DISTINCTIVE FEATURES OF COMBUSTION
OF A PROPELLANT AT A LEWIS NUMBER
OTHER THAN UNITY IN THE GAS PHASE
K. O. Sabdenov and L. L. Min'kov



UDC 536.46

The nonstationary combustion regimes of a homogeneous 
solid propellant, i.e., stability and steady-state combustion in an 
acoustic-wave field, are investigated. Analytical formulas for the 
boundary of stable combustion, the nonstationary rate of combustion, 
and the acoustic admittance are found. Account for the relaxation 
time of the gas phase substantially changes the concept of the region 
of stable combustion of a solid propellant. The exothermal reaction 
of decomposition of the propellant turns out to be improbable by virtue 
of the smallness of the stability region and the positiveness of 
henomenological coefficients. In the case of pressure oscillations with a
 period, comparable to the relaxation time of the gas phase, the acoustic 
dmittance of the propellant depends strongly on both this relaxation time and 
the Lewis number in the gas phase.

Tomsk State University, Tomsk, Russia; email: sabdenov@ftf.tsu.ru. 
Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 74, No. 6, 
pp. 61-72, November-December, 2001. Original article submitted 
March 27, 2001.

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