电控旋翼直升机飞行动力学建模与配平特性研究  

Flight dynamics modeling and trim characteristics of helicopters with electrically controlled rotor

作　　者：陆洋[1] 王超[1] 赵鑫[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国防科技重点实验室,江苏南京210016

出　　处：《空气动力学学报》2013年第3期388-393,400,共7页Acta Aerodynamica Sinica

基　　金：国防科技重点实验室基金项目(9140C400502090C40)

摘　　要：首先基于Peters-He广义动态尾迹理论,建立了电控旋翼动态尾迹入流模型,进一步结合电控旋翼襟翼操纵与桨叶变距之间的关系、桨叶挥舞运动方程和带襟翼翼型非定常气动力模型建立了适用于飞行力学分析的电控旋翼气动力模型。在此基础上,结合机身、尾桨、尾面的气动力模型,建立了完整的电控旋翼直升机飞行动力学分析模型。以Z-11直升机为基准改造为电控旋翼直升机作为算例,计算了前飞状态下电控旋翼直升机的诱导速度分布和桨盘迎角分布,对比了电控旋翼与常规旋翼的气动特性差异;在此基础上,进一步分析了电控旋翼直升机的配平特性随前飞速度的变化规律以及与常规直升机的差异。Firstly, a dynamic inflow model for electrically controlled rotor （ECR） is developed based on the ＂Peters-He＂ generalized dynamic wake theory, and an accurate aerodynamics model of ECR, which is suited for the analysis of ECR helicopter flight dynamics, is built combined with the relationship between flap deflection and blade pitch, the blade flapping equation and the unsteady aerodynamic model of airfoil with trailing-edge flap. Then, on this basis, an ECR helicopter flight dynamics model is established combined with the aerodynamics models of airframe, tail rotor, horizontal and vertical tail. Taking Z-11 helicopter as a numerical example, the distributions of ECR induced velocity and angles of attack variations with advance speed are calculated and compared with the baseline rotor. Furthermore, the trim characteristics of the ECR helicopter is investigated.

关 键 词：电控旋翼 动态入流 飞行动力学 配平特性 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]