Nozzle optimization of dual thrust rocket motor
Апстракт
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:
optimization / convergent-divergent nozzle / rocket propulsion / dual thrustИзвор:
Proceedings of 5th International Conference "New Technologies, Development, and Application NT-2019", Sarajevo, Bosnia and Hercegovina, 2019, 31-Издавач:
- SOCIETY FOR ROBOTICS OF BOSNIA AND HERZEGOVINA
Финансирање / пројекти:
Колекције
Институција/група
Mašinski fakultetTY - 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 .