折叠翼展开到位碰撞特性分析

Impact Characteristics of the Folded-Deploying Wing

运用理论力学中的碰撞理论对折叠翼到位展开时的瞬时碰撞问题进行理论分析,采用MSC.Adams多体动力学虚拟样机软件对折叠翼到位的接触碰撞局部动力学过程进行数值模拟,用碰撞力函数描述减震垫与弹翼的碰撞作用,给出了力函数参数的确定方法。分析结果表明:本文的建模方法适合从理论上和数值模拟方面给出折叠翼展开到位的碰撞特性;针对燃烧室压强14 MPa典型设计工况,通过分析弹翼与减震垫在1 mm碰撞行程内的动力学特性,得到碰撞时间为2.3 ms,碰撞力的峰值为905 N,小于设计上限4 000 N,符合碰撞力峰值的安全性要求;作动筒燃气压力是影响碰撞过程中峰值碰撞载荷的主要因素。

In the article, impact theory was applied to analyze the problem of transient collisions when folded wing deploying to expected position, the dynamics process of the partial contact impact was numerical simulated by the multibody dynamics software ADAMS, and impact function was used to express the force action between cushion and wing. Meanwhile, the parameters of the force action were determinate. The model method properly obtains the impact characteristic of foldedwing from theory and numerical simulation. Then the dynamic characteristic was ana lyzed in the penetration depth 1 mm process between cushion and wing for the combustor classic pressure of 14 MPa. The contact impact time of 2.3 ms and the peak impact force of 905 N were obtained, respectively. The results were satisfying the safety margin. The combustor pressure was the main factor for the peak impact force through the analy sis, and the conclusion was a certain reference value for foldedwing engineering design.