Study on varying dynamic pressure control of flow field in 2m supersonic wind tunnel
-
摘要: 颤振试验要求风洞必须具备变速压试验能力，为此在2 m超声速风洞开展了流场变速压控制方法研究。针对总压宽范围多阶梯运行时主调压阀调节能力不一致的问题，采用总压分组、误差分段的控制方法解决了这一难题。通过基于主调压阀阀门特性曲线的控制方法，实现了总压上升速率可调的目标，避免了复杂的控制参数整定过程，显著减少了调试车次。试验结果表明：采用该控制方法，一次试验可以完成多个总压阶梯的控制，并且总压稳定精度达0.3%，速压超调量小于0.5 kPa，总压上升速率可调。通过本文工作，2 m超声速风洞具备了变速压试验能力，并成功应用于型号试验。Abstract: The flutter test requires that the wind tunnel must have the capability of varying dynamic speed pressure. Therefore, the flow field control method was studied in the 2m supersonic wind tunnel. For the problem that the regulating characteristics of the main pressure regulating valve are not consistent when the total pressure is running in a wide range of steps, the method of the total pressure grouping and error segmentation control is adopted to solve the problem. The control method based on the characteristic curve of the main pressure regulating valve is adopted to meet the requirements of adjustable total pressure rise rate, which avoids the process of setting control parameters and requires fewer times of debugging. Test results show that the method can complete multiple total pressure control in a test, the main pressure stable precision reaches 0.3%, the overshoot of the dynamic pressure is less than 0.5kPa, and the total pressure rise rate is adjustable. The 2m supersonic wind tunnel has the capability of varying dynamic speed pressure, and has been successfully applied in the model test.
-
图 3 改进后的总压稳定控制系统结构框图
Figure 3. Block diagram of the improved total pressure stability control
图 4 典型马赫数主调压阀特性曲线
Figure 4. Characteristic curves of main pressure valve of typical Mach numbers
-
[1] 李周复.风洞试验手册[M].北京:航空工业出版社, 2015. [2] 樊则文.导弹伺服气动弹性稳定性分析方法研究[D].西安: 西北工业大学, 2005. [3] 闫昱, 余立, 吕彬彬, 等.超声速颤振风洞试验技术研究[J].实验流体力学, 2016, 30(6): 76-80. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201606012Yan Y, Yu L, Lyu B B, et al. Research on flutter test technique in supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(6): 76-80. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201606012 [4] 郭洪涛, 陈德华, 吕彬彬, 等.大展弦比机翼跨声速静气动弹性风洞试验[J].空气动力学学报, 2017, 35(6): 841-845. doi: 10.7638/kqdlxxb-2015.0075Guo H T, Chen D H, Lyu B B, et al. Wind tunnel test on transonic static aeroelasticity of high-aspect-ratio wing[J]. Acta Aerodynamica Sinica, 2017, 35(6): 841-845. doi: 10.7638/kqdlxxb-2015.0075 [5] Ruhlin C L, Tuovila W J. Transonic and supersonic flutter investigation of 1/2-size models of all-movable canard surface of an expendable powered target[R]. NASA-TM-SX-616, 1961. [6] Ryneveld A D. Correlation of flutter analysis and test results for half-span SST wing models in subsonic and supersonic flow[R]. Boeing Commercial Airplane Company, 1973. [7] William D A. The aeroelastic design and testing of the F/A-22[C]//Proc of the 2005 USAF Aircraft Structural Integrity Program Conference. 2005. [8] 芮伟, 易凡, 杜宁, 等. 2.4 m跨声速风洞颤振试验流场控制技术研究[J].实验流体力学, 2012, 26(6): 83-86. doi: 10.3969/j.issn.1672-9897.2012.06.018Rui W, Yi F, Du N, et al. Study on flow field control technical of flutter test in 2.4 m transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(6): 83-86. doi: 10.3969/j.issn.1672-9897.2012.06.018 [9] 高鹏, 郭洪涛, 余立, 等. 0.6 m风洞亚跨声速连续变速压运行方式研究[C]//中国空气动力测控技术六届五次全国学术交流会论文集. 