中等展弦比飞翼布局无人机后缘射流滚转控制

邵帅; 郭正; 贾高伟; 陈清阳; 侯中喜; 张来平

doi:10.7572/S1000-6893.2022.27437

航空学报 >

2023 , Vol. 44 >Issue 10: 127437 - 127437

DOI: https://doi.org/10.7572/S1000-6893.2022.27437

流体力学与飞行力学

中等展弦比飞翼布局无人机后缘射流滚转控制

邵帅 ,
郭正 ,
贾高伟 ,
陈清阳 ,
侯中喜 ,
张来平

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^1.国防科技大学空天科学学院，长沙 410073
^2.军事科学院国防科技创新研究院，北京 100071

．E-mail： guozheng@nudt.edu.cn

收稿日期: 2022-05-13

修回日期: 2022-06-16

录用日期: 2022-07-13

网络出版日期: 2022-08-03

基金资助

国家自然科学基金(61801495);湖南省科技创新计划项目(2021RC3077)

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Roll control of medium-aspect-ratio flying-wing UCAV based on trailing-edge jet

Shuai SHAO ,
Zheng GUO ,
Gaowei JIA ,
Qingyang CHEN ,
Zhongxi HOU ,
Laiping ZHANG

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^1.College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China
^2.National Innovation Institute of Defense Technology，Academy of Military Sciences，Beijing 100071，China

E-mail： guozheng@nudt.edu.cn

Received date: 2022-05-13

Revised date: 2022-06-16

Accepted date: 2022-07-13

Online published: 2022-08-03

Supported by

National Natural Science Foundation of China(61801495);Science and Technology Innovation Program of Hunan Province(2021RC3077)

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摘要

飞翼布局飞行器有望依靠射流主动流动控制技术实现无舵面飞行以改善隐身特性，但鲜有针对中等展弦比（3~4.5）战术级飞翼的相关研究。本文为中等展弦比飞翼布局无人机设计环量控制激励器取代传统副翼，开展全机数值模拟和飞行试验研究，探究后缘环量控制射流的滚转控制能力。数值模拟使用压力入口边界并考虑射流动量贡献的气动力，实现对飞翼绕流和激励器内流耦合模拟和整机气动特性预测。数值模拟研究表明，射流的滚转控制能力随射流动量系数线性增长，且未产生显著的横航向或横纵向耦合力矩。飞行试验结果表明，环量控制激励器实现了平均滚转角速率25.5~26.7 （°）/s，最大滚转角速率40.1 （°）/s，最大滚转角83.9°的控制效果。

关键词： 主动流动控制; 环量控制; 飞翼布局; 滚转控制; 飞行试验

本文引用格式

邵帅 , 郭正 , 贾高伟 , 陈清阳 , 侯中喜 , 张来平 . 中等展弦比飞翼布局无人机后缘射流滚转控制[J]. 航空学报, 2023 , 44(10) : 127437 -127437 . DOI: 10.7572/S1000-6893.2022.27437

Abstract

With jet active flow control technologies， the flying-wing aircraft are expected to achieve flapless flight which can improve the stealth characteristics. However， little research has been done on the tactical flying-wing platforms with a medium aspect ratio （3-4）. We design a Circulation Control Effector （CCE） to replace the ailerons of a medium-aspect-ratio flying-wing UCAV. Numerical simulations and flight tests of the demonstrator are conducted to investigate the roll control effectiveness of the trailing-edge circulation control jet. In numerical simulations， the pressure inlet boundary is adopted， and the contribution of the jet momentum is also considered in the aerodynamic force calculation. Then， the coupling simulation of the inner flow in the CCE and the outer flow over the flying-wing UCAV is realized， and the aerodynamic characteristics of the demonstrator are predicted. The simulation results show that with the increase of the jet momentum coefficient， the roll control capability increases almost linearly， with no obvious coupling yaw moment or pitch moment. The flight test results indicate that remarkable roll control effectiveness is achieved by the CCE， with the mean roll rate being 25.5-26.7 （°）/s， the maximum roll rate 40.1 （°）/s， and the maximum roll angle 83.9°.

Key words： active flow control; circulation control; flying-wing aircraft; roll control; flight test

