桨叶根部段静强度试验控制方法研究  

Study of Control Method for Blade Root Static Test

作　　者：陈淑平[1] 曹发胜[1] CHEN Shuping CAO Fasheng(China Helicopter Research and Development Institute, Jingdezhen 333001, China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2017年第3期55-59,共5页Helicopter Technique

摘　　要：桨叶根部段静强度试验力控制方案中,由于各通道力载荷间存在交叉耦合现象,造成各方向作动器施加力载荷与试件实际受载情况不一致,试验过程中需要对各通道控制载荷进行修正计算,存在试验周期长,无法保证等比例加载等缺点。针对上述问题,选取某直升机复合材料桨叶根段结构,以其真实受载情况作为分析对象,以应变作为控制参数,在挥舞、摆振通道引入应变控制方式,提出力控制和应变控制相结合的联合控制方案。通过对两种控制方案进行对比试验,得出结论:新方案控制参数稳定可靠,可有效缩短试验周期,并能解决各级应变非等比例加载问题,可为以后同类型试验的控制工作提供参考。In the process of blade root static test force control method,cross coupling exists in each channel; the load imposed on test part by actuator in every direction is not equal to the real load in that direction. Therefore,it is necessary to recalculate the load of each control channel,the test process is so complex that it needs a long time to accomplish the test task. To solve this problem,selected the blade root as the test object and analyzed its structure during test process. Strain control modes were adopted in flap and lag control channels,force control mode reserved in control channel of axial force. Contrasted the two control methods,the combination control method could shorten the test period,ensured the load process in geometric proportion and served as a reference for later similar tests.

关 键 词：桨叶根部段 静强度试验 耦合 应变控制 联合控制 

分 类 号：V216.12[航空宇航科学与技术—航空宇航推进理论与工程]