| 高速风洞投放试验弹射机构及试验研究 |
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| 引用本文： | 王帅,董金刚,张晨凯,赵星宇,谢峰.高速风洞投放试验弹射机构及试验研究[J].实验流体力学,2021,35(6):73-78. |
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| 作者姓名： | 王帅 董金刚 张晨凯 赵星宇 谢峰 |
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| 作者单位： | 中国航天空气动力技术研究院，北京 100074 |
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| 基金项目： | 国家数值风洞工程（NNW） |
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| 摘 要： | 新一代战斗机超声速内埋武器投放需要进行分离安全性评估。针对内埋武器高速风洞投放试验的需求，设计了一套新型双气缸弹射机构。使用三维建模软件开展了弹射机构的结构设计。基于气缸无杆/有杆腔内压力方程、储气罐与无杆腔流量方程、有杆腔与大气相连的流量方程以及活塞驱动力方程等，建立了弹射过程的数学模型，并利用运动仿真软件对所设计的弹射机构进行仿真分析，验证了结构的合理性。设计了弹射机构伺服控制系统，利用电气伺服阀及相关控制元件实现对弹射机构的控制。在中国航天空气动力技术研究院FD-12风洞中开展了试验验证（马赫数1.5）。结果表明:当前后气缸压力不超过1.0 MPa时，载弹最大弹射速度可达5.68 m/s，满足设计要求与使用需求。
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| 关 键 词： | 投放试验 弹射机构 风洞试验 运动仿真 内埋武器 |
| 收稿时间： | 2020-12-01 |
The study of ejection mechanism and drop-test in high-speed wind tunnel |
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| Affiliation: | China Academy of Aerospace Aerodynamics, Beijing 100074, China |
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| Abstract: | It is necessary to evaluate the separation safety of supersonic embedded weapons for the new generation fighter. According to the requirements of high-speed wind tunnel launching test of embedded weapons, a new type of double cylinder ejection mechanism is designed, which can realize the continuously adjustment of the initial velocity and the initial angular velocity. Firstly, the NX modeling software is used to design the structural and three-dimensional modeling of the ejection mechanism. Secondly, based on the pressure equations of the cylinder rod free cavity and rod cavity, and the flow equation of the rod free cavity and rod cavity connected with the atmosphere and the piston driving force equation, the mathematical model of the ejection process was established, and the design of the ejection mechanism was simulated and analyzed by using the motion simulation software to verify the rationality of the structure. According to the control requirements of the ejection mechanism, the servo control system of the ejection mechanism was designed by using the electric servo valve and related control elements. Finally, the wind tunnel test of Mach 1.5 was carried out. The experiment shows that the maximum ejection speed of the model can reach 5.68 m/s under the condition that the air pressure is not more than 1.0 MPa, and the initial attitude of the carrier is close to the simulation results, which can meet the design and use requirements. |
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