直升机水平飞行状态下型阻功率同前进比的数学关系  

Mathematical Relationship between Form Drag Power and Forward Ratio of Helicopter in Horizontal Flight

作　　者：魏立 邱良军[1] WEI Li;QIU Liangjun(China Helicopter Research and Development Institute,Jingdezhen Jiangxi 333000)

机构地区：[1]中国直升机设计研究所,江西景德镇333000

出　　处：《中国科技纵横》2022年第5期73-75,共3页China Science & Technology Overview

摘　　要：直升机在水平飞行时的型阻功率对直升机的使用是非常重要且值得研究的问题,其直接影响了直升机能飞多远、完成任务剖面所需要的油耗等重要的性能指标。目前国外相关文献给出了水平飞行前进比在0〜0.35之间的型阻功率近似计算表达式,但是当前进比超过0.5后此表达式便有误差而不再适用。基于此,本文简要介绍了直升机水平飞行状态下的旋翼气动环境和受力模型,给出了型阻功率数学上的理论计算模型公式,通过数值积分的方法给出了前进比在0〜1之间都适用的型阻功率解析式。The drag power of the helicopter in horizontal flight is a very important and worthy issue for the use of the helicopter,which directly affects the important performance indicators such as how far the helicopter can fly,the fuel consumption required to complete the mission profile and so on.At present,the relevant foreign literatures give the approximate calculation expression of the type resistance power for the advance ratio of horizontal flight between 0 and 0.35〉but when the advance ratio exceeds 0.5,this expression has errors and is no longer applicable.Based on this,this paper briefly introduces the aerodynamic environmen t and force model of the rotor in the helicopter's horizon tai flight state,gives the mathematical theoretical calculation model formula of the drag power,and then gives the forward ratio between 0 and 1 by numerical integration the type resistance power analytical formula that is applicable to both.

关 键 词：型阻功率 水平飞行 气动模型 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]