Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines
Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of th...
| Main Authors: | , |
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| Format: | Article |
| Language: | fas |
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Aerospace Research Institute
2023-05-01
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| Series: | فصلنامه علوم و فناوری فضایی |
| Subjects: | |
| Online Access: | https://jsst.ias.ir/article_166663_0299a59da402e3ce9c61c9e76e4f63c1.pdf |
| _version_ | 1827251513676791808 |
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| author | Vahid Rahimi Ghoradel Hossein Mahdavy-Moghaddam |
| author_facet | Vahid Rahimi Ghoradel Hossein Mahdavy-Moghaddam |
| author_sort | Vahid Rahimi Ghoradel |
| collection | DOAJ |
| description | Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the warhead by enemy agents. In such a situation, after completing the engine mission, the mechanism of separating the steps and separating the head from the body is used. One of the separation methods is to use the thrust termination system method. In this paper, with the studies performed on the thrust termination system and the presentation of mathematical relations, the pressure drop and inverse thrust created in the chamber after opening the reverse thrust valves are predicted. Also, cold type separation and thrust termination system were used and the combustion chamber pressure drop is simulated. Then, the effect of important and influential factors on the thrust termination system has been investigated. |
| first_indexed | 2024-03-08T13:38:34Z |
| format | Article |
| id | doaj.art-b44548d368c74083bac7826aee6af8e2 |
| institution | Directory Open Access Journal |
| issn | 2008-4560 2423-4516 |
| language | fas |
| last_indexed | 2025-03-22T00:20:38Z |
| publishDate | 2023-05-01 |
| publisher | Aerospace Research Institute |
| record_format | Article |
| series | فصلنامه علوم و فناوری فضایی |
| spelling | doaj.art-b44548d368c74083bac7826aee6af8e22024-05-15T11:57:38ZfasAerospace Research Instituteفصلنامه علوم و فناوری فضایی2008-45602423-45162023-05-0116211710.30699/jsst.2023.1409166663Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel EnginesVahid Rahimi Ghoradel0Hossein Mahdavy-Moghaddam1M.Sc. Student, Faculty of Aerospace Engineering, K. N. Toosi University of Technology,Tehran, IranAssociate Professor, Faculty of Aerospace Engineering, K. N. Toosi University of Technology,Tehran, IranEach missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the warhead by enemy agents. In such a situation, after completing the engine mission, the mechanism of separating the steps and separating the head from the body is used. One of the separation methods is to use the thrust termination system method. In this paper, with the studies performed on the thrust termination system and the presentation of mathematical relations, the pressure drop and inverse thrust created in the chamber after opening the reverse thrust valves are predicted. Also, cold type separation and thrust termination system were used and the combustion chamber pressure drop is simulated. Then, the effect of important and influential factors on the thrust termination system has been investigated.https://jsst.ias.ir/article_166663_0299a59da402e3ce9c61c9e76e4f63c1.pdfreverse thrustcold type separationthrust termination systemchamber pressure drop |
| spellingShingle | Vahid Rahimi Ghoradel Hossein Mahdavy-Moghaddam Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines فصلنامه علوم و فناوری فضایی reverse thrust cold type separation thrust termination system chamber pressure drop |
| title | Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines |
| title_full | Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines |
| title_fullStr | Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines |
| title_full_unstemmed | Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines |
| title_short | Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines |
| title_sort | simulation and parametric analysis of thrust reverser system in solid fuel engines |
| topic | reverse thrust cold type separation thrust termination system chamber pressure drop |
| url | https://jsst.ias.ir/article_166663_0299a59da402e3ce9c61c9e76e4f63c1.pdf |
| work_keys_str_mv | AT vahidrahimighoradel simulationandparametricanalysisofthrustreversersysteminsolidfuelengines AT hosseinmahdavymoghaddam simulationandparametricanalysisofthrustreversersysteminsolidfuelengines |