载机滚转条件下的导弹弹射分离横向位移研究

Hao Liu, Jun Zhou, Shiwei Zhang, Zijiang Qi

科研成果: 期刊稿件文章同行评审

1 引用 (Scopus)

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
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
38
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

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