2014. [10] 季辰, 赵玲, 朱剑, 等.高超声速风洞连续变动压舵面颤振试验[J].实验流体力学, 2017, 31(6): 37-44. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201706006Ji C, Zhao L, Zhu J, et al. Hypersonic wind tunnel flutter test research on rudder models by continuously varying dynamic pressure[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(6): 37-44. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201706006 [11] 高川, 周波, 蒋婧妍, 等.基于LabVIEW的大型超声速风洞总压测控系统设计与应用[J].测控技术, 2014, 33(8): 84-87. doi: 10.3969/j.issn.1000-8829.2014.08.022Gao C, Zhou B, Jiang J Y, et al. Design and implementation of total pressure measurement and control system of large scare supersonic wind tunnel based on LabVIEW[J]. Measurement and Control Technology, 2014, 33(8): 84-87. doi: 10.3969/j.issn.1000-8829.2014.08.022 [12] 路波.高速风洞测力试验数据处理方法[M].北京:国防工业出版社, 2015. [13] 黄知龙, 徐大川, 张国彪.大型暂冲式风洞调压阀设计与特性实验[J].实验流体力学, 2012, 26(6): 87-90, 95. doi: 10.3969/j.issn.1672-9897.2012.06.019Huang Z L, Xu D C, Zhang G B. Aerodynamic design and characteristic test of large intermittent wind tunnel control value[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(6): 87-90, 95. doi: 10.3969/j.issn.1672-9897.2012.06.019 [14] 洪志伟.暂冲式风洞马赫数模糊自适应控制系统研究[D].沈阳: 东北大学, 2011.Hong Z W. The research of fuzzy adaptive control system in blow-off wind tunnel Mach number[D]. Shenyang: Northeastern University, 2011. [15] 金志伟, 杨兴锐, 苏北辰.基于神经网络的风洞马赫数预测控制仿真研究[J].兵工自动化, 2016, 35(3): 59-60. doi: 10.7690/bgzdh.2016.03.014Jin Z W, Yang X R, Su B C. Predictive control simulation research of Mach number in wind tunnel based on neural net-work[J]. Ordnance Industry Automation, 2016, 35(3): 59-60. doi: 10.7690/bgzdh.2016.03.014 [16] 尼文斌, 董金刚, 刘书伟, 等.自适应遗传PID算法在风洞风速控制中的应用[J].实验流体力学, 2015, 29(5): 84-88. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201505014Ni W B, Dong J G, Liu S W, et al. Application of PID based on adaptive genetic algorithms in wind velocity control system of wind tunnels[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(5): 84-88. http://d.old.wanfangdata.com.cn/Periodical/ltlxsyycl201505014 [17] 王博文, 黄叙辉, 秦建华, 等.遗传算法在跨超声速风洞总压控制中的应用[J].计算机测量与控制, 2017, 25(11): 74-77. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=jsjzdclykz201711019Wang B W, Huang X H, Qin J H, et al. Application of genetic algorithms in total pressure control system of transonic and supersonic wind tunnel[J]. Computer Measurement & Control, 2017, 25(11): 74-77. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=jsjzdclykz201711019 [18] 高川, 刘烽, 周波, 等.某超声速风洞测控系统[J].兵工自动化, 2013, 32(2): 63-66. http://d.old.wanfangdata.com.cn/Periodical/bgzdh201302018Gao C, Liu F, Zhou B, et al. Measure and control system of the supersonic wind tunnel[J]. Ordnance Industry Automation, 2013, 32(2): 63-66. http://d.old.wanfangdata.com.cn/Periodical/bgzdh201302018 [19] 褚卫华, 汤更生, 王帆. 2 m×2 m超声速风洞流场控制策略研究与实现[J].实验流体力学, 2012, 26(5): 98-102. doi: 10.3969/j.issn.1672-9897.2012.05.021Chu W H, Tang G S, Wang F. Research and realization on the control strategies of the 2 m×2 m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(5): 98-102. doi: 10.3969/j.issn.1672-9897.2012.05.021 -
下载:
点击查看大图
图(8)
计量
- 文章访问数: 152
- HTML全文浏览量: 90
- PDF下载量: 11
- 被引次数: 0
