摘要
机翼垂向大变形会导致航向载荷加载力线方向发生变化,引起附加载荷,从而影响试验加载精度。为了真实模拟机翼航向受载状态,航向载荷的施加需要根据机翼的变形实时调整加载方向,确保大变形下航向加载力线方向与实际受载方向始终一致。为了满足试验要求,提出一种考虑机翼变形的主动反馈式双力控机翼航向自适应加载技术,基于机翼大变形的主动反馈,结合力的矢量合成原理,通过2个力控加载作动筒实时主动控制保证机翼航向加载的大小与方向,从而解决机翼大变形下航向载荷施加难题。通过设计模拟试验验证了新方法的可行性、有效性和实用性。最后将所提技术成功应用于某型号稳定俯仰2.5 g工况限制载荷静力试验。结果表明:此技术能够有效实现大变形机翼航向载荷的随动加载,提升了试验的加载精度。
The large vertical deformation of the wing will cause the direction of the loading force line of the heading load to change,causing additional loads in other directions,thus affecting the loading accuracy of the test.The heading load needs to adjust the loading direction in real time according to the deformation of the wing,so as to ensure that the direction of the heading loading force line is consistent with the actual load direction.In order to simulate the heading load state of the wing,the heading load needs to adjust the loading direction in real time according to the deformation of the wing,to ensure that the direction of the heading loading force line is consistent with the actual load under large deformation.In order to meet the test requirements,an active feedback dual force-controlled wing heading adaptive loading technology considering the deformation of the wing was proposed.Based on the active feedback of large deformation of the wing,combined with the principle of force vector synthesis,the size and direction of the wing heading loading were actively controlled by two force control loading driving cylinders in real time,so as to solve the problem of heading load application under large deformation of the wing.Then a simulation test was designed to verify the feasibility,effectiveness and practicability of the new method.Finally,the proposed technology was successfully applied to the certain static test of the model′s stable pitch under the 2.5 g working condition limit load.The results show that the proposed technology can effectively realize the follow-up loading of large deformation wing heading load,and improve the loading accuracy of the test.
作者
陈超
王刚
张柁
CHEN Chao;WANG Gang;ZHANG Tuo(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi′an Shaanxi 710065,China)
出处
《机床与液压》
北大核心
2024年第20期84-89,共6页
Machine Tool & Hydraulics
基金
航空科学基金(2016ZD23017)。
关键词
机翼大变形
自适应加载
航向载荷
主动反馈
large deformation of the wing
adaptive loading
heading load
active feedback
