Ice shape modulation is a technology that significantly reduces the power of anti-icing and broadens the safety boundary of ice-tolerant flight under the premise of ensuring the aerodynamic performance and flight safety of the aircraft. It uses the power excited by the plasma actuator to change the dangerous spanwise continuous ice into safer intermittent ice, thereby improving the ice-containing flight capability of the aircraft. To verify the feasibility of the technology, plasma anti-icing experiments were carried out in the ice wind tunnel. The results show that the nanosecond pulse plasma actuator can change the continuous ice in the airfoil front edge into discontinuous ice. The formation of a wave-like front edge preliminarily verifies the ability of plasma ice shape modulation. To explore the effect of the technology on the aerodynamic performance of the wing, 3D printed typical ice shapes (glaze ice, rime ice, and mixed ice) were intermittently arranged on the NACA0012 airfoil at an incoming flow velocity of 30 m/s. The aerodynamic performance was tested in the wind tunnel, and the influence of different ratios of icing area to non-icing area and the width of the icicle L on the aerodynamic performance of the airfoil was compared and analyzed. The results show that for the glaze ice, the aerodynamic performance has the best improvement when the ratio of icing area to non-icing area is equal to 1∶1 (L=2 cm), with the maximum lift coefficient being increased by 34.8% and the drag coefficient at the angle of attack of 10° being reduced by 86.0% in comparison with the full-ice state. For the rime ice and mixed ice, the aerodynamic performance has the best improvement when the ratio is equal to 3∶2 (L=6 cm) and to 3∶2 (L=4 cm), with the maximum lift coefficient being increased by 19.7% and 30.6% respectively and the drag coefficient being significantly reduced in comparison with the full-ice state.
[1] MA L. Aircraft icing and flight safety[J]. Ciuil Aviation Economics & Technology, 1999(5): 37-38 (in Chinese). 马玲. 飞机积冰与飞行安全[J]. 民航经济与技术, 1999(5): 37-38.
[2] JIANG T J. Investigation of icing accretion influences on aircraft flight performance[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2008: 28-39 (in Chinese). 蒋天俊. 结冰对飞机飞行性能影响的研究[D]. 南京: 南京航空航天大学, 2008: 28-39.
[3] WANG Q D. Investigation of the aircraft longitudinal stability and control with ice accretion[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2009: 16-24 (in Chinese). 王起达. 结冰后飞机的纵向稳定性和操纵性研究[D]. 南京: 南京航空航天大学, 2009: 16-24.
[4] LI Q Y, BAI T, ZHU C L. Research summary ofmechnical de-icing systems of aircrafts[J]. Aircraft Design, 2015, 35(4): 73-77 (in Chinese). 李清英, 白天, 朱春玲. 飞机机械除冰系统的研究综述[J]. 飞机设计, 2015, 35(4): 73-77.
[5] LI Q Y, ZHU C L, BAI T. De-icing experiment and numerical simulation of the electro-impulse de-icing system[J]. Journal of Aerospace Power, 2012, 27(2): 350-356 (in Chinese). 李清英, 朱春玲, 白天. 电脉冲除冰系统的除冰实验与数值模拟[J]. 航空动力学报, 2012, 27(2): 350-356.
[6] LEVIN I A. USSR electric impulse de-icing system design[J]. Aircraft Engineering and Aerospace Technology, 1972, 44(7): 7-10.
[7] Aircraft de-icing/anti-icing fluids-ISO type Ⅰ: ISO 11075—2007[S]. 2007 (in Chinese). 航空器除冰液和防冰液. ISO Ⅰ型: ISO 11075—2007[S]. 2007.
[8] ENGINEERS S O A. Fluid, aircraft deicing/anti-icing, non-Newtonian, (pseudoplastic): SAE types Ⅱ, Ⅲ, and Ⅳ[R]. 1998.
[9] PLANQUART P, BORRE G V, BUCHLIN J M. Experimental and numerical optimization of a wing leading edge hot air anti-icing system[C]//43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston: AIAA, 2005.
[10] BU X Q, YU J, LIN G P, et al. Investigation of the design of wing hot-air anti-icing system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(8): 927-930 (in Chinese). 卜雪琴, 郁嘉, 林贵平, 等. 机翼热气防冰系统设计[J]. 北京航空航天大学学报, 2010, 36(8): 927-930.
[11] LIN G P, BU X Q, SHEN X B. Aircraft icing and anti-icing technology[M]. Beijing: Beihang University Press, 2016: 32-36 (in Chinese). 林贵平, 卜雪琴, 申晓斌. 飞机结冰与防冰技术[M]. 北京: 北京航空航天大学出版社, 2016: 32-36.
[12] GU H Y, SANG W M, PANG R, et al. Numericalsimulation of wing hot air anti-icing and ice ridge formation[J]. Physics of Gases, 2019, 4(4): 41-49 (in Chinese). 顾洪宇, 桑为民, 