军民用直升机旋翼轴的共用结构试验验证方法研究  

Research on Common Structure Validation Method for Rotor Shaft of Militaryand Civil Helicopters

作　　者：罗愫 付双检 李宏 LUO Su;FU Shuangjian;LI Hong(Jiangxi Aircraft Airworthiness Certification Center of CAAC,Nanchang 330000,Jiangxi,China)

机构地区：[1]中国民用航空江西航空器适航审定中心,江西南昌330000

出　　处：《民航学报》2023年第6期103-106,共4页Journal of Civil Aviation

摘　　要：直升机依靠旋翼产生动力,可以实现垂直起降、空中悬停、前后左右移动,具备优异的机动性能。直升机的独特优势使其在军民用领域获得广泛应用,本文探讨在旋翼轴重要结构件上使用共用的试验验证方法。根据适航条款CCAR-27.305和CCAR-27.307的要求,结构必须能承受限制载荷而无有害的或永久的变形。本文以某型直升机旋翼轴为例,结合旋翼轴的结构构型,讨论了共用试验的设计、试验件及位置传感器和力传感器配套装置的安装、试验的加载顺序,完整地概述了该结构试验的验证方法,及如何通过试验验证表明结构强度和变形的符合性,对军民机适航审定符合性验证工作有一定的参考价值。Helicopters rely on rotor blades to generate power and can achieve vertical takeoff and landing,hover in the air,and move forward,backward,left and right,possessing excellent maneuverability.The unique advantages of helicopters have led to their widespread military and civil applications,and important structural components can be verified by using a common sample testing method.According to the airworthiness clauses CCAR-27.305 and CCAR-27.307,the structure must be able to withstand limited loads without harmful or permanent deformation.Taking a certain type of helicopter rotor shaft as an example,this paper discusses the design of shared tests,the installation of test pieces and supporting devices for position sensors and force sensors,and the loading sequence of tests based on the structural configuration of the rotor shaft,and provides a complete overview of the verification method for this structural test and how to demonstrate the compliance of structural strength and deformation through experimental verification.It has certain reference value for airworthiness certification of military and civil aircraft.

关 键 词：直升机 军民用 旋翼轴 共用结构验证 

分 类 号：V3[航空宇航科学技术]