Applied Physics ◽

10.1063/1.361182 ◽

1996 ◽

Vol 79 (5) ◽

pp. 2186-2191 ◽

Cited By ~ 20

Author(s):

Y. F. Lu ◽

M. H. Hong ◽

S. J. Chua ◽

B. S. Teo ◽

T. S. Low

Keyword(s):

Acoustic Wave ◽

Excimer Laser ◽

Laser Interaction ◽

Wave Emission ◽

Acoustic Wave Emission

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X-RAY DIAGNOSTICS FOR LOCAL BURNING RATE MEASUREMENT OF SOLID PROPELLANTS

International Journal of Energetic Materials and Chemical Propulsion ◽

10.1615/intjenergeticmaterialschemprop.v4.i1-6.850 ◽

1997 ◽

pp. 918-926 ◽

Cited By ~ 1

Author(s):

Masahiro Kohno ◽

Angelo Volpi ◽

Shin-Ichiro Tokudome

Keyword(s):

Burning Rate ◽

Solid Propellants ◽

Rate Measurement ◽

X Ray ◽

Local Burning

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Effect of Oxidizer-Fuel Mixture Ratio to the Pressure Exponent of Ammonium Perchlorate Based Composite Propellant

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.110-116.1380 ◽

2011 ◽

Vol 110-116 ◽

pp. 1380-1386

Author(s):

Amir Aziz ◽

Wan Khairuddin bin Wan Ali

Keyword(s):

Experimental Investigation ◽

Burning Rate ◽

Ammonium Perchlorate ◽

Fuel Mixture ◽

Isophorone Diisocyanate ◽

Composite Propellant ◽

Mixture Ratio

In this paper, experimental investigation of pressure exponent in burning rate of composite propellant was conducted. Four sets of different propellant compositions had been prepared with the combination of Ammonium Perchlorate (AP) as an oxidizer, Aluminum (Al) as fuel and Hydroxy-Terminated Polybutadiene (HTPB) as fuel and binder. For each mixture, HTPB binder was fixed at 15% and cured with isophorone diisocyanate (IPDI). By varying AP and Al, the effect of oxidizer-fuel mixture ratio (O/F) on the whole propellant can be determined. The propellant strands were manufactured using compression molded method and burnt in a strand burner using wire technique over a range of pressure from 1atm to 31atm. The results obtained shows that the pressure exponent n, increases with increasing O/F. The highest pressure exponent achieved was 0.561 for propellant p80 which has O/F ratio of 80/20.

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