Research on static thrust accurate measurement testing technology of vectoring nozzle
-
摘要: 详细论述了矢量喷管静推力精确测量试验技术的原理、所需设备以及试验方法，该技术主要模拟喷管模型喷流落压比以及出口马赫数相似参数，将模型安装在推力测量平台的真空试验舱中，同时利用外式天平进行矢量喷管气动力的精确测量。试验数据经过流量修正、安装姿态修正、基于橡胶膜片的空气桥系统对于天平的压力影响以及流量影响修正之后，即可以得到较为精确的矢量喷管静推力值、推力系数以及矢量角等参数。试验结果表明：在推力测量平台进行矢量喷管静推力测量试验，轴向、法向推力系数以及矢量角随落压比的变化规律正确，试验精度满足国军标要求，达到型号应用水平。Abstract: The principle, test bench and method of the vectoring nozzle static thrust measurement experimental technology are introduced in this paper. The primary simulation parameters are the nozzle pressure ratio (NPR) and the Mach number at the nozzle exhaust. The nozzle model is installed in the vacuum cabin of the thrust test bench, and aerodynamic forces of the nozzle model are measured accurately by the wall balance. After the mass flow correction, installation position correction, and the correction of pressure effect and mass flow effect to the balance caused by the air bridge system based on the rubber membrane, the exact values of the vector nozzle static thrust, thrust coefficient and vector angles etc. are obtained. The experimental results show that the axial thrust coefficient, the normal thrust coefficient and the variation trend of vector angle with NPR, which is measured in the vector nozzle static thrust measurement experiment using the thrust test bench are correct, the test results precision can satisfy the GJB requirements for force-test precision, and the technique can be applied in project test.
-
Key words:
- vector nozzle /
- static thrust /
- NPR /
- thrust coefficient /
- vector angle /
- air bridge
-
图 6 临界流文氏管在平台内的安装照片
Figure 6. Photograph of critical Venturi nozzle installed in thrust testing bench
图 8 无流动状态下纵向三元的压力修正曲线
Figure 8. Modified curve of pressure affection of bellows system
图 9 流动状态下纵向三元的流量影响修正曲线
Figure 9. Modified curve of mass-flow affection of bellows system
表 1 相对位置偏差结果
Table 1. Position error results
Y/mm Z/mm α/(°) β/(°) γ/(°) 流量校准试验 0 0 0.12 0.16 0.19 喷管静推力试验 0 0 0.12 0.17 0.19 
下载: 导出CSV
表 2 光天平及带空气桥天平精准度
Table 2. Calibration results of two balances
Y MZ X 设计载荷加载
载荷/(N, N·m)1250
8751750
14002500
1750综合加载
重复性误差/%合格指标 0.20 0.20 0.30 先进指标 0.06 0.06 0.10 光天平 0.03 0.01 0.03 空气桥天平 0.027 0.01 0.032 综合加载
准度误差/%合格指标 0.40 0.40 0.50 先进指标 0.10 0.10 0.20 光天平 0.35 0.10 0.20 空气桥天平 0.39 0.21 0.16
下载: 导出CSV
表 3 光天平与及带空气桥天平系统主系数差异
Table 3. Main coefficient differences between two balances
Y MZ X 光天平 10.199 1.477 10.254 带空气桥天平 10.217 1.491 10.303 绝对差异 -0.018 -0.014 -0.049 相对差异/% -0.18 -0.94 -0.48
下载: 导出CSV
表 4 试验数据重复性结果
Table 4. Repetition of testing
车次 NPR Cfx Cfy θ/(°) 1 25.26 0.9493 -0.1886 -11.23 2 25.32 0.9502 -0.1880 -11.19 3 25.30 0.9498 -0.1886 -11.23 4 25.27 0.9492 -0.1884 -11.23 5 25.29 0.9497 -0.1884 -11.22 6 25.30 0.9500 -0.1888 -11.24 7 25.28 0.9494 -0.1882 -11.21 aver 25.29 0.9497 -0.1884 -11.22 σ 0.0188 0.0003 0.0002 0.0154
下载: 导出CSV
-
