直升机机体结构减振优化设计

Vibration Reduction Optimization Design of Helicopter Body Structure

直升机在飞行过程中,由于旋翼空气动力学环境及结构的特殊性,旋翼桨叶受到周期性的气动载荷使桨叶产生弹性振动,在桨叶内部引起结构振动载荷,其振动载荷沿桨毂传到机体上,引起机体的振动响应,从而形成直升机严重的振动问题。为了解决直升机机体的振动问题,基于Patran/Nastran有限元软件,对型号直升机机身进行动力学特性分析,研究旋翼载荷和机体结构等方面对机体振动的影响,并集成Isight优化软件对其进行结构优化分析,从而达到机体减振的效果。

During the flight of the helicopter,due to the particularity of the aerodynamic environment and structure of the rotor,the rotor blades are subjected to periodic aerodynamic loads to cause the blade to generate elastic vibrations,causing structural vibration loads inside the blades.The vibration load is transmitted along the hub to the body,causing the body’s vibration response,thus forming a serious vibration problem for helicopters.In order to solve the vibration problem of helicopter airframe,this paper analyzes the dynamic characteristics of helicopter airframe based on Patran/Nastran finite element software,studies the influence of rotor load and airframe structure on airframe vibration,and integrates Isight optimization software to optimize its structure,so as to achieve the effect of airframe vibration reduction.