载机滚转条件下的导弹弹射分离横向位移研究

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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.

Key words： rotary aircraft quasi-coordinates lateral deformation embedded ejection stiffness matching launching safety.

Received: 03 January 2018 Published: 28 June 2019

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	Articles by authors
	LIU Hao1
	ZHOU Jun1
	ZHANG Shiwei2
	QI Zijiang2

Cite this article:

LIU Hao1,ZHOU Jun1,ZHANG Shiwei2, et al. Lateral displacement of missile ejection separation with aircraft rolling[J]. JOURNAL OF VIBRATION AND SHOCK, 2019, 38(13): 1-6.

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http://jvs.sjtu.edu.cn/EN/ OR http://jvs.sjtu.edu.cn/EN/Y2019/V38/I13/1

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