共轴刚性旋翼飞行器配平特性及验证  

Trim Characteristics and Verification of Coaxial Rigid Rotor Aircraft

作　　者：袁野[1] 陈仁良[1] 李攀[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210006

出　　处：《南京航空航天大学学报》2016年第2期186-193,共8页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金青年科学基金(51405227)资助项目;航空科学基金(20145752034)资助项目;江苏高校优势学科建设工程资助项目

摘　　要：针对共轴刚性旋翼与常规旋翼的区别,从挥舞运动、变距操纵和诱导速度3方面建立共轴刚性旋翼的气动力模型。采用等效挥舞运动概念,建立共轴刚性旋翼的挥舞运动方程;引入提前操纵角概念,建立与共轴刚性旋翼挥舞频率相适应的变距操纵模型;引入上下旋翼干扰因子,建立共轴刚性旋翼的诱导速度模型。在此基础上,建立共轴刚性旋翼飞行器飞行动力学模型,并以XH-59A直升机为例计算纯直升机飞行模式的配平特性,使用飞行试验数据验证了理论模型的正确性,同时讨论了共轴刚性旋翼飞行器与常规直升机配平特性的异同点。Aiming at the difference between the coaxial rigid rotor and the conventional rotor, the aerody- namic models of coaxial rigid rotor are built in terms of rotor flapping, pitch control and induced veloci- ty. The flapping movement function of the coaxial rigid rotor is introduced based on the concept of e- quivalent flapping. The pitch control motion fitting with the flapping frequency of coaxial rigid rotor is modeled based on the concept of control phase angle. The induced inflow velocity of the coaxial rigid ro- tor is modeled by using the interference factor. With the flight dynamic models mentioned above, the trim characteristics of pure-helicopter mode with the example of XH-59A helicopter are analyzed, and the models are verified by the flight test data. Comparison of the trim characteristics between coaxial rigid rotor aircraft and conventional single rotor helicopter is performed.

关 键 词：直升机 共轴刚性旋翼 挥舞运动 动态入流 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]