螺旋桨推进式柔性翼飞机操稳特性研究与试飞  

Investigation and flight tests on control and stability of aircraft with after-mounted propeller and flexible wing

作　　者：吴大卫[1] 吴征[2] 张兰丁[2] 邓彦敏[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]南京水利科学研究院水工所,南京210029

出　　处：《空气动力学学报》2011年第6期726-732,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(10772013);中央高校基本科研业务费专项资金

摘　　要：采用柔性翼面的小型飞行器在通用航空器和特种飞行器领域得到了较广泛的应用。由于此类飞行器往往采用蒙皮为可变形柔性织物的高置上单翼以及推进式螺旋桨,其特殊的升阻特性、总体布局和动力影响使得其飞行动力学具有很大特殊性。结合气动力估算、风洞实验和飞行实验结果,在此类飞机的纵、横航向操纵性与稳定性方面得出了有别于传统飞机的一些结论,并给出了有关物理解释;提供了适合此类飞机的飞行动力学建模方法和一系列有别于传统飞机的设计参数取值范围。Small scale aircraft with flexible wing is relatively popular among utility aircrafts and in some special fields, but there are still confusions in conceptual design which is mainly according to experiences. These aircrafts usually have the configuration of high wing with flexible fabric skin and after-mounted propeller, therefore the characters of aerodynamics, layout and power effect bring about some prominent particularities in flight dynamics. According to aerodynamic prediction, wind tunnel tests and flight tests, this paper shows some conclusions about longitudinal/ lateral contol and stability different from conventional aircrafts and gives the physical explanations for the results, then supplies the suitable methods of modeling these aircrafts for analyzing flight dynamics and recommends a series of range for designing parameters different from other conventional aircrafts.

关 键 词：柔性翼 动力影响 气动力估算 风洞实验 飞行实验 操纵性 稳定性 

分 类 号：V221[航空宇航科学与技术—飞行器设计]