类F-16飞行器风洞虚拟飞行试验研究

张石玉; 赵俊波; 付增良; 梁彬; 周家检

doi:10.11729/syltlx20180157

类F-16飞行器风洞虚拟飞行试验研究

doi: 10.11729/syltlx20180157

中国航天空气动力技术研究院, 北京 100074

基金项目:

国家自然科学基金 11502263

钱学森青年创新基金 800008000102008

详细信息

作者简介:
张石玉(1984-), 男, 四川遂宁人, 高级工程师。研究方向:飞行动力学与实验流体力学。通讯地址:北京市7201信箱56分箱(100074)。E-mail:zhangsy701@sina.com

通讯作者:
赵俊波, E-mail:zjbo503@sina.com

中图分类号: V211.7
计量
- 文章访问数: 527
- HTML全文浏览量: 294
- PDF下载量: 38
- 被引次数: 0
出版历程
- 收稿日期: 2018-10-29
- 修回日期: 2018-12-20
- 刊出日期: 2020-02-25

Wind tunnel based virtual flight testing research of F-16 fighter

China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 为研究高性能战斗机在大迎角机动飞行时复杂的非定常流动现象和运动-控制耦合现象，研制了三自由度风洞虚拟飞行试验系统，开展了类F-16飞行器模型风洞虚拟飞行试验。在小迎角试验中完成模型短周期运动模态模拟和控制律验证，在大迎角试验中测量到俯仰运动失稳现象，在负迎角试验中测量到横航向耦合失稳现象。研究表明：在横航向耦合失稳时，采用副翼增稳滚转通道难以恢复横航向稳定性，且可能发生运动-控制耦合振荡，而通过升降舵机动改变迎角可有效恢复横航向稳定性。
- F-16 /
- 3-DOF /
- 虚拟飞行试验 /
- 非定常气动力 /
- 大迎角 /
- 横航向稳定性
Abstract: A three degree-of-freedom (3-DOF) Wind Tunnel Based Virtual Flight Test (WTBVFT) system is developed to study unstable aerodynamic phenomena and maneuver characteristics coupling with motion of high-performance fighters maneuvering at high angle of attack. Based on this system, a series of 3-DOF virtual flight tests of F-16 fighter are performed. As the results, the short-time modes of flight dynamics are simulated from wind tunnel tests with small angle of attack, and control law are validated in those tests. Then an instability phenomenon in pitch is detected from tests with high angle of attack. A group of lateral-directional unstable aerodynamic-coupling motions are detected from tests when angle of attack is less than zero. In these tests, augmentation control of aileron cannot recover lateral-directional stability of flight, but always leading to control coupling motion. It is more effective to adopt elevator control to change angle of attack to recover the lateral-directional stability.
- F-16 /
- 3-DOF /
- virtual flight test /
- unstable aerodynamic /
- high angle of attack /
- lateral and directional stability

HTML全文

图 1 三自由度虚拟飞行试验系统

Figure 1. DOF virtual flight test system in wind tunnel

下载: 全尺寸图片幻灯片

图 2 三自由度轴承机构结构示意图

Figure 2. Configuration of 3 DOF-bearing combination

下载: 全尺寸图片幻灯片

图 3 三自由度轴承机构安装图

Figure 3. 3 DOF-bearing combination

下载: 全尺寸图片幻灯片

图 4 升降舵开环控制试验曲线

Figure 4. Open-loop control test curves in elevator maneuvering flight mode test

下载: 全尺寸图片幻灯片

图 5 方向舵开环控制试验曲线

Figure 5. Open-loop control test curves in rudder maneuvering test

下载: 全尺寸图片幻灯片

图 6 不同迎角自动配平试验曲线

Figure 6. Test curves of auto-trim at different angle of attack

下载: 全尺寸图片幻灯片

图 7 自动配平过程的阶跃响应

Figure 7. Step response in auto-trim test

下载: 全尺寸图片幻灯片

图 8 迎角正弦指令跟随性试验曲线

Figure 8. Sinusoid α command close-loop control test curves

下载: 全尺寸图片幻灯片

图 9 大迎角俯仰失稳现象

Figure 9. Longitudinal unstable phenomenon at high angle of attack

下载: 全尺寸图片幻灯片

图 10 迎角为－5°时横航向失稳现象

Figure 10. Lateral and directional unstable phenomenon (α=－5°)

