Analysis and design of a fixed wing unmanned aerial vehicle gas launching system
In order to meet the development requirements of unmanned aerial vehicle (UAV) boosters, a detachable launch booster for fixed wing UAVs was designed, which is driven by high-pressure carbon dioxide gas. A mathematical model for gas launch was established based on the internal ballistic equation of...
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Editorial Office of Command Control and Simulation
2025-02-01
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| Series: | Zhihui kongzhi yu fangzhen |
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| Online Access: | https://www.zhkzyfz.cn/fileup/1673-3819/PDF/1737421348761-690149133.pdf |
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| author | LI Xiang, LI Qiang, WANG Teng, WANG Shaoquan, ZHANG Shiyu |
| author_facet | LI Xiang, LI Qiang, WANG Teng, WANG Shaoquan, ZHANG Shiyu |
| author_sort | LI Xiang, LI Qiang, WANG Teng, WANG Shaoquan, ZHANG Shiyu |
| collection | DOAJ |
| description | In order to meet the development requirements of unmanned aerial vehicle (UAV) boosters, a detachable launch booster for fixed wing UAVs was designed, which is driven by high-pressure carbon dioxide gas. A mathematical model for gas launch was established based on the internal ballistic equation of the gas cannon. Through theoretical calculations and the use of dynamic simulation software ADAMS to simulate the designed 3D model, the variation laws of initial velocity, overload, displacement, etc. during the launch of unmanned aerial vehicles of different masses were obtained. The results show that the initial velocity, displacement, and overload variation curves obtained through simulation when the drone leaves the launch pad are highly consistent with the theoretical calculation results, verifying the correctness of the calculation and simulation. The research results indicate that the fixed wing unmanned aerial vehicle (UAV) booster launcher can successfully launch UAVs weighing 14 kg or less and achieve initial takeoff speed without exceeding maximum overload. The simulation results have an error of no more than 3% compared to theoretical calculations. The research results can further provide theoretical guidance for gas emission. |
| format | Article |
| id | doaj-art-c91bfeb053fc4afa8e87147e4a9e09bb |
| institution | Kabale University |
| issn | 1673-3819 |
| language | zho |
| publishDate | 2025-02-01 |
| publisher | Editorial Office of Command Control and Simulation |
| record_format | Article |
| series | Zhihui kongzhi yu fangzhen |
| spelling | doaj-art-c91bfeb053fc4afa8e87147e4a9e09bb2025-01-21T11:12:00ZzhoEditorial Office of Command Control and SimulationZhihui kongzhi yu fangzhen1673-38192025-02-01471323710.3969/j.issn.1673-3819.2025.01.004Analysis and design of a fixed wing unmanned aerial vehicle gas launching systemLI Xiang, LI Qiang, WANG Teng, WANG Shaoquan, ZHANG Shiyu0College of Mechanical and Electrical Engineering, North University of China, Taiyuan 030051, ChinaIn order to meet the development requirements of unmanned aerial vehicle (UAV) boosters, a detachable launch booster for fixed wing UAVs was designed, which is driven by high-pressure carbon dioxide gas. A mathematical model for gas launch was established based on the internal ballistic equation of the gas cannon. Through theoretical calculations and the use of dynamic simulation software ADAMS to simulate the designed 3D model, the variation laws of initial velocity, overload, displacement, etc. during the launch of unmanned aerial vehicles of different masses were obtained. The results show that the initial velocity, displacement, and overload variation curves obtained through simulation when the drone leaves the launch pad are highly consistent with the theoretical calculation results, verifying the correctness of the calculation and simulation. The research results indicate that the fixed wing unmanned aerial vehicle (UAV) booster launcher can successfully launch UAVs weighing 14 kg or less and achieve initial takeoff speed without exceeding maximum overload. The simulation results have an error of no more than 3% compared to theoretical calculations. The research results can further provide theoretical guidance for gas emission.https://www.zhkzyfz.cn/fileup/1673-3819/PDF/1737421348761-690149133.pdfuav|launch frame|gas emission|structural design|dynamics simulation |
| spellingShingle | LI Xiang, LI Qiang, WANG Teng, WANG Shaoquan, ZHANG Shiyu Analysis and design of a fixed wing unmanned aerial vehicle gas launching system Zhihui kongzhi yu fangzhen uav|launch frame|gas emission|structural design|dynamics simulation |
| title | Analysis and design of a fixed wing unmanned aerial vehicle gas launching system |
| title_full | Analysis and design of a fixed wing unmanned aerial vehicle gas launching system |
| title_fullStr | Analysis and design of a fixed wing unmanned aerial vehicle gas launching system |
| title_full_unstemmed | Analysis and design of a fixed wing unmanned aerial vehicle gas launching system |
| title_short | Analysis and design of a fixed wing unmanned aerial vehicle gas launching system |
| title_sort | analysis and design of a fixed wing unmanned aerial vehicle gas launching system |
| topic | uav|launch frame|gas emission|structural design|dynamics simulation |
| url | https://www.zhkzyfz.cn/fileup/1673-3819/PDF/1737421348761-690149133.pdf |
| work_keys_str_mv | AT lixiangliqiangwangtengwangshaoquanzhangshiyu analysisanddesignofafixedwingunmannedaerialvehiclegaslaunchingsystem |