Open AccessTwo-component propellant grain for rocket motor: Combustion analysis and geometric optimization
Author(s) -
Mohammed Alazeezi,
Nikola Popović,
Predrag Elek
Publication year - 2022
Publication title -
thermal science/thermal science
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.339
H-Index - 43
eISSN - 2334-7163
pISSN - 0354-9836
DOI - 10.2298/tsci210604290a
Subject(s) - propellant , solid fuel rocket , rocket (weapon) , aerospace engineering , materials science , combustion , rocket propellant , component (thermodynamics) , surface (topology) , process (computing) , mechanics , combustion products , mechanical engineering , thermodynamics , geometry , computer science , physics , chemistry , mathematics , engineering , operating system
The paper considers utilization of rocket motor propellant grains that consist of two propellants. The idea is to achieve approximately neutral burning using an outer surface inhibited cylindrical shape and complex contact surface between propellants. An existing propellant grain with complex geometry has been analytically modeled in terms of determination of evolution of corresponding burning surface areas. The analytical and experimental results? diagrams of this grain have been found to have a saw-tooth shape because of the segments that separate the two propellants, causing potential problems in the burning process during the relatively short active phase, showing an obvious need for further optimization. This has created an opportunity for development of improved propellant grain geometry and corresponding mathematical model for determination of main interior ballistic parameters. Comparison between calculation results based on both models and experimentally determined chamber pressure data shows very good agreement. Therefore, two-component propellant grains have significant application possibilities using the suggested modeling approaches.