Nozzle Optimization of Dual Thrust Rocket Motors
Само за регистроване кориснике
2020
Конференцијски прилог (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
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.
Кључне речи:
Rocket propulsion / Optimization / Dual thrust / Convergent-divergent nozzleИзвор:
New Technologies, Development and Application Ii, 2020, 76, 468-477Издавач:
- Springer International Publishing Ag, Cham
DOI: 10.1007/978-3-030-18072-0_54
ISSN: 2367-3370
WoS: 000494447600054
Scopus: 2-s2.0-85065421317
Колекције
Институција/група
Mašinski fakultetTY - 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 . .