TY  - 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 . .

TY  - CONF
AU  - Alazeezi, Mohammed
AU  - Elek, Predrag
PY  - 2020
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3376
AB  - Optimizing the nozzle of a solid propellant rocket motor plays an essential rule in the overall performance of the motor. In this paper, the investigation of an optimization model of dual thrust propellant rocket motors will be presented. Due to having two phases of thrust in this type of rocket motors, determination of the rocket nozzle expansion ratio is a non-trivial problem. The idea is to use a simple, fixed length and expansion ratio, convergent-divergent nozzle, which provides the highest total impulse of the motor. Usual assumptions for an ideal rocket motor have been used. The optimization model was developed in MATLAB and calculations has been performed using previously obtained interior ballistic and other relevant data for a dual thrust solid propellant rocket motor.
PB  - Springer International Publishing Ag, Cham
C3  - New Technologies, Development and Application Ii
T1  - Nozzle Optimization of Dual Thrust Rocket Motors
EP  - 477
SP  - 468
VL  - 76
DO  - 10.1007/978-3-030-18072-0_54
ER  - 

@conference{
author = "Alazeezi, Mohammed and Elek, Predrag",
year = "2020",
abstract = "Optimizing the nozzle of a solid propellant rocket motor plays an essential rule in the overall performance of the motor. In this paper, the investigation of an optimization model of dual thrust propellant rocket motors will be presented. Due to having two phases of thrust in this type of rocket motors, determination of the rocket nozzle expansion ratio is a non-trivial problem. The idea is to use a simple, fixed length and expansion ratio, convergent-divergent nozzle, which provides the highest total impulse of the motor. Usual assumptions for an ideal rocket motor have been used. The optimization model was developed in MATLAB and calculations has been performed using previously obtained interior ballistic and other relevant data for a dual thrust solid propellant rocket motor.",
publisher = "Springer International Publishing Ag, Cham",
journal = "New Technologies, Development and Application Ii",
title = "Nozzle Optimization of Dual Thrust Rocket Motors",
pages = "477-468",
volume = "76",
doi = "10.1007/978-3-030-18072-0_54"
}

Alazeezi, M.,& Elek, P.. (2020). Nozzle Optimization of Dual Thrust Rocket Motors. in New Technologies, Development and Application Ii
Springer International Publishing Ag, Cham., 76, 468-477.
https://doi.org/10.1007/978-3-030-18072-0_54

Alazeezi M, Elek P. Nozzle Optimization of Dual Thrust Rocket Motors. in New Technologies, Development and Application Ii. 2020;76:468-477.
doi:10.1007/978-3-030-18072-0_54 .

Alazeezi, Mohammed, Elek, Predrag, "Nozzle Optimization of Dual Thrust Rocket Motors" in New Technologies, Development and Application Ii, 76 (2020):468-477,
https://doi.org/10.1007/978-3-030-18072-0_54 . .

TY  - CONF
AU  - Alazeezi, Mohammed
AU  - Elek, Predrag
PY  - 2019
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4911
AB  - Optimizing the nozzle of a solid propellant rocket motor plays an essential rule in the overall performance of the motor. In this paper, the investigation of an optimization model of dual thrust propellant rocket motors will be presented. Due to having two phases of thrust in this type of rocket motors, determination of the rocket nozzle expansion ratio is a non-trivial problem. The idea is to use a simple, fixed length and expansion ratio, convergent-divergent nozzle, which provides the highest total impulse of the motor. Usual assumptions for an ideal rocket motor have been used. The optimization model was developed in MATLAB and calculations has been performed using previously obtained interior ballistic and other relevant data for a dual thrust solid propellant rocket motor.
PB  - SOCIETY FOR ROBOTICS OF BOSNIA AND HERZEGOVINA
C3  - Proceedings of 5th International Conference "New Technologies, Development, and Application NT-2019", Sarajevo, Bosnia and Hercegovina
T1  - Nozzle optimization of dual thrust rocket motor
SP  - 31
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4911
ER  - 

@conference{
author = "Alazeezi, Mohammed and Elek, Predrag",
year = "2019",
abstract = "Optimizing the nozzle of a solid propellant rocket motor plays an essential rule in the overall performance of the motor. In this paper, the investigation of an optimization model of dual thrust propellant rocket motors will be presented. Due to having two phases of thrust in this type of rocket motors, determination of the rocket nozzle expansion ratio is a non-trivial problem. The idea is to use a simple, fixed length and expansion ratio, convergent-divergent nozzle, which provides the highest total impulse of the motor. Usual assumptions for an ideal rocket motor have been used. The optimization model was developed in MATLAB and calculations has been performed using previously obtained interior ballistic and other relevant data for a dual thrust solid propellant rocket motor.",
publisher = "SOCIETY FOR ROBOTICS OF BOSNIA AND HERZEGOVINA",
journal = "Proceedings of 5th International Conference "New Technologies, Development, and Application NT-2019", Sarajevo, Bosnia and Hercegovina",
title = "Nozzle optimization of dual thrust rocket motor",
pages = "31",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4911"
}