参考文献

1	李为吉. 飞机总体设计［M］. 西安：西北工业大学出版社， 2005： 78-102.
	LI W J. Overall design of aircraft［M］. Xi’an： Northwestern Polytechnical University Press， 2005： 78-102 （in Chinese）.
2	车竞，何开锋，钱炜祺. 制空型无人机的关键技术、气动布局及特性［J］. 空气动力学学报， 2017， 35（1）： 13-19， 26.
	CHE J， HE K F， QIAN W Q. Key technique and aerodynamic configuration characteristic of UCAV with command of the air［J］. Acta Aerodynamica Sinica， 2017， 35（1）： 13-19， 26 （in Chinese）.
3	SMITH D R， WARSOP C. NATO AVT-239 task group： ‘Innovative control effectors for manoeuvring of air vehicles’-introduction and overview［C］∥AIAA Scitech 2019 Forum. Reston： AIAA， 2019.
4	MILLER D N. NATO AVT-239 task group： An assessment on the prospects of active flow control on a future UAS［C］∥AIAA Scitech 2019 Forum. Reston： AIAA， 2019.
5	GOLDEN R， MARSHALL D. Design and performance of circulation control flap systems［C］∥48th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston： AIAA， 2010.
6	WARSOP C， CROWTHER W J. Fluidic flow control effectors for flight control［J］. AIAA Journal， 2018， 56（10）： 3808-3824.
7	FIELDING J P， LAWSON C P， PIRES R， et al. Development of the demon technology demonstrator UAV［C］∥27th Congress of the International Council of the Aeronautical Sciences， 2010， 1： 114-120.
8	KAY A. Successful demonstration of breakthrough blown-air flight technologies to revolutionise future aircraft design［EB/OL］. （2019-05-02）［2022-07-15］. .
9	CHEN K， SHI Z W， ZHU J C， et al. Roll aerodynamic characteristics study of an unmanned aerial vehicle based on circulation control technology［J］. Proceedings of the Institution of Mechanical Engineers， Part G： Journal of Aerospace Engineering， 2019， 233（3）： 871-882.
10	SHI Z W， ZHU J C， DAI X X， et al. Aerodynamic characteristics and flight testing of a UAV without control surfaces based on circulation control［J］. Journal of Aerospace Engineering， 2019， 32（1）： 04018134.
11	ZHU J C， SHI Z W， SUN Q B， et al. Yaw control of a flying-wing unmanned aerial vehicle based on reverse jet control［J］. Proceedings of the Institution of Mechanical Engineers， Part G： Journal of Aerospace Engineering， 2020， 234（6）： 1237-1255.
12	孙全兵，史志伟，耿玺，等. 基于主动流动控制技术的无舵面飞翼布局飞行器姿态控制［J］. 航空学报， 2020， 41（12）： 124080.
	SUN Q B， SHI Z W， GENG X， et al. Attitude control of flying wing aircraft without control surfaces based on active flow control［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（12）： 124080 （in Chinese）.
13	BRANDT S， MCLAUGHLIN T E， WILLIAMS D R， et al. NATO AVT-239 task group： Flight test of compressed and bleed-air driven control effectors on the ICE/SACCON UAS subscale aircraft［C］∥AIAA Scitech 2019 Forum. Reston： AIAA， 2019.
14	李林，马超，王立新. 小展弦比飞翼布局飞机稳定特性［J］. 航空学报， 2007， 28（6）： 1312-1317.
	LI L， MA C， WANG L X. Stability features of low aspect-ratio flying wings［J］. Acta Aeronautica et Astronautica Sinica， 2007， 28（6）： 1312-1317 （in Chinese）.
15	HOHOLIS G A. Assessment of fluidic control effectors using computational fluid dynamics［D］. Liverpool： The University of Liverpool， 2016.
16	FORSTER M J. Computational modelling of transonic circulation control［D］. Liverpool： The University of Liverpool， 2017.
17	FU Z J， CHU Y W， CAI Y S， et al. Numerical investigation of circulation control applied to flapless aircraft［J］. Aircraft Engineering and Aerospace Technology， 2020， 92（6）： 879-893.
18	HE X， ZHAO Z， MA R， et al. Validation of hyperFLOW in subsonic and transonic flow［J］. Acta Aerodynamica Sinica， 2016， 34（2）： 267-275.
19	王年华，常兴华，马戎，等. HyperFLOW软件非结构网格亚跨声速湍流模拟的验证与确认［J］. 力学学报， 2019， 51（3）： 813-825.
	WANG N H， CHANG X H， MA R， et al. Verification and validation of hyperflow solver for subsonic and transonic turbulent flow simulations on unstructured/hybrid grids［J］. Chinese Journal of Theoretical and Applied Mechanics， 2019， 51（3）： 813-825 （in Chinese）.
20	NANGIA R K， COPPIN J， GHOREYSHI M. A UCAV wing design， assessment and comparisons［C］∥ 2018 Applied Aerodynamics Conference. Reston： AIAA， 2018.
21	ALEXANDER M G， ANDERS S， JOHNSON S K， et al. Trailing edge blowing on a two-dimensional six-percent thick elliptical circulation control airfoil up to transonic conditions： NASA/TM-2005-213545［R］.Washington， D.C.： NASA， 2013.
22	LI Y H， QIN N. Airfoil gust load alleviation by circulation control［J］. Aerospace Science and Technology， 2020， 98： 105622.
23	XU H Y， QIAO C L， YANG H Q， et al. Active circulation control on the blunt trailing edge wind turbine airfoil［J］. AIAA Journal， 2017， 56（2）： 554-570.
24	LUO Z B， ZHAO Z J， LIU J F， et al. Novel roll effector based on zero-mass-flux dual synthetic jets and its flight test［J］. Chinese Journal of Aeronautics， 2022， 35（8）： 1-6.

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