Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket
The flight performance and flight trajectory of any unguided rocket should be determined because its capability and flight trajectory are uncountable in flights. The purpose in this study was to develop a performance and trajectory prediction program for an unguided 2.75-inch solid propellant rocket...
| Main Authors: | , , , , , , |
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| Format: | Conference or Workshop Item |
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Springer Science and Business Media
2024
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| Online Access: | http://psasir.upm.edu.my/id/eprint/116615/ |
| _version_ | 1848867737068109824 |
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| author | Hamlan, Nur Syahirah Shafek Gires, Ezanee Ahmad, Kamarul Ariffin Mustapha, Faizal Mazlan, Norkhairunnisa Yidris, Noorfaizal Basri, Adi Azriff |
| author_facet | Hamlan, Nur Syahirah Shafek Gires, Ezanee Ahmad, Kamarul Ariffin Mustapha, Faizal Mazlan, Norkhairunnisa Yidris, Noorfaizal Basri, Adi Azriff |
| author_sort | Hamlan, Nur Syahirah Shafek |
| building | UPM Institutional Repository |
| collection | Online Access |
| description | The flight performance and flight trajectory of any unguided rocket should be determined because its capability and flight trajectory are uncountable in flights. The purpose in this study was to develop a performance and trajectory prediction program for an unguided 2.75-inch solid propellant rocket and to perform a parametric analysis. The program uses the Runge–Kutta Fehlberg (or RKF45) method, and it was developed using Python. It requires multiple geometric designs and motor parameters as the program input. The program was then verified and validated with previous experimental flight data obtained from literature papers. Then, a parametric analysis (also called as sensitivity analysis) was done to analyze how significant these parameters affect the flight of a rocket, compared with the results based on the baseline rocket. Based on the prediction results, the baseline rocket flies with a range of 3040 m, reaches up to 3307 m in altitude and has a peak velocity of 747.554 m/s. In parametric analysis, the parameter that gave the most significant difference was motor grain configuration, followed by launch angle and nozzle expansion ratio. |
| first_indexed | 2025-11-15T14:41:15Z |
| format | Conference or Workshop Item |
| id | upm-116615 |
| institution | Universiti Putra Malaysia |
| institution_category | Local University |
| last_indexed | 2025-11-15T14:41:15Z |
| publishDate | 2024 |
| publisher | Springer Science and Business Media |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | upm-1166152025-08-12T00:49:47Z http://psasir.upm.edu.my/id/eprint/116615/ Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket Hamlan, Nur Syahirah Shafek Gires, Ezanee Ahmad, Kamarul Ariffin Mustapha, Faizal Mazlan, Norkhairunnisa Yidris, Noorfaizal Basri, Adi Azriff The flight performance and flight trajectory of any unguided rocket should be determined because its capability and flight trajectory are uncountable in flights. The purpose in this study was to develop a performance and trajectory prediction program for an unguided 2.75-inch solid propellant rocket and to perform a parametric analysis. The program uses the Runge–Kutta Fehlberg (or RKF45) method, and it was developed using Python. It requires multiple geometric designs and motor parameters as the program input. The program was then verified and validated with previous experimental flight data obtained from literature papers. Then, a parametric analysis (also called as sensitivity analysis) was done to analyze how significant these parameters affect the flight of a rocket, compared with the results based on the baseline rocket. Based on the prediction results, the baseline rocket flies with a range of 3040 m, reaches up to 3307 m in altitude and has a peak velocity of 747.554 m/s. In parametric analysis, the parameter that gave the most significant difference was motor grain configuration, followed by launch angle and nozzle expansion ratio. Springer Science and Business Media 2024 Conference or Workshop Item PeerReviewed Hamlan, Nur Syahirah Shafek and Gires, Ezanee and Ahmad, Kamarul Ariffin and Mustapha, Faizal and Mazlan, Norkhairunnisa and Yidris, Noorfaizal and Basri, Adi Azriff (2024) Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket. In: 2nd International Seminar on Aeronautics and Energy, 17 Sept. 2022 (pp. 175-184). https://link.springer.com/chapter/10.1007/978-981-99-6874-9_14 10.1007/978-981-99-6874-9_14 |
| spellingShingle | Hamlan, Nur Syahirah Shafek Gires, Ezanee Ahmad, Kamarul Ariffin Mustapha, Faizal Mazlan, Norkhairunnisa Yidris, Noorfaizal Basri, Adi Azriff Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| title | Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| title_full | Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| title_fullStr | Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| title_full_unstemmed | Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| title_short | Flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| title_sort | flight performance and trajectory prediction of a 2.75-inch solid propellant rocket |
| url | http://psasir.upm.edu.my/id/eprint/116615/ http://psasir.upm.edu.my/id/eprint/116615/ http://psasir.upm.edu.my/id/eprint/116615/ |