螺旋桨桨叶载荷标定方法研究及试验验证

Research and experimental verification of propeller blade load calibration method

摘要

涡桨发动机通过螺旋桨的旋转产生大部分的推进力，进而推动飞机前行。螺旋桨桨叶在工作时，受到挥舞弯矩、摆振弯矩和扭转等多种载荷的复合作用，桨叶载荷测量是获取螺旋桨结构数据、对其疲劳寿命进行合理评估的重要手段，而空中桨叶载荷测量的准确性较大程度受地面标定试验获得的标定曲线的影响。本研究针对地面标定试验中的常见的挥舞和摆振载荷耦合问题，开展了物理解耦方法研究，通过逐步趋近法不断调整应变片测量位置，并在螺旋桨桨叶上开展了试验验证。试验结果表明，该方法能够较好地实现挥舞和摆振载荷的解耦，解耦之前二者的相对耦合系数高达178%，解耦后各测试截面相对耦合系数均达到了3%以下，表明该解耦方法合理可行，为后续开展其他螺旋桨桨叶载荷标定试验提供了重要借鉴经验。

Abstract

The thrust of the turboprop engine is mostly generated by the rotation of the propeller，which propels the aircraft forward. The propeller blade is subjected to the combined action of various loads such as flapping bending moment，shimmy bending moment and torsion when it is working. And blade load measurement is an important means to obtain propeller structural data and evaluate its fatigue life reasonably. However，the accuracy of blade load measurement in the air is greatly affected by the calibration curve obtained from the ground calibration test. In this paper，the physical decoupling method is studied for the common coupling problem of flapping and shimmy loads in ground calibration test. This method continuously adjusts the measurement position of the strain gauge by the step-by-step approach method，and the experimental verification is carried out on the propeller blade for the first time. The test results show that the method can better realize the decoupling of flapping and shimmy loads. Before decoupling，the relative coupling coefficient of the two is as high as 178%. However，after decoupling，the relative coupling coefficient of each test section reaches below 3%，indicating that the decoupling method is reasonable and feasible，which provides important reference experience for the subsequent load calibration tests of other propeller blades.

关键词

螺旋桨桨叶 / 挥舞载荷 / 摆振载荷 / 标定试验 / 逐步趋近 / 物理解耦

Key words

propeller blade / flapping load / shimmy load / calibration test / gradually approaching / physical decoupling

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基金资助

军科委基础加强研究项目(2022-JCJQ-ZD-195-02)