摘要
Here, lateral displacement of an air-to-air missile ejection separation with aircraft rolling was studied. Using Lagrange's equations in form of quasi-coordinates, a dynamic model for high-speed stretching process of an airborne ejection launcher was established. Dynamic characteristics of missile ejection separation with aircraft rolling were numerically simulated. The results showed that the missile ejection separation speed is normal, but the lateral deformation of the airborne ejection launcher is significant due to the action of Coriolis force to cause large later displacement of the missile tail, and threat the separation safety between aircraft and ejected missile. Due to constraints of weight and space as well as very short ejection actuation time, the traditional mechanism stiffness-enhancing method and the active control method were difficult to implement in engineering. For this difficult problem, a new idea to do a stiffness matching design for front and rear links of the ejection launcher was proposed. Simulations and tests showed that this method is effective and easy to realize in engineering; it provides a theoretical guidance for missile ejection under the condition of aircraft rolling.
投稿的翻译标题 | Lateral displacement of missile ejection separation with aircraft rolling |
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源语言 | 繁体中文 |
页(从-至) | 1-6 |
页数 | 6 |
期刊 | Zhendong yu Chongji/Journal of Vibration and Shock |
卷 | 38 |
期 | 13 |
DOI | |
出版状态 | 已出版 - 15 7月 2019 |
关键词
- Aircraft rolling
- Ejection safety
- Embedded ejection
- Lateral displacement
- Quasi-coordinates
- Stiffness matching