다목적헬리콥터용 복합재로터깃 구조의 비행 대 비행 응력스펙트럼 산출

Abstract

기동비행 중 고속?막? 회전하는 헬리콥터 로터깃은 구조적 안전성과 연관되는 피로강도 및 피로수명 평가가 설계과정에서 중요한 과제이다, 로터깃의 피로해석을 위하여 우선 헬리콥터의 실제운용 중 예상되는 신뢰성 있는 비행모사 하중스펙트럼을 구성하여야 한다. 여기서는 다목적헬리콥터용으로 설계된 복합재로터깃에 대하여 무힌지로터깃의 표준하중 스펙트럼인 FELIX 데이터를 활용하여 비행 대 비행 하중스펙트럼을 구성하고 피로손상이 가장 극심하게 예상되는 부위에서 복합재 적층판해석을 통하여 응력스펙트럼을 산출하였다. 이러한 결과는 향후 다목적헬리콥터 로터깃의 피로수명해석 및 시험평가에 활용될 수 있을 것이다.

It is one of the important design assessment items to evaluate the fatigue life for the helicopter rotor blades. For this purpose, It is necessary to describe reliable load spectrum expected in the real operating of helicopters. A study of the development procedure of flight-by-flight load spectrum for the composite rotor blade of ultipurpose helicopter using FELIX data which is the data of standard load spectrum for hingeless rotor blades. And the analysis of composite laminate structure was also made to obtain the local stress spectrum on the site where the fatigue damages are anticipated. Thers results are applicable to analyze the fatigue life and to perform the fatigue test for the composite rotor blade of multipurpose helicopter.

It is one of the important design assessment items to evaluate the fatigue life for the helicopter rotor blades. For this purpose, It is necessary to describe reliable load spectrum expected in the real operating of helicopters. A study of the development procedure of flight-by-flight load spectrum for the composite rotor blade of ultipurpose helicopter using FELIX data which is the data of standard load spectrum for hingeless rotor blades. And the analysis of composite laminate structure was also made to obtain the local stress spectrum on the site where the fatigue damages are anticipated. Thers results are applicable to analyze the fatigue life and to perform the fatigue test for the composite rotor blade of multipurpose helicopter.