摘要
离子风推进器具有结构简单、静音性好和可微型化的特点,应用前景广阔,但缺乏对其推力和推力功率比(推功比)的多因素系统研究和多级电极阵列试验数据支撑。该文分析电极形状尺寸和电极阵列结构等对推力和推功比的影响。研究表明:当导线电极直径为0.2~0.6mm、翼型电极弦长为50~70mm以及型号为NACA0010、NACA0020时,减小导线电极直径或增大翼型电极前缘半径,推力增大,推功比减小;增加翼型电极弦长,推力增大,推功比也增大。当电极阵列组间距为80~240mm时,间距越小,推力和推功比越大;当电极阵列对间距为100~200mm时,间距越小,推力和推功比越小。矩阵式排列中,1×n结构具有给定电极组数下的最大推力和推功比。实测推进电极阵列产生推力3.2N,为离子风飞机飞行推进试验创造了条件。
An ionic wind propeller has the characteristics of being simple in structure, quietness, and miniaturization, and thus has broad prospect. Previous studies on thrust and thrust to power ratio(T/P) of ionic wind propeller lack systematic researches on a variety of factors, as well as experimental data for multi-electrode array. In this work, the effects of electrode shape and size, electrode array structure on thrust and T/P were studied. With the wire electrode diameter of 0.2~0.6mm, the airfoil electrode chord length of 50~70mm, and the shape of NACA0010 or NACA0020, it can be found that reducing the wire electrode diameter or increasing the radius of curvature of airfoil electrode can increase the thrust, but decrease T/P;while increasing the chord length of airfoil electrode can achieve not only a higher thrust but also a higher T/P. When the electrode array group spacing is 80~240mm, the smaller the spacing, the higher the thrust and T/P. When the electrode arrays pair spacing is 100~200mm, the smaller the spacing, the lower the thrust and T/P. For the rectangular arrangement, the 1×n structure has the maximum thrust and T/P for a given number of electrodes. We measured the thrust of the propulsion electrode array is 3.2N, which lays a foundation for the flight propulsion test of ionic-wind driven aircraft.
作者
欧阳芳相
陈赦
许冬冬
杨发友
徐千鸣
赵振兴
OUYANG Fangxiang;CHEN She;XU Dongdong;YANG Fayou;XU Qianming;ZHAO Zhenxing(College of Electrical and Information Engineering,Hunan University,Changsha 410082,Hunan Province,China;Hiwing Aviation General Equipment Co.,Ltd.,Fengtai District,Beijing 100074,China;College of Electrical and Information Engineering,Hunan Institute of Engineering,Xiangtan 411104,Hunan Province,China)
出处
《中国电机工程学报》
EI
CSCD
北大核心
2022年第8期3098-3106,共9页
Proceedings of the CSEE
基金
国家自然科学基金项目(51977063)
海鹰航空通用装备有限责任公司项目(MF2019084S214)。
关键词
离子风
电晕放电
推力
推力功率比
飞机推进
ion wind
corona discharge
thrust
thrust to power ratio
aircraft propulsion