下载: 全尺寸图片幻灯片

图 11 迎角为－7.5°时横航向失稳现象

Figure 11. Lateral and directional unstable phenomenon (α=－7.5°)

下载: 全尺寸图片幻灯片

图 12 迎角为－13°时横航向失稳现象

Figure 12. Lateral and directional unstable phenomenon (α=－13°)

下载: 全尺寸图片幻灯片

表 1 模型外形与实际F/A-16差异表

Table 1. Difference between test model and real F/A-16

外形	F/A-16	模型	稳定性影响
腹鳍	有	无	导致滚转静稳定性提高，偏航静稳定性降低
平尾	下反角 10°	下反角 5°	导致俯仰静稳定性提高，偏航静稳定性降低

下载: 导出CSV

表 2 升降舵开环机动气动参数辨识结果

Table 2. Aero-parameter identification results of elevator maneuvering test

	v=10 m/s	v=15 m/s	v=20 m/s	文献[21]
C_ma	-0.43	-0.46	-0.49
误差带	0.064	0.083	0.053
C_mq	-5.10	-5.96	-5.34	-5.8
误差带	1.48	1.88	1.05

下载: 导出CSV

表 3 控制系统阶跃信号动态指标

Table 3. Dynamic performance of control system in step response test

超调量σ/(°)	过渡过程时间t_s/ s	振荡次数N
2	5.25	≈3

下载: 导出CSV

参考文献(22)

