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Analysis of Combustion Characteristics for Liquid Propellant Electrothermal Chemical Launcher(PDF)

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
1999年02期
Page:
24-27
Research Field:
Publishing date:

Info

Title:
Analysis of Combustion Characteristics for Liquid Propellant Electrothermal Chemical Launcher
Author(s):
Wuxuan Li Baoming Lu Shunxiang
School of Dynamic Engineering,NUST,Nanjing210094
Keywords:
plasmas combust ion process similarity mumerical simulat ion
PACS:
TJ01
DOI:
-
Abstract:
A theoret ical model has been presented to describe the combust ion process in a liquid propellant elect rothermal chemical launcher. T he model predict s the t ransient variat ions of g un chamber pressure, projectile motion and the decomposit ion rate of propellant. The calculat ions show that there exist double peaks during the process in the g un chamber pressures. The first peak, w hich appears at the moment that the project ile hardly moves, is associated w ith the init ial Tay lor cavity and the init ial discharg e of the plasma jet , w hereas the second peak is a result of both the discharge of plasma jet and the combust ion of liquid propellant . The influences of init ial Taylor cavity , input of plasma energy, coeff icients of propellant decomposit ion rate and project ile masses on the combust ion process have also been analyzed.

References:

1 Yabe T ,Hoshino H. Two and three-dimensional behav ior of rayleigh- tay lor and Kelvin-Helmholtz instabilities. Physical Review, 1991, 44( 4) : 55~ 61
2 Goug h P S. Theor etical modeling of the interior ballist ics of the electro thermal gun. ADA268583,1993
3 Chen J L, Kuo K K. Theo ret ic modeling of the inter ior ballistics processes in an electrothermalGun. 27 t h JANNAF Combustion Meeting, 1990, 11( 1) : 33~ 47

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Last Update: 2013-03-29