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某型飞机在使用过程中,多次发生配重组件破损,滚柱飞出而击伤发动机,严重威胁飞行安全.为分析配重组件破损的原因,基于配重的工作原理,分析了发动机油门快速操纵对曲轴扭转振动的影响,依据扭纵耦合理论,对滚柱冲击挡片的机理进行了研究,并完成了试验验证.建立了配重组件在冲击载荷作用下的有限元计算模型,并对配重组件进行了机械性能测试,采用疲劳强度安全系数法,完成了配重组件的强度分析.研究结果表明,发动机油门的快速操纵引起配重摆动角度过大,配重为非线性摆动,其摆动频率与曲转扭转振动频率差异过大,配重消除曲轴扭转振动效果差,曲轴产生剧烈的扭转共振,扭转振动耦合成轴向振动,造成滚柱高频冲击挡片.在冲击载荷作用下,挡片的疲劳强度最小,最易发生疲劳破损,可适当改善其疲劳强度,提高配重组件不发生疲劳破损的可靠性.
In the course of using a certain type of aircraft, the weight components are damaged several times, the rollers fly out to injure the engine, which seriously threaten the flight safety.In order to analyze the cause of the damage of the weight components, based on the working principle of the weight, the engine throttle The influence of rapid manipulations on the torsional vibration of the crankshaft, the mechanism of the impact plate of the roller was studied based on the torsional-longitudinal coupling theory, and the experimental verification was completed.The finite element calculation model of the counterweight assembly under impact load The mechanical performance of the counterweight component was tested and the fatigue strength safety factor method was adopted to finish the strength analysis of the counterweight component.The results show that the rapid manipulation of the engine throttle causes the counterweight swinging angle to be too large and the counterweight to vibrate nonlinearly, Its swing frequency and torsional torsional vibration frequency difference is too large, counterbalance to eliminate crankshaft torsional vibration effect is poor, the crankshaft produces severe torsional resonance, torsional vibration coupled into axial vibration, resulting in high-frequency roller impact blanket in the impact of the role of load Under the block the smallest fatigue strength, the most prone to fatigue damage, may be appropriate to improve its fatigue strength, weight components to improve the reliability of fatigue damage does not occur.