飞翼布局飞行器航向射流控制方案优化

朱佳晨; 史志伟; 耿玺; 付军泉; 孙全兵; 陈永亮

doi:10.13224/j.cnki.jasp.20200466

飞翼布局飞行器航向射流控制方案优化

doi: 10.13224/j.cnki.jasp.20200466

朱佳晨^1,2,
史志伟^1,2, ,,
耿玺^1,2,
付军泉^1,2,
孙全兵^1,2,
陈永亮^1,2

1.
南京航空航天大学航空学院空气动力学系，南京 210016
2.
南京航空航天大学航空学院非定常空气动力学与流动控制工业和信息化部重点实验室，南京 210016

基金项目: 江苏省研究生科研与实践创新计划项目（KYCX19_0155）；航空动力基金（6141B09050389）；航空基金（2019ZA052001）；江苏高校优势学科建设工程资助项目

详细信息

作者简介:
朱佳晨（1993-），男，博士生，主要从事主动流动控制技术研究。

通讯作者:
史志伟（1972-），男，教授、博士生导师，博士生，主要从事流动控制技术和飞行仿真研究。E-mail：szwam@nuaa.edu.cn

中图分类号: V211
计量
- 文章访问数: 142
- HTML浏览量: 5
- PDF量: 343
- 被引次数: 0
出版历程
- 收稿日期: 2020-11-02
- 刊出日期: 2021-11-28

Scheme optimization of yaw control of flying-wing aircraft based on jet flow control

ZHU Jiachen^1,2,
SHI Zhiwei^{1,2
, ,},
GENG Xi^1,2,
FU Junquan^1,2,
SUN Quanbing^1,2,
CHEN Yongliang^1,2

1.
Department of Aerodynamics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Key Laboratory of Unsteady Aerodynamics and Flow Control，Ministry of Industry and Information Technology，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要: 由于飞翼布局飞行器取消了垂尾，其航向控制困难。为辅助和优化航向控制，基于射流控制技术设计了多种激励方案。设计并制作了航向射流控制激励器，通过风洞测力实验和二维数值模拟，对各方案的控制效果和作用机理进行分析，并选取出最优控制方案。研究结果表明：相同射流动量系数下，产生阻力比施加推力更容易获得偏航力矩。当激励开启后，射流包含与来流相逆的分量越多，与来流作用越明显，形成的分离区越大，控制效果越好。其中前对称吹气为最优控制方案，可以产生约70°阻力舵偏转效果，且力矩耦合程度较小。
- 飞翼布局 /
- 射流控制 /
- 阻力舵 /
- 航向控制 /
- 流动分离
Abstract: There are difficulties in yaw control of a flying-wing aircraft due to the cancellation of vertical tail.A variety of control schemes were designed based on the jet flow control technology to assist in and optimize the yaw control.The jet control actuator was designed and manufactured.Through the wind tunnel force measurement experiment and two-dimensional numerical simulation，the control effect and mechanism of each scheme were analyzed，and the optimal control scheme was selected.The results showed that under the same jet momentum coefficient，it was easier to obtain yaw moment by producing resistance than by applying thrust.After turning on the excitation，the more inverse components the jet contains in relation to the incoming flow，the more obvious the interaction with the incoming flow；the larger the separation zone formed，the better the control effect.The forward symmetric blowing was proved to be the optimal control scheme，which can produce about rudder effect equivalent to a split drag rudder deflection of 70°，and the coupling degree of moment was small.
- flying-wing layout /
- jet flow control /
- drag rudder /
- yaw control /
- flow separation

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