Method of determining the location for aircraft icing prober
-
摘要: 结冰传感器的安装直接决定了冰的探测效果,在飞机设计阶段往往要耗费巨大的工作量来确定合适结冰传感器安装的位置。本文提出了一种高效确定结冰传感器安装位置的方法,其基本思路是采用数值计算的手段,获得不安装结冰传感器飞机流场的水滴容积分数分布;再根据水滴收集率的定义,得到传感器拟安装区域不同位置的水滴收集率,并与机翼表面的水滴收集率对比;从保证传感器可以起到预警作用的角度出发,进而给出传感器的安装位置。采用该方法对某型民航客机进行了分析,给出了该型飞机适合安装传感器的区域。在此基础上,将传感器加载到对应位置进行数值仿真验证。仿真结果显示:传感器探头处的水滴收集率与不加载传感器时该位置的水滴收集率基本一致,均大于同等条件机翼上的最大水滴收集率,符合飞机的结冰防护需求。本文方法可普遍应用于运输类飞机设计,有效提高结冰防护系统设计的效率。Abstract: The icing prober is an important component of an aircraft icing protection system. The location of an icing prober affects the ice detection results greatly. It often takes a huge amount of work to determine the location of the icing prober in the process of aircraft design. In this paper, a method of determining the installation position of the icing prober with high efficiency is presented. The basic idea is using numerical method to obtain the volume fraction distribution of water droplets in the flow field around the aircraft without introducing the icing prober firstly. Then the water collection efficiency at the locations where the prober may be installed is yielded according to the results of the volume fraction distribution of water droplets, and it is compared with water collection efficiency on the wing. Finally the locations of the prober are given from the point of view that the prober has an early warning function. The method is then used in an airliner design, and the position suitable for prober location is given. On this basis, the prober is loaded at the corresponding position and a full numerical simulation is taken for the combining configuration of the aircraft and the prober. The simulation results show that the water collection efficiency at the position with prober is similar to that without prober, and both are larger than the value on the wing under the same condition, which means the requirements of the icing protection for early warning are met. The method can be applied to the any transport aircraft and improve the design efficiency of the icing protection system.
-
表 1 各状态下机翼最大水滴收集率
Table 1. The maximum local collection coefficient on the wings under each condition
编号 速度
/(m·s-1)水滴直径
/μm迎角
/(°)最大水滴
收集率β1 116 20 2 0.623 2 116 40 2 0.720 3 116 20 4 0.615 4 116 40 4 0.718 5 116 20 6 0.570 6 116 40 6 0.708 7 127 20 2 0.635 8 127 40 2 0.742 9 127 20 4 0.639 10 127 40 4 0.742 11 127 20 6 0.603 12 127 40 6 0.733 表 2 截面1水滴收集率与机翼上最大水滴收集率的比值
Table 2. The ratio of local collection coefficient in section 1 to maximum local collection coefficient on the wing
编号 1_1 1_2 1_3 1_4 1_5 1_6 1 1.38 1.371 1.372 1.547 1.663 1.713 2 1.491 1.460 1.422 1.59 1.663 1.713 3 1.607 1.605 1.542 1.621 1.763 1.825 4 1.755 1.534 1.491 1.496 1.807 1.845 5 1.79 1.792 1.658 1.728 1.819 1.865 6 2.077 1.683 1.525 1.505 1.604 1.727 7 1.492 1.498 1.469 1.661 1.866 1.919 8 1.457 1.405 1.346 1.534 1.731 1.962 9 1.591 1.522 1.485 1.595 1.676 1.749 10 1.57 1.476 1.429 1.431 1.561 1.614 11 1.724 1.749 1.731 1.684 1.738 1.866 12 1.749 1.716 1.408 1.415 1.523 1.574 表 3 截面2水滴收集率与机翼上最大水滴收集率的比值