[1]	LOWENBERG M H, KYLE H L. Development of a pendulum support rig dynamic wind tunnel apparatus[R]. AIAA 2002-4879, 2002.
[2]	DAVISON P M, LOWENBERG M H, BERNARDO M D. Modelling non-linear behavior in a single degree-of-freedom dynamic wind tunnel rig[R]. AIAA 2003-5314, 2003.
[3]	RICHARDSON T S, DUBS A, LOWENBERG M H, et al. Wind-tunnel testing of a dynamic state-feedback gain scheduled control system[R]. AIAA 2005-5976, 2005.
[4]	GATTO A, LOWENBERG M H. Evaluation of a three degree of freedom test rig for stability derivative estimation[J]. Journal of Aircraft, 2006, 43(6): 1747-1762. doi: 10.2514/1.19821
[5]	PATTINSON J, LOWENBERG M H, GOMAN M G. A multi-degree-of-freedom rig for the wind tunnel determination of dynamic data[R]. AIAA 2009-5727, 2009.
[6]	MAGILL J C, CATALDI P, MORENCY J R, et al. Demon-stration of a wire suspension system for dynamic wind tunnel testing[R]. AIAA 2004-1296, 2004.
[7]	BERGMANN A, HUEBNER A, LOESER T. Experimental and numerical research on the aerodynamics of unsteady moving aircraft[J]. Progress in Aerospace Sciences, 2007, 44(2): 121-137. http://cn.bing.com/academic/profile?id=275024735e837ece9b05e2aa83089fdf&encoded=0&v=paper_preview&mkt=zh-cn
[8]	CARNDUFF S D, ERBSLOEH S D, COOKE A K, et al. Development of a low cost dynamic wind tunnel facility utilizing MEMS inertial sensors[R]. AIAA 2008-196, 2008.
[9]	STENFELT G, RINGERTZ U. Yaw control of a tailless air-craft configuration[J]. Journal of Aircraft, 2010, 47(5): 1807-1810. doi: 10.2514/1.C031017
[10]	胡静, 李潜.风洞虚拟飞行试验技术初步研究[J].实验流体力学, 2010, 24(1): 95-99. doi: 10.3969/j.issn.1672-9897.2010.01.018 HU J, LI Q. Primary investigation of the virtual flight testing techniques in wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(1): 95-99. doi: 10.3969/j.issn.1672-9897.2010.01.018
[11]	赵忠良, 吴军强, 李浩, 等. 2.4 m跨声速风洞虚拟飞行试验技术研究[J].航空学报, 2016, 37(2): 504-512. http://d.old.wanfangdata.com.cn/Periodical/hkxb201602014
[12]	李浩, 赵忠良, 范召林.风洞虚拟飞行试验模拟方法研究[J].实验流体力学, 2011, 25(6): 72-76. doi: 10.3969/j.issn.1672-9897.2011.06.014 LI H, ZHAO Z L, FAN Z L. Simulation method for wind tunnel based virtual flight testing[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(6): 72-76. doi: 10.3969/j.issn.1672-9897.2011.06.014
[13]	赵忠良, 吴军强, 李浩, 等.高机动导弹气动/运动/控制耦合的风洞虚拟飞行试验技术[J].空气动力学学报, 2016, 34(1): 14-19. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb201601005 ZHAO Z L, WU J Q, LI H, et al. Wind tunnel based virtual flight testing of aerodynamics, flight dynamics and flight control for high maneuver missile[J]. Acta Aerodynamica Sinica, 2016, 34(1): 14-19. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb201601005
[14]	郭林亮, 祝明红, 孔鹏, 等.风洞虚拟飞行模型机与原型机动力学特性分析[J].航空学报, 2016, 37(8): 2583-2593. http://d.old.wanfangdata.com.cn/Periodical/hkxb201608025 GUO L L, ZHU M H, KONG P, et al. Analysis of dynamic characteristics between prototype aircraft and scaled-model of virtual flight test wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8): 2583-2593. http://d.old.wanfangdata.com.cn/Periodical/hkxb201608025
[15]	GUO L L, ZHU M H, FU H, et al. Modeling and simulation for a low speed wind tunnel virtual flight test rig[J]. Acta Aerodynamica Sinica, 2017, 35(5): 708-717. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kqdlxxb201705016
[16]	吕光男.风洞虚拟飞行试验中的飞行力学与控制问题研究[D].南京: 南京航空航天大学, 2009. LYU G N. Research on a flight dynamics and control in wind tunnel based virtual flight test[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2009.
[17]	张蓓蕾.基于RTX的风洞虚拟飞行试验数据采集与控制系统研究[D].南京: 南京航空航天大学, 2011. ZHANG B L. Research on data acquisition and control system of RTX for wind tunnel based virtual flight testing[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2011.
[18]	陈孟钢, 高金源.缩比模型飞机及其飞控系统与原型机的相似关系[J].飞行力学, 2003, 21(2): 34-37. doi: 10.3969/j.issn.1002-0853.2003.02.010 CHENG M G, GAO J Y. Similarityrelationships between scaled-model aircraft with its flight control system and prototype aircraft[J]. Flight Dynamics, 2003, 21(2): 34-37. doi: 10.3969/j.issn.1002-0853.2003.02.010
[19]	黄敏, 王中伟, 郭振云.评估飞控系统的风洞虚拟飞行试验系统与关键技术[J].国防科技大学学报, 2017, 39(2): 1-8. http://d.old.wanfangdata.com.cn/Periodical/gfkjdxxb201702001 HUANG M, WANG Z W, GUO Z Y. Wind tunnel based virtual flight testing system and key technologies for the evaluation of flight control system[J]. Journal of National University of Defense Technology, 2017, 39(2): 1-8. http://d.old.wanfangdata.com.cn/Periodical/gfkjdxxb201702001
[20]	梁彬, 张石玉, 赵俊波, 等.航空飞行器多自由度控制响应风洞试验技术研究[C]//第六届近代实验空气动力学会议论文集. 2017. LIANG B, ZHANG S Y, ZHAO J B, et al. Research on wind tunnel test technique of multi-degree of freedom control response for aviation aircraft[C]//Proc of the Sixth Modern Experimental Aerodynamics Conference. 2017.
[21]	GILBERT W P, NGUYEN L T, VANGUNST R W. Simulator study of the effectiveness of an automatic control system designed to improve the high-angle-of-attack characteristics of a fighter airplane[R]. NASA TN-D-8176, 1976.
[22]	祝立国, 王永丰, 庄逢甘, 等.高速高机动飞行器的横航向偏离预测判据分析[J].宇航学报, 2007, 28(6): 1550-1553. doi: 10.3321/j.issn:1000-1328.2007.06.022 ZHU L G, WANG Y F, ZHUANG F G, et al. The lateral-directional departure criteria analysis of high-speed and high maneuverability aircraft[J]. Journal of Astronautics, 2007, 28(6): 1550-1553. doi: 10.3321/j.issn:1000-1328.2007.06.022