Fast Reactions in Energetic Materials. High-Temperature Decomposition of Rocket Propellants and Explosives

Shteinberg, Alexander S. Translated from Russian by Maria Rusanova

ISBN 10: 3540788603 / ISBN 13: 9783540788607

Published by Springer, Berlin, 2008

About this Item

xiv + 201 pp. Rubber-stamped on front free endpaper.

Seller Inventory # 24456

Bibliographic Details

• Title: Fast Reactions in Energetic Materials. High-Temperature Decomposition of Rocket Propellants and Explosives
• Publisher: Springer, Berlin
• Publication Date: 2008
• Language: English
• ISBN 10: 3540788603
• ISBN 13: 9783540788607
• Binding: Hardback
• Condition: Very Good
• Dust Jacket Condition: jacketcondition
• Book Type: book
• Seller catalogs:
  • Chemistry

About this title

Synopsis

Modern energetic materials include explosives, blasting powders, pyrotechnic m- tures and rocket propellants [1, 2]. The study of high-temperature decomposition of condensed phases of propellants and their components (liquid, solid and hybrid) is currently of special importance for the development of space-system engineering [3, 4]. To better understand the burning mechanisms (stationary, nonstationary, - steady) of composite solid propellants and their components, information about the macrokinetics of their high-temperature decomposition is required [5]. To be able to evaluate the ignition parameters and conditions of safe handling of heat-affected explosives, one needs to know the kinetic constants of their high-temperature - composition. The development of new composite solid propellants characterized by high performance characteristics (high burning rates, high thermal stability, stability to intrachamber perturbations, and other aspects) is not possible without quanti- tive data on the high-temperature decomposition of composite solid propellants and their components [6]. The same reasons have resulted in signi?cant theoretical and practical interest in the high-temperature decomposition of components of hybrid propellants. It is known that hybrid propellants have not been used very widely due to the low bu- ing (pyrolysis) rates of the polymer blocks in the combustion chambers of hybrid rocket engines. To increase the burning rates it is necessary to obtain information about their relationships to the corresponding kinetic and thermophysical prop- ties of the fuels.