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Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Печать: 2150-766X
ISSN Онлайн: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2014001411
pages 97-110


Rodrigo R. Rapozo
GAC-AFS, P.O. Box 69037, 0169, Pretoria, South Africa and Instituto Tecnologico de Aeronautica, Praca Marechal Eduardo Gomes, 50 Vila das Acacias, Sao Jose dos Campos, SP, Brazil

Краткое описание

A review of one-dimensional steady-state equations was performed for the flow in a subsonic blast tube/tailpipe of a rocket motor. Assuming a constant diameter and only frictional losses, the analytical model that was derived from these equations is discussed. A simplified, semi-analytical model regarding internal ballistic effects was developed and is presented in spite of the complex set of chemical reactions between the combustion products from the motor chamber and the ablative liner, char-layer formation, and wall roughness variation. The trend of tailpipes leads to overestimating the characteristic velocity (C*) of the propellant and underestimating the thrust coefficient (CF) due to new stagnation conditions. Even for bell-shaped nozzles, the raw data after static firing tests have shown an appreciable loss in their performance. Some considerations have to be taken into account to compensate for these perturbations without jeopardizing the overall performance. The findings of this study are validated with data from firings of a real low-smoke propellant solid rocket motor.