Thrust/drag calibrations for integral inlet and jet testing on a aircraft with blended wing/body
-
摘要: 在研究嵌入式动力装置的进/排气效应对扁平融合式飞机气动特性的影响时，发展了一种整体式进/排气模拟试验方法及推/阻校准方法。采用与飞机模型融为一体的内置式引射器同时模拟飞机的进气效应和排气效应，模型气动载荷与引射器工作时的作用力由天平同时测量获得；把模型推进系统部分分离出来，在TPS校准箱中进行推/阻校准，建立模型气动载荷与推/阻力之间的剥离方法，获得真实的进/排气效应影响试验数据。用典型的背负式进气道扁平融合式飞机模型进行了推/阻校准试验和进/排气影响风洞验证试验，验证了该方法的可行性。Abstract: When researching on the influence of the inlet and jet exhaust plume of the embedded propulsion system on the aerodynamic characteristics of a blended wing/body aircraft, a calibration method of thrust and drag for the integral inlet and jet simulation test is developed. The embedded ejector integrated with the aircraft model is employed to simulate the inlet and jet effects simultaneously. The total value of the aerodynamic load on the aircraft model and the thrust of the working ejector are measured by the balance. With the TPS calibration tank, the thrust and drag of the propulsion system can be calibrated, the decoupling of the aerodynamic load on the aircraft model with the thrust and drag of the propulsion system can be efficaciously realized, and the reliability data of inlet and jet effects can be obtained. The thrust/drag calibration method is verified by the inlet and jet simultaneously testing with black-embedded inlets of a blended wing/body aircraft.
-
Key words:
- blended wing/body model /
- inlet and jet /
- integral simulation /
- thrust/drag calibrations /
- ejector
-
[1] 李周复.风洞试验手册[M].北京:航空工业出版社, 2015.Li Z F. Handbook of wind tunnel test[M]. Beijing:Aeronautics Industry Press, 2015. [2] Burgsmüller W, Castan C, Kooi J W, et al. Recent developments in low-speed TPS-testing for engine integration drag and installed thrust reverser simulation[R]. Aerospace paper, 1992. [3] Bousquet J M. Survey of engine integration testing in ONERA wind tunnels[R]. AIAA-2005-3705, 2005. [4] 徐铁军, 郝卫东, 李聪, 等.气动院校准箱工作原理分析及TPS校准目标量的获得方法[J].流体力学实验与测量, 2004, 18(4):99-104. doi: 10.3969/j.issn.1672-9897.2004.04.021Xu T J, Hao W D, Li C, et al. Analysis of operative principles of calibration tank in CARIA and acquired methods of objective parameters in TPS calibration[J]. Experiments and Measurements in Fluid Mechanics, 2004, 18(4):99-104. doi: 10.3969/j.issn.1672-9897.2004.04.021 [5] 芮伟, 易凡, 杜宁, 等. 2.4 m跨声速风洞TPS测控系统设计与实现[J].实验流体力学, 2008, 22(4):72-75. doi: 10.3969/j.issn.1672-9897.2008.04.016Rui W, Yi F, Du N, et al. Design and realization of TPS measurement and control system for 2.4 m transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2008, 22(4):72-75. doi: 10.3969/j.issn.1672-9897.2008.04.016 [6] 陶洋, 刘光远, 张兆, 等.高速风洞带动力模拟试验TPS短舱唇口设计[J].航空动力学报, 2013, 28(5):1081-1085. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201305016Tao Y, Liu G Y, Zhang Z, et al. Engine nacelle lip design for high speed TPS wind tunnel tests[J]. Journal of Aerospace Power, 2013, 28(5):1081-1085. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201305016 [7] 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].实验流体力学, 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 [8] 章荣平, 王勋年, 黄勇.发动机动力模拟风洞试验中的空气桥技术[J].航空动力学报, 2015, 30(4):910-914. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201504018Zhang R P, Wang X N, Huang Y. Air bridge technology for engine power simulate test in wind tunnel[J]. Journal of Aerospace Power, 2015, 30(4):910-914. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb201504018 [9] Robinson C E. Evaluation of ejector-powered simulator at transonic Mach numbers[R]. AIAA-79-1165, 1979. [10] 郝卫东.高速风洞发动机进/排气动力模拟试验技术[J].北京航空航天大学学报, 2005, 31(4):459-463. doi: 10.3969/j.issn.1001-5965.2005.04.020Hao W D. Simulate test technique for engine air intake and exhaust in high speed wind tunnel[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(4):459-463. doi: 10.3969/j.issn.1001-5965.2005.04.020 [11] 王勋年, 巫朝君, 陈洪, 等.战斗机推进系统模拟低速风洞试验技术研究[J].实验流体力学, 2011, 25(3):46-49. doi: 10.3969/j.issn.1672-9897.2011.03.011Wang X N, Wu C J, Chen H, et al. Investigation on test technique of fighters with propulsion simulation in low wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(3):46-49. doi: 10.3969/j.issn.1672-9897.2011.03.011 [12] 郁新华, 陶于金, 张琳.飞翼布局无人机进/排气效应风洞试验研究[J].空气动力学学报, 2013, 31(4):494-497.Yu X H, Tao Y J, Zhang L. Wind tunnel experimental research on effect of air intake and exhaust on the aerodynamics of flying wing UAV[J]. Acta Aerodynamica Sinica, 2013, 31(4):494-497. [13] Grellmann H W. B-2 aerodynamic design[R]. AIAA-90-1802, 1990. [14] Smith C L, Riddle T R. Jet effects testing considerations for the next-generation long-range strike aircraft[R]. AIAA-2008-1621, 2008. [15] 陈嵩禄, 云梦东, 刘日明, 等.飞机设计手册-动力装置系统设计[M].北京:航空工业出版社, 2006. [16] von Geyr H Frhr, Rossow C C. A correct thrust determination method for turbine powered simulators in wind tunnel testing[R]. AIAA-2005-3707, 2005. [17] 塞登J, 戈德史密斯E L.进气道空气动力学[M].骆长天, 涂鼎立, 程大光, 等译.沈阳: 航空工业部第六〇一研究所, 1992. -
下载:
点击查看大图
图(11)
计量
- 文章访问数: 200
- HTML全文浏览量: 88
- PDF下载量: 7
- 被引次数: 0
