Two-component propellant grain for rocket motor combustion analysis and geometric optimization
Апстракт
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 pre...ssure data shows very good agreement. Therefore, two-component propellant grains have significant application possibilities using the suggested modeling approaches.
Кључне речи:
two-component grain / solid propellant / rocket propulsion / possibilities using suggested modeling approaches / optimization / grain geometryИзвор:
Thermal Science, 2022, 26, 2, 1567-1578Издавач:
- Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
DOI: 10.2298/TSCI210604290A
ISSN: 0354-9836
WoS: 000791221600026
Scopus: 2-s2.0-85126919544
Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Alazeezi, Mohammed AU - Popović, Nikola P. AU - Elek, Predrag PY - 2022 UR - https://machinery.mas.bg.ac.rs/handle/123456789/3788 AB - 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. PB - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd T2 - Thermal Science T1 - Two-component propellant grain for rocket motor combustion analysis and geometric optimization EP - 1578 IS - 2 SP - 1567 VL - 26 DO - 10.2298/TSCI210604290A ER -
@article{ author = "Alazeezi, Mohammed and Popović, Nikola P. and Elek, Predrag", year = "2022", abstract = "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.", publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd", journal = "Thermal Science", title = "Two-component propellant grain for rocket motor combustion analysis and geometric optimization", pages = "1578-1567", number = "2", volume = "26", doi = "10.2298/TSCI210604290A" }
Alazeezi, M., Popović, N. P.,& Elek, P.. (2022). Two-component propellant grain for rocket motor combustion analysis and geometric optimization. in Thermal Science Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 26(2), 1567-1578. https://doi.org/10.2298/TSCI210604290A
Alazeezi M, Popović NP, Elek P. Two-component propellant grain for rocket motor combustion analysis and geometric optimization. in Thermal Science. 2022;26(2):1567-1578. doi:10.2298/TSCI210604290A .
Alazeezi, Mohammed, Popović, Nikola P., Elek, Predrag, "Two-component propellant grain for rocket motor combustion analysis and geometric optimization" in Thermal Science, 26, no. 2 (2022):1567-1578, https://doi.org/10.2298/TSCI210604290A . .