Alazeezi, M.,& Elek, P.. (2019). Nozzle optimization of dual thrust rocket motor. in Proceedings of 5th International Conference "New Technologies, Development, and Application NT-2019", Sarajevo, Bosnia and Hercegovina
SOCIETY FOR ROBOTICS OF BOSNIA AND HERZEGOVINA., 31.
https://hdl.handle.net/21.15107/rcub_machinery_4911

Alazeezi M, Elek P. Nozzle optimization of dual thrust rocket motor. in Proceedings of 5th International Conference "New Technologies, Development, and Application NT-2019", Sarajevo, Bosnia and Hercegovina. 2019;:31.
https://hdl.handle.net/21.15107/rcub_machinery_4911 .

Alazeezi, Mohammed, Elek, Predrag, "Nozzle optimization of dual thrust rocket motor" in Proceedings of 5th International Conference "New Technologies, Development, and Application NT-2019", Sarajevo, Bosnia and Hercegovina (2019):31,
https://hdl.handle.net/21.15107/rcub_machinery_4911 .

TY  - CONF
AU  - Alazeezi, Mohammed
AU  - Elek, Predrag
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/4585
AB  - Burnback analysis is a critical stage in the design of solid propellant rocket motors. This paper will focus on investigating the burnback analysis of an end burner grain with central cylindrical cavity. Analytical and numerical methods for evaluating the burning surface area have been used. The analytical geometrical equations that illustrate the burning surface area evolution were developed for the two-phase burning process. The first phase is the boost phase and the second phase is the sustaining which lasts longer. A parametric model of the grain was also created in PTC Creo to simulate the burn back numerically. The results from both methods show an agreement which approves that the numerical method could be used for complex grain shapes, for which it is difficult to obtain the analytical solution. Furthermore, a MATLAB program was developed in order to compare the numerical and analytical results and to predict some of the main interior
ballistics parameters.
PB  - Belgrade : Military Technical Institute
C3  - 8th International Scientific Conference on Defensive Technologies OTEH 2018, Belgrade 11-12 October
T1  - Analytical and numerical burnback analysis of end burner grain with cylindrical cavity
EP  - 188
SP  - 184
UR  - https://hdl.handle.net/21.15107/rcub_machinery_4585
ER  - 

@conference{
author = "Alazeezi, Mohammed and Elek, Predrag",
year = "2018",
abstract = "Burnback analysis is a critical stage in the design of solid propellant rocket motors. This paper will focus on investigating the burnback analysis of an end burner grain with central cylindrical cavity. Analytical and numerical methods for evaluating the burning surface area have been used. The analytical geometrical equations that illustrate the burning surface area evolution were developed for the two-phase burning process. The first phase is the boost phase and the second phase is the sustaining which lasts longer. A parametric model of the grain was also created in PTC Creo to simulate the burn back numerically. The results from both methods show an agreement which approves that the numerical method could be used for complex grain shapes, for which it is difficult to obtain the analytical solution. Furthermore, a MATLAB program was developed in order to compare the numerical and analytical results and to predict some of the main interior
ballistics parameters.",
publisher = "Belgrade : Military Technical Institute",
journal = "8th International Scientific Conference on Defensive Technologies OTEH 2018, Belgrade 11-12 October",
title = "Analytical and numerical burnback analysis of end burner grain with cylindrical cavity",
pages = "188-184",
url = "https://hdl.handle.net/21.15107/rcub_machinery_4585"
}

Alazeezi, M.,& Elek, P.. (2018). Analytical and numerical burnback analysis of end burner grain with cylindrical cavity. in 8th International Scientific Conference on Defensive Technologies OTEH 2018, Belgrade 11-12 October
Belgrade : Military Technical Institute., 184-188.
https://hdl.handle.net/21.15107/rcub_machinery_4585

Alazeezi M, Elek P. Analytical and numerical burnback analysis of end burner grain with cylindrical cavity. in 8th International Scientific Conference on Defensive Technologies OTEH 2018, Belgrade 11-12 October. 2018;:184-188.
https://hdl.handle.net/21.15107/rcub_machinery_4585 .

Alazeezi, Mohammed, Elek, Predrag, "Analytical and numerical burnback analysis of end burner grain with cylindrical cavity" in 8th International Scientific Conference on Defensive Technologies OTEH 2018, Belgrade 11-12 October (2018):184-188,
https://hdl.handle.net/21.15107/rcub_machinery_4585 .