直升机复合材料主桨叶缺陷容限验证技术  

The Study on Flaw Tolerance Substantiation of Helicopter Composite Material Main Rotor Blade

作　　者：潘春蛟[1] 顾文标[1] 曾玖海[1] 邹静[1] 虞汉文[1] 

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》2015年第2期50-57,共8页Helicopter Technique

摘　　要：目前直升机主桨叶结构多采用复合材料,作为直升机特有的关键性动部件,工作时一直处于复杂的受力环境中,其状况直接影响到直升机的飞行安全。复合材料主桨叶设计与生产工艺复杂,制造中很容易出现如分层、错位、皱褶、夹杂等内部缺陷,而使用时的高速旋转使其很容易受到外物如飞沙、走石等的冲击损伤。按照适航FAR/CCAR27/29.571条的要求,提出复合材料桨叶缺陷容限性能验证的方法并予以实施,降低了用户使用和维护成本,提高了结构的安全可靠性。Main rotor blades are most important parts of helicopter and always work under multiply loads environment, their enough strength will be critical for the flight safety of helicopter. Today main rotor blades are usually designed by composite material, some type of flaws such as delamina- tions, misalignments, undulations （waves）, metallic inclusions and Impacts etc. are frequently a- rose during blade manufacturing process and service. Flaw tolerance substantiation of helicopter crit- ical structures is required in FAR/CCAR27/29. 571. The flaw tolerance substantiation approach of full - scale blades was shown and the acceptance criteria of flaw type and parameter were given, it would reduce costs of blades production and service beside more safety.

关 键 词：直升机 主桨叶 复合材料 缺陷容限 验证技术 

分 类 号：V250.2[一般工业技术—材料科学与工程] V214.8[航空宇航科学与技术—航空宇航制造工程]