Table 3. The ratio of local collection coefficient in section 2 to maximum local collection coefficient on the wings
编号 2_1 2_2 2_3 2_4 2_5 2_6 1 1.586 1.608 1.705 1.893 2.173 2.191 2 2.239 1.834 1.836 2.666 3.229 2.767 3 1.756 1.662 1.747 1.882 2.007 2.124 4 3.167 2.244 1.938 2.223 3.173 3.023 5 1.904 1.910 1.904 2.000 2.126 2.174 6 2.884 2.915 2.313 2.191 2.589 2.852 7 1.600 1.618 1.689 1.892 2.048 2.269 8 1.708 1.685 1.786 2.226 3.251 2.680 9 1.711 1.706 1.725 1.861 1.982 2.110 10 2.717 1.913 2.110 2.474 3.146 2.901 11 1.796 1.877 1.835 1.929 2.045 2.276 12 2.900 3.094 2.580 2.098 2.887 2.702 表 4 截面3水滴收集率与机翼上最大水滴收集率的比值
Table 4. The ratio of local collection coefficient in section 3 to maximum local collection coefficient on the wings
编号 3_1 3_2 3_3 3_4 3_5 3_6 1 1.456 1.743 2.054 2.016 2.38 2.347 2 2.001 2.086 3.324 3.081 2.052 0.287 3 1.529 1.827 2.100 2.193 2.297 2.411 4 2.348 1.849 3.311 2.873 2.196 1.296 5 1.723 1.913 2.097 2.139 2.303 2.255 6 2.680 2.253 3.376 3.440 2.992 2.080 7 1.498 1.837 2.026 2.063 2.367 2.353 8 1.848 2.036 3.016 3.166 0.856 0.250 9 1.553 1.788 2.096 2.054 2.359 2.456 10 2.729 2.172 3.366 3.245 1.594 0.862 11 1.807 1.839 2.144 2.136 2.343 2.239 12 2.839 2.822 3.363 3.323 1.438 2.988 表 5 截面4水滴收集率与机翼上最大水滴收集率的比值
Table 5. The ratio of local collection coefficient in section 4 to maximum local collection coefficient on the wings
编号 4_1 4_2 4_3 4_4 4_5 4_6 1 2.723 2.137 2.478 2.390 2.510 2.485 2 2.276 0.216 0.089 0.211 0.001 0.089 3 2.295 2.328 2.190 2.705 2.487 2.310 4 0.933 1.642 1.277 0.03 0.000 0.015 5 2.704 2.27 2.476 2.573 2.640 2.513 6 1.588 2.188 0.72 0.122 0.030 0.089 7 2.402 2.245 2.365 2.614 2.279 2.445 8 1.203 1.800 0.057 0.015 0.000 0.001 9 2.539 2.253 2.258 2.587 2.501 2.578 10 1.059 1.332 0.459 0.087 0.003 0.001 11 2.694 2.352 2.505 2.488 2.52 2.433 12 0.618 1.155 0.116 0.015 0.004 0.143 -
[1] Cebeci T, Kafyeke F. Aircraft icing[J]. Annual Review of Fluid Mechanics, 2003, 35:11-21. doi: 10.1146/annurev.fluid.35.101101.161217 [2] 桂业伟, 周志宏, 李颖晖, 等.关于飞机结冰的多重安全边界问题[J].航空学报, 2017, 38(2):520723-520734. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=hkxb201702001&dbname=CJFD&dbcode=CJFQGui Y W, Zhou Z H, Li Y H, et al. Multiple safety boundaries protection on aircraft icing[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):520723-520734. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=hkxb201702001&dbname=CJFD&dbcode=CJFQ [3] 张恒, 李杰, 龚志斌.多段翼型缝翼前缘结冰大迎角分离流动数值模拟[J].航空学报, 2017, 38(2):520733-520746. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=hkxb201702005&dbname=CJFD&dbcode=CJFQZhang H, Li J, Gong Z B. Numerical simulation of separated flow around a multi-element airfoil at high angle of attack with iced slat[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):520733-520746. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=hkxb201702005&dbname=CJFD&dbcode=CJFQ [4] 朱东宇, 张付昆, 裴如男, 等.