直升机旋翼桨叶气弹优化减振设计方法  

AEROELASTIC OPTIMIZATION OF A HELICOPTER ROTOR WITH SINGLE-CELL COMPOSITE BLADES FOR VIBRATION REDUCTION

作　　者：向锦武[1] 张晓谷[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1999年第2期212-214,共3页Journal of Aerospace Power

基　　金：航空科学基金

摘　　要：从振源着手通过设计参数的最优选择设计直升机旋翼桨叶，使传递到机身的交变载荷最小达到降低振动水平的目的是旋翼桨叶设计思想的进步。本文在简单概述该方法的基础上，以某４桨摆振柔软的无铰复合材料桨叶为研究对象，将其大梁模拟为一单闭室复合材料盒形梁，研究了通过铺层角的优化选择，降低４次／转的桨毂交变力与力矩的情况。数值算例表明方法效果良好。An unsteady aerodynamic environment and highly flexible rotating blades lead to harmonic loadings on the rotor so as to cause high vibration in the helicopter.An optimization is carried out for a four-bladed,soft in-plane hingeless rotor consisting of a single-cell composite box-beam spar for helicopter vibration reduction.The design variables are the ply angles of the box-beam walls;the objective function is of the vibration hub loads.Constraints are imposed on blade rotating frequencies and aeroelastic stability.As compared to the initial design,the optimum solution results in a 20-70% reduction of the 4/rev hub loads.

关 键 词：旋翼桨叶 气动力弹性 优化 减振 直升机 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]