直升机旋翼气弹响应及桨毂载荷的参数灵敏度分析  

Efficient Sensitivity Analysis of Aeroelastic Response and Hub Loads for a Helicopter Rotor

作　　者：杨卫东[1] 张呈林[1] 王华明[1] 

机构地区：[1]南京航空航天大学飞行器系,南京210016

出　　处：《南京航空航天大学学报》1996年第6期733-738,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：提出了一种有效的旋翼气弹响应及桨毂载荷的参数灵敏度分析方法.建立了响应灵敏度导数的时域有限元方程,通过配平计算及响应灵敏度的耦合分析,由力积分法与多桨叶求和法直接得到桨毂载荷的灵敏度导数.数值计算结果表明,与灵敏度分析的有限差法比较,直接的灵敏度分析法可以大幅度降低灵敏度分析所需的计算时间,为有效的旋翼结构多学科综合优化提供了快速的参数灵敏度分析方法.An efficient sensitivity analysis of aeroelastic response and hub loads for a helicopterrotor with respect to structural parameters is investigated. The nonlinear, periodic, steady re-sponse and sensitivity equations of the blade is derived using a finite element in space and timeapproach. The vehicle trim and steady response are calculated iteratively as one coupled solu-tion using a modified Newton method. The derivatives of blade response and hub loads are im-plemented using a direct analysis approach. Numerical results show that a considerable reduc-tion of CPU time is achieved by using the direct analytical approach, compared with the finite-difference approach.

关 键 词：直升机旋翼 气动力弹性 结构最优化 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计] V211.47