临界冰形确定方法及其对气动特性的影响研究[J].空气动力学学报, 2016, 34(6):714-720. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=kqdx201606004&dbname=CJFD&dbcode=CJFQZhu D Y, Zhang F K, Pei R N, et al. Research on critical ice shape determination and its effects on aerodynamics[J]. Acta Aerodynamica Sinica, 2016, 34(6):714-720. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=kqdx201606004&dbname=CJFD&dbcode=CJFQ [5] 薛源, 徐浩军, 裴彬彬, 等.基于蒙特卡罗法的飞机结冰后动力学特性分析[J].实验流体力学, 2016, 30(2):26-31, 37. http://www.syltlx.com/CN/abstract/abstract10913.shtmlXue Y, Xu H J, Pei B B, et al. Dynamic characteristics analysis after aircraft icing based on Monte Carlo method[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(2):26-31, 37. http://www.syltlx.com/CN/abstract/abstract10913.shtml [6] Aircraft Ice Protection Appendix K. Ice and icing condition detection[S]. AC20-73A, 2006. [7] 张洪, 叶林, 张杰.飞机结冰探测技术初探[J].国际航空, 2007, 10:65-67. http://www.doc88.com/p-2671293193850.htmlZhang H, Ye L, Zhang J. Discussion on problems of aircraft ice detection[J]. International Avation, 2007, 10:65-67. http://www.doc88.com/p-2671293193850.html [8] 张杰, 周磊, 张洪, 等.飞机结冰探测技术[J].仪器仪表学报, 2006, 27(12):1578-1586. doi: 10.3321/j.issn:0254-3087.2006.12.005Zhang J, Zhou L, Zhang H, et al. Aircraft icing detection technology[J]. Chinese Journal of Scientific Instrument, 2006, 27(12):1578-1586. doi: 10.3321/j.issn:0254-3087.2006.12.005 [9] Jackson D, Owens D, Cronin D, et al. Certification and integration aspects of a primary ice detection system[R]. AIAA-2001-0398, 2001. [10] 张洪, 张文倩, 郑英.过冷大水滴结冰探测技术研究进展[J].实验流体力学, 2016, 30(3):33-39. http://www.syltlx.com/CN/abstract/abstract10931.shtmlZhang H, Zhang W, Zheng Y. Research progress on supercooled large droplet icing detection technology[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(3):33-39. http://www.syltlx.com/CN/abstract/abstract10931.shtml [11] 周峰, 冯丽娟, 徐超军, 等.民用飞机适航用临界冰形的确定及验证[J].实验流体力学, 2016, 30(2):8-13. http://www.syltlx.com/CN/abstract/abstract10910.shtmlZhou F, Feng L J, Xu C J, et al. Determination and verification of critical ice shape for the certification of civil aircraft[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(2):8-13. http://www.syltlx.com/CN/abstract/abstract10910.shtml [12] 史献林, 王大伟.民用飞机结冰探测器安装位置研究[J].科技信息, 2011, 22:806-807. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kjxx201122676 [13] 易贤. 飞机积冰的数值计算与积冰试验相似准则研究[D]. 绵阳: 中国空气动力研究与发展中心, 2007.Yi X. Numerical computation of aircraft icing and study on icing test scaling law[D]. Mianyang: China Aerodynamics Research and Development Center, 2007. [14] 易贤, 王开春, 桂业伟, 等.结冰面水滴收集率欧拉计算方法研究及应用[J].空气动力学学报, 2010, 28(5):596-601. http://industry.wanfangdata.com.cn/hk/Detail/Periodical?id=Periodical_kqdlxxb201005019Yi X, Wang K C, Gui Y W, et al. Study on Eulerian method for icing collection efficiency computation and its application[J]. Acta Aerodynamica Sinica, 2010, 28(5):596-601. http://industry.wanfangdata.com.cn/hk/Detail/Periodical?id=Periodical_kqdlxxb201005019