Institute of Chemical Physics, Russian Academy of Sciences
Institute of Space and Astronautical Science
Nissan Motor Co., Ltd.
Nissan Motor Co., Ltd.
出版者
宇宙科学研究所
出版者（英）
Institute of Space and Astronautical Science
雑誌名
The Institute of Space and Astronautical Science report
巻
661
ページ
1 - 51
発行年
1996-01
抄録（英）
To study nonlinear behavior phenomena in a solid propellant rocket motor one should consider both nonlinear acoustic field and nonlinear interaction between acoustic field and combustion process. The former topic has been discussed in literature rather fully. The latter is not a new one but is not studied in detail. In the work presented a new concept of the higher order burning rate response function to acoustic oscillation with several modes is introduced. Analytical calculations are performed in the framework of Z-N theory. Short introduction in this theory is given. The physical-chemical basis of a very high oscillatory quality of condensed system combustion are discussed. In connection with wide use of highly metallized propellants the linear response function of such propellants is calculated. Two most important examples of the first harmonic self-interaction and the first and second modes interaction are obtained analytically. A relative role of the linear and the higher order response functions is discussed. It is shown that nonlinear effects in combustion must be included in solving solid rocket nonsteady behavior problem.
Solid Propellant Burning Rate Response Functions of Higher Orders
SA0035219.pdf
(2.2MB)
