摘要
微小型垂直起降飞行器悬停时往往采用螺旋桨滑流内舵面偏转进行姿态控制,但容易出现操纵力矩不足的问题。本文针对这一问题对微小型静推力状态螺旋桨与带舵面机翼的组合体进行了系统性的实验。通过对实验数据分析,本文指出通过优选螺旋桨几何参数可以改善操纵特性,并得出带舵面机翼不同构型对操纵特性影响的一系列结论,为如何改善此类飞行器悬停时的操纵特性提供了设计参考。
Mini vertical takeoff and landing（VTOL） aircraft popularly control their attitudes by deflecting the control surface in propeller slipstream when hovering,but usually lack of enough control moment.This paper shows the systematic experiments about the assembly of static propellers with small scale and wing with plain flap.According to analyzing the data,this paper indicates that plain flap control characteristics can be modified by selecting optimal propeller geometric parameters and gives a series of conclusions about the configuration influence of wing with plain flap on control characteristics.The results can be referenced in designing phase for increasing the control power of these aircrafts.
出处
《空气动力学学报》
EI
CSCD
北大核心
2011年第5期567-572,共6页
Acta Aerodynamica Sinica
基金
国家自然科学基金(10772013)
北航研究生创新实践基金资助
关键词
垂直起降
螺旋桨
滑流
舵面
操纵力矩
vertical takeoff and landing（VTOL）
propeller
slipstream
plain flap
control moment
