载机滚转条件下的导弹弹射分离横向位移研究

Translated title of the contribution: Lateral displacement of missile ejection separation with aircraft rolling

Hao Liu, Jun Zhou, Shiwei Zhang, Zijiang Qi

Research output: Contribution to journalArticlepeer-review

1 Scopus citations

Abstract

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.

Translated title of the contributionLateral displacement of missile ejection separation with aircraft rolling
Original languageChinese (Traditional)
Pages (from-to)1-6
Number of pages6
JournalZhendong yu Chongji/Journal of Vibration and Shock
Volume38
Issue number13
DOIs
StatePublished - 15 Jul 2019

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