[1] 王如根, 高坤华.航空发动机新技术[M].北京:航空工业出版社, 2003.Wang R G, Gao K H. The new technology of aero engine[M]. Beijing:Aviation Industry Press, 2003. [2] Steven A. Thrust vectoring:a new angle to air superiority[J]. Mechanical Engineering, 1995:58-64. https://dialnet.unirioja.es/servlet/articulo?codigo=401939 [3] Thomas M B, Norbert C B. Thrust vector behaviorof highly integrated asymmetric nozzle for advanced fighter aircraft[R]. AIAA-98-0948, 1998. [4] 王猛杰, 额日其太, 王强, 等.激波矢量控制喷管落压比影响矢量性能及分离区控制数值模拟[J].航空动力学报, 2015, 30(2):526-536. doi: 10.13224/j.cnki.jasp.2015.03.002.htmlWang M J, Eriqitai, Wang Q, et al, Numerical simulation of nozzle pressure ratio effect on vector performance and separation control for shock vector control nozzle[J]. Journal of Aerospace Power, 2015, 30(2):526-536. doi: 10.13224/j.cnki.jasp.2015.03.002.html [5] Karen A D. Summary of fluidic thrust vectoring research conducted at NASA Langley research center[R]. AIAA-2003-3800, 2003. http://www.cs.odu.edu/~mln/ltrs-pdfs/NASA-aiaa-2003-3800.pdf [6] Wing D J. Static investigation of two fluidic thrust-vectoring concepts on a two-dimensional convergent-divergent nozzle[R]. NASA TM-4574, 1994. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19950012627.pdf [7] Deere K A. Computational investigation of the aerodynamic effects on fluidic thrust vectoring[R]. AIAA-2000-3598, 2000. https://www.scientific.net/amr.998-999.613.pdf [8] Andrew J N, Fernando N G, John Y. Performance studies of shock vector control fluidic thrust vectoring[R]. AIAA-2007-5086, 2007. [9] 谭杰, 金捷.单边膨胀喷管几何参数对内特性和流场的影响[J].推进技术, 2013, 34(2):152-160. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=tjjs201302003&dbname=CJFD&dbcode=CJFQTan J, Jin J. Effect of geometric parameters on internalperformance and flow field on single expansion ramp nozzles[J]. Journal of Propulsion Technology, 2013, 34(2):152-160. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=tjjs201302003&dbname=CJFD&dbcode=CJFQ [10] Bousquet J M. Survey of engine integration testing in ONERA wind tunnels[C]. 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005. http://mams.rmit.edu.au/42tca1i3stiy.doc [11] Fluidic Dynamics Panel Working Group 19. Sonic nozzles for mass flow measurement and reference nozzles for thrust verification[R]. AGARD-AR-321, 1997. http://dtic.mil/cgi-bin/GetTRDoc?AD=ADA326995 [12] 范洁川.风洞试验手册[M].北京:航空工业出版社, 2002.Fan J C. Handbook of wind tunnel test[M]. Beijing:Aviation Industry Press, 2002. [13] Beale D K. Experimental measurement of venturi discharge coefficient including sensitivity to geometric and flow quality variables[R]. AIAA-99-0304, 1999. [14] 章荣平, 王勋年, 黄勇, 等.低速风洞全模TPS试验空气桥的设计与优化[J].试验流体力学, 2012, 26(6):48-52. doi: 10.3969/j.issn.1672-9897.2012.06.011Zhang R P, Wang X N, Huang Y, et al. Design and optimization of the air bridge for low speed full-span TPS test[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(6):48-52. doi: 10.3969/j.issn.1672-9897.2012.06.011 [15] Becle J P, Girard D. Development of strain gage balances with air flow-through system for ONERA wind tunnels[C]. Seventy-first Simi-annual S T A Meeting, 1989. -
点击查看大图
计量
- 文章访问数: 145
- HTML全文浏览量: 93
- PDF下载量: 13
- 被引次数: 0
