【作者】 高宇剑； 张刚锋； 程小全；

【Author】 GAO Yujian,ZHANG Gangfeng,CHENG Xiaoquan (School of Aeronautical Science and Engineering,Beihang University,Beijing 100191,China)

【机构】 北京航空航天大学航空科学与工程学院；

【摘要】 选取某型直升机桨叶靠近桨根的翼段为研究对象,利用CATIA建立三维实体模型,并导入ANSYS建立有限元分析模型。分别对翼段不同位置、不同方向的穿透性损伤进行静强度校核分析。在此基础上,应用APDL参数化设计语言开发了计算大梁带及复合材料层合结构各铺层强度比的程序,在不考虑空气动力和桨叶自身重力的情况下,计算得到了翼段在离心力、挥舞弯矩和摆振弯矩同时作用下的应力应变云图及其中各结构的强度比。计算结果表明,该翼段满足静强度设计的要求。更多还原

【Abstract】 By choosing a blade panel adjacent to the root of a certain helicopter blade as the object of this study,The author first established the 3D model of the object by CATIA,then modeled the 3D model for finite element analysis through ANSYS.The author then analyzed the performance of the static strength of the blade panel shot from different positions and directions.By writing a APDL (ANSYS Parameter Design Language,which is able to calculate the specific strength of the main beam and other composite laminate structures layers)program,the author got the clouds of stress and strain and the values of every structure under centrifugal force,wave moment and shimmy moment without considering the aerodynamic force as well as the gravity of the blade panel itself.In the end,the author gained the strength ratio of each component of the blade panel before and after the penetration damage.Result of this paper shows that this blade panel blade satisfies to the static strength design.更多还原