基于深度学习技术的激波风洞智能测力系统研究
DEEP-LEARNING-BASED INTELLIGENT FORCE MEASUREMENT SYSTEM USING IN A SHOCK TUNNEL
查看参考文献29篇
|
文摘
|
高焓条件气动力测量试验对高超声速飞行器气动外形设计和优化起决定性作用.通常采用脉冲风洞(如激波风洞)产生高温、高压驱动气体以模拟高超声速高焓试验气流.在脉冲风洞对高超飞行器模型进行测力试验时,测力天平输出信号结果无法摆脱惯性载荷的干扰影响,其导致的测力模型低频振动问题基本无法通过滤波彻底解决,尤其对试验时间只有几毫秒的情况,六分量测力天平的结构设计研究受到了极大挑战.因此,对实现短试验时间条件高性能测力的深入研究发现,天平动态校准凸显重要性和必要性.本研究提出一种新的基于人工智能深度学习技术的单矢量动态自校准方法和智能测力系统概念,并应用于目前激波风洞测力试验中.该动校方法的最主要特点之一是对整体测力系统的校准,而非仅仅针对天平,并且保证校准的测力系统即为风洞试验对象,确保校准与应用的一致性.在测试评估中,测试样本和风洞试验验证均得到了较为理想的效果,大幅度低频振动干扰基本被消除,脉冲风洞测力的精度和可靠性得到了大幅提高. |
|
其他语种文摘
|
Aerodynamic force measurement in high-enthalpy flow is very important for the design and optimization of hypersonic vehicles.Currently,impulse facilities are used for generating high-temperature and high-pressure driving gas to simulate the high-enthalpy flow with hypersonic flight-conditions,such as a shock tunnel.However,when force tests are conducted in an impulse facility,the inertial force has a large influence on the measuring results,which creates low-frequency vibrations of the test model and its motion cannot be addressed through digital filtering.In the case of a few milliseconds of test time,the structural design of the six-component balance is greatly challenged.Therefore,dynamic calibration becomes very important for improving the precision and accuracy of force measurement during short-duration.A new method,deep-learning-based single-vector dynamic self-calibration of the force measurement system,and intelligent force measurement system are proposed for obtaining high-accurate aerodynamic force in impulse facilities.One of the main features of this dynamic calibration method is the calibration of the overall force measurement system,not just the balance.Applying this method,the calibrated force measurement system is the wind tunnel test object,which ensures the consistency of calibration and application.In the evaluation,the test verification has achieved relatively ideal results,the large-scale low-frequency vibration interference has been basically eliminated,and the accuracy and reliability of the force measurement in impulse facility have been greatly improved. |
|
来源
|
力学学报
,2020,52(5):1304-1313 【核心库】
|
|
DOI
|
10.6052/0459-1879-20-190
|
|
关键词
|
激波风洞
;
人工智能
;
测力系统
;
动态校准
;
气动力测量
;
应变天平
|
|
地址
|
1.
中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
2.
中国科学院大学工程科学学院, 北京, 100049
|
|
语种
|
中文 |
|
文献类型
|
研究性论文 |
|
ISSN
|
0459-1879 |
|
学科
|
航空 |
|
基金
|
国家自然科学基金资助项目
|
|
文献收藏号
|
CSCD:6829047
|
参考文献 共
29
共2页
|
|
1.
黄志澄. 高超声速气动试验的新进展.
气动实验与测量控制,1993,7(1):1-13
|
被引
6
次
|
|
|
|
|
2.
Bernstein L. Force measurement in short-duration hypersonic facilities.
AGAR Dograph No. 214,1975
|
被引
1
次
|
|
|
|
|
3.
Storkmann V. Force Measurements in Hypersonic Impulse Facilities.
AIAA Journal,1998,36(3):342-348
|
被引
6
次
|
|
|
|
|
4.
程忠宇. 多加速度计振动分离惯性补偿测力技术.
流体力学实验与测量,1999,13(4):57-60
|
被引
4
次
|
|
|
|
|
5.
Naumann K W. Technique for aerodynamic force measurement in shock tunnels.
Shock Waves,1991,1(3):223-232
|
被引
5
次
|
|
|
|
|
6.
Joarder R. A new free floating accelerometer balance system for force measurements in shock tunnels.
Shock Waves,2003,13:409-412
|
被引
7
次
|
|
|
|
|
7.
Saravanan S. Aerodynamic force measurement using 3-component accelerometer force balance system in a hypersonic shock tunnel.
Shock Waves,2009,18:425-435
|
被引
9
次
|
|
|
|
|
8.
Sahoo N. An accelerometer balance system for measurement of aerodynamic force coefficients over blunt bodies in a hypersonic shock tunnel.
Meas. Sci. Technol,2003,14:260-272
|
被引
9
次
|
|
|
|
|
9.
Robinson M. Design and implementation of an internal stress wave force balance in a shock tunnel.
CEAS Space Journal,2011,1:45-57
|
被引
7
次
|
|
|
|
|
10.
Sanderson S.
A drag measurement technique for free-piston shock tunnels. AIAA Paper 91-0540,1991
|
被引
1
次
|
|
|
|
|
11.
Mee D. Three-component force balance for flows of millisecond duration.
AIAA Journal,1996,34(3):590-595
|
被引
9
次
|
|
|
|
|
12.
Seiler F. Development of a free flight force measuring technique (FFM) at the ISL Shock Tube Laboratory.
25th International Symposium on Shock Wave,2005
|
被引
1
次
|
|
|
|
|
13.
Wey P. Determination of aerodynamic coefficients from shock tunnel free-flight trajectories.
Proceedings of the 28th Aerodynamic Measurement Technology, Ground Testing and Flight Testing Conference,2012
|
被引
1
次
|
|
|
|
|
14.
Martinez B. Free-flight measurement technique in shock tunnel.
Proceedings of the 30th Aerodynamic Measurement Technology and Ground Testing Conference,2014
|
被引
1
次
|
|
|
|
|
15.
Tanno H. Free-flight measurement technique in the free-piston shock tunnel HIEST.
Review of Scientific Instrumentation,2014,85:045112
|
被引
4
次
|
|
|
|
|
16.
Laurence S. An improved visualization-based force measurement technique for short-duration hypersonic facilities.
Experiments in Fluids,2010,48:949-965
|
被引
7
次
|
|
|
|
|
17.
Marineau E. Force measurements in hypervelocity flows with an acceleration compensated strain gage balance.
Journal of Spacecraft and Rockets,2012,49(3):474-482
|
被引
9
次
|
|
|
|
|
18.
Wang Y P. Force measurement using straingauge balance in a shock tunnel with long test duration.
Review of Scientific Instruments,2016,87:055108
|
被引
5
次
|
|
|
|
|
19.
Wang Y P. Design of a pulse-type strain gauge balance for a long-test-duration hypersonic shock tunnel.
Shock Waves,2016,26(6):835-844
|
被引
9
次
|
|
|
|
|
20.
汪运鹏. 长试验时间激波风洞测力技术研究.
力学学报,2016,48(3):545-556
|
被引
12
次
|
|
|
|
|
了解气象卫星更多信息，请访问