A New Approach to Modelling and Testing the Fatigue Strength of Helicopter Rotor Blades during Repair Process

Q4 Engineering

Fatigue of Aircraft Structures Pub Date : 2019-12-01 DOI:10.2478/fas-2019-0006

Michał Sałaciński, R. Kowalski, Michał Szmidt, S. Augustyn

{"title":"A New Approach to Modelling and Testing the Fatigue Strength of Helicopter Rotor Blades during Repair Process","authors":"Michał Sałaciński, R. Kowalski, Michał Szmidt, S. Augustyn","doi":"10.2478/fas-2019-0006","DOIUrl":null,"url":null,"abstract":"Abstract The fatigue test was carried out on an element of a rotor blade removed from the Mi-2 helicopter. The purpose of the test was to check the fatigue strength of the repaired rotor blade. Metal composite rotor blades have a metal spar in the form of a box and the trailing sections in the form of metallic honeycomb sandwich panels. The trailing sections are bonded to the spar. The repair had been carried out at the point where the trailing section became debonded from the spar at the Air Force Institute of Technology in Warsaw using a methodology developed for carrying out repairs of rotor blades’ damage. All types of the Mi family helicopters are equipped with metal composite rotors blades. Depending on MTOW (Maximum Take-Off Weight) and destination of helicopters, blades differ in dimensions, but their design solutions are practically the same. For this reason, the developed repair methodology can be used for all characteristic rotor blades structures for Mi helicopters. The fatigue test was performed at the Łukasiewicz - Institute of Aviation in Warsaw, using a hydraulically driven fatigue machine. The fatigue test was carried out by performing over 1.1 million load cycles. In repair places, upon completion of fatigue testing, no damage was found.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":"2019 1","pages":"56 - 67"},"PeriodicalIF":0.0000,"publicationDate":"2019-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Fatigue of Aircraft Structures","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.2478/fas-2019-0006","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"Engineering","Score":null,"Total":0}

引用次数: 0

Abstract

Abstract The fatigue test was carried out on an element of a rotor blade removed from the Mi-2 helicopter. The purpose of the test was to check the fatigue strength of the repaired rotor blade. Metal composite rotor blades have a metal spar in the form of a box and the trailing sections in the form of metallic honeycomb sandwich panels. The trailing sections are bonded to the spar. The repair had been carried out at the point where the trailing section became debonded from the spar at the Air Force Institute of Technology in Warsaw using a methodology developed for carrying out repairs of rotor blades’ damage. All types of the Mi family helicopters are equipped with metal composite rotors blades. Depending on MTOW (Maximum Take-Off Weight) and destination of helicopters, blades differ in dimensions, but their design solutions are practically the same. For this reason, the developed repair methodology can be used for all characteristic rotor blades structures for Mi helicopters. The fatigue test was performed at the Łukasiewicz - Institute of Aviation in Warsaw, using a hydraulically driven fatigue machine. The fatigue test was carried out by performing over 1.1 million load cycles. In repair places, upon completion of fatigue testing, no damage was found.

查看原文本刊更多论文

直升机旋翼桨叶修复过程疲劳强度建模与测试的新方法

摘要对从米-2直升机上拆下的旋翼桨叶的一个部件进行了疲劳试验。试验的目的是检查修复后的转子叶片的疲劳强度。金属复合材料转子叶片具有箱形形式的金属翼梁和金属蜂窝夹芯板形式的尾部。尾部与翼梁相连。在华沙空军理工学院，使用为修复转子叶片损坏而开发的方法，在尾部从翼梁上脱落时进行了修复。所有类型的米族直升机都配备了金属复合材料旋翼叶片。根据直升机的最大起飞重量和目的地，叶片的尺寸不同，但它们的设计方案实际上是相同的。因此，所开发的维修方法可用于Mi直升机的所有特征旋翼叶片结构。疲劳试验在华沙航空研究所使用液压驱动疲劳机进行。疲劳试验是通过执行超过110万次载荷循环进行的。在修复处，疲劳试验完成后，未发现任何损坏。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

求助全文

约1分钟内获得全文求助全文

来源期刊

Fatigue of Aircraft Structures Engineering-Safety, Risk, Reliability and Quality

CiteScore

0.40

自引率

0.00%

发文量

期刊介绍： The publication focuses on problems of aeronautical fatigue and structural integrity. The preferred topics include: full-scale fatigue testing of aircraft and aircraft structural components, fatigue of materials and structures, advanced materials and innovative structural concepts, damage tolerant design of aircraft structure, life extension and management of ageing fleets, structural health monitoring and loads, fatigue crack growth and life prediction methods, NDT inspections, airworthiness considerations.