自转旋翼机飞行性能理论建模技术  

Theoretical Modeling Technology for Gyroplane Flight Performance

作　　者：王俊超[1] 李建波[1] 韩东[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,江苏南京210016

出　　处：《航空学报》2014年第12期3244-3253,共10页Acta Aeronautica et Astronautica Sinica

基　　金：江苏高校优势学科建设工程资助项目;国家自然科学基金(11202097);航空科学基金(2011ZA52014)~~

摘　　要：为研究自转旋翼机的飞行性能理论建模技术,基于基本分析法和配平分析法,对自转旋翼机整机需用功率的建模方法进行了研究,并研究了自转旋翼机的桨盘迎角特性、升阻特性以及自转旋翼桨叶剖面迎角分布特性等。研究表明:建立的基本分析法和配平分析法计算模型均可以准确计算自转旋翼机的整机需用功率和自转旋翼桨盘迎角,两种方法均可用于自转旋翼机飞行性能的分析;小速度时整机需用功率主要来自于自转旋翼功率,大速度时机身废阻功率成为整机需用功率的主要来源;适当增加总距可以提高自转旋翼和整机的升阻比;在自转旋翼设计时可以对桨叶剖面翼型的展向分布进行优化,在桨根处优先采用相对不易失速的翼型以推迟失速对最大飞行速度的限制。To investigate the theoretical modeling technology of gyroplane flight performance,the modeling method of gyroplane total power required is studied in this paper based on the fundamental analysis method and trim analysis method.Then the gyroplane rotor disk angle of attack characteristics,lift and drag characteristics and angle of attack distribution characteristics of autorotating rotor blade section are investigated.The results indicate that both the fundamental analysis method and trim analysis method can calculate total power required and autorotating rotor disk angle of attack accurately.Both methods can be used to analyze the gyroplane flight performance.The total power required mainly comes from the autorotating rotor power at low speed,and the fuselage parasite power becomes the main source of the total power required at high speed.Increasing the collective pitch properly can increase the lift drag ratio of the autorotating rotor and the gyroplane.In the autorotating rotor design process,the optimization can be applied to the aerofoil spanwise distribution.The airfoil which has excellent stall characteristics can be used at the blade root preferentially to delay the maximum flight speed limit by stall.

关 键 词：自转旋翼机 旋翼 性能 功率 配平 升阻比 迎角 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]