动力入流对直升机旋翼前飞操纵导数的影响  

THE EFFECTS OF DYNAMIC INFLOW ON ROTOR CONTROL DERIVATIVES IN FORWARD FLIGHT

作　　者：包劲松[1] 张晓谷[1] 

机构地区：[1]南京航空航天大学

出　　处：《飞行力学》1994年第4期23-27,共5页Flight Dynamics

基　　金：航空科学基金

摘　　要：动力入流模型把直升机旋翼扰动运动产生的气动力变化和诱导速度的扰动直接联系起来，是一种简便实用的旋翼非定常气动力模型。本文把动力入流模型引入到直升机旋翼前飞操纵导数（升力、滚转力矩和俯仰力矩随总距及周期变距的变化）的分析计算中。通过分析，弄清了不同前进比、不同总距条件下动力入流对操纵导数的影响规律，并对动力入流的影响作了物理解释。Dynamic inflow model is a simple and practical means of analysing rotorunsteady aerodynamics,associating the perturbation in lift with the change in inducedinflow directly. This paper develops a method taking dynamic inflow into account toanalyse the rotor control response(rotor thrust,pitch and roll moments derivatives with respect to collective pitch and cyclic pitch).The paper reveals the influence of dy-namic inflow on rotor control derivatives in forward flight with different advance ratioand collective pitch.A brief explaination for the influence is given.

关 键 词：直升机 非定常空气动力 操纵导数 动力入流 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计] V211.15