带大载荷吊挂直升机悬停纵向操纵性分析  

Lognitudinal Control Characteristic Analysis of Heavy Slung-Load Helicopter

作　　者：孙传伟[1] 徐进[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家重点实验室,南京210016

出　　处：《南京航空航天大学学报》2005年第4期421-426,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：建立带吊挂直升机飞行操纵性分析的理论分析模型。在广义动态入流理论的基础上,基于经典非定常气动载荷理论,建立了尾迹畸变和尾迹耗散的实时分析模型。为模拟大负载情况下旋翼转速的波动,建立了双发准定常涡轮轴发动机实时仿真模型。吊挂模型为多段柔性吊索模型,包括吊钩模型和吊挂载荷模型。最后,对比计算和分析了吊挂飞行时的悬停操纵功效。To analyze the handling quality of a helicopter with the heavy slung-load, this paper presents a theoretical analysis model. Based on the generalized dynamic inflow theory and classic non-steady aerodynamic loading theory, a real-time model is obtained by establishing wake distortion and decay， Then a real-time quasi-steady turboshaft twin-engined model is founded by simulating the rotor speed fluctuation. The slung-load model-a multi-segment flexible cable model consists of a hook model and a slungload model， Finally, the handling efficiency of the helicopter with the heavy slung-load is analyzed。

关 键 词：直升机 吊挂 动态入流 尾迹畸变 旋翼 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]