悬停状态下无轴承尾桨气弹稳定性分析  

Aeroelastic Stability Analysis for Bearingless Tail Rotor in Hovering

作　　者：江湘清[1] 张呈林[1] 王浩文[1] 刘勇 

机构地区：[1]南京航空航天大学航空宇航学院

出　　处：《南京航空航天大学学报》2001年第3期212-216,共5页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：新型尾桨型式无轴承尾桨的气弹稳定性分析非常复杂 ,而目前国内在这方面的研究还是空白。本文试图建立一套有工程实用意义的无轴承尾桨气弹稳定性分析方法和相应的分析程序 ,并进行参数影响分析和计算。在前期研究工作的基础上 ,本文推导出基于正交各向异性复合材料梁的应变能变分表达式 ,并将其用于推导旋翼 /机身耦合系统的运动方程。再通过对系统的稳态周期解进行摄动 ,得到相应的线化周期时变动力学方程 ,用Floquet理论判断系统的稳定性。最后 ,分析计算了悬停状态下某无人直升机无轴承尾桨的气弹稳定性 ,表明其孤立桨叶及尾桨 /传动轴 /尾梁的耦合系统是稳定的 ;并进行了参数分析 ,得到一些有意义的结论。The aeroelastic stability of bearingless tail rotor is complex, while there is no research work in this region in ou r country at present. This paper introduces a set of engineering aeroelastic sta bility analysis method and corresponding analysis program for the bearingless ta il rotor, practically and to analyze the influence of some key parameters on th e system′s aeroelastic stability. Based on previous re search work, the paper gives the derivation of the strain energy variation ex pression for the orthogonal anisotropic composite beam, and applies it to settin g up the equations of motion for the rotor and fuselage coupling system. Then by perturbing the steady periodic solution of the systems′ equations of motion, we may obtain the corresponding linear periodic time-variation dynamic equation , and use floquet theory to judge the stability of the system. Finally, an aeroe lastic stability analysis is made for the bearingless tail rotor system of an u nmanned helicopter in hovering, and it proves that this bearingless tail rotor a nd its coupling system are stable. Meanwhile, some good conclusions are obtained by analyzing some parameter′s influence.

关 键 词：无轴承尾浆 气弹稳定性 复合材料柔性梁 悬停状态 直升飞机 旋翼 

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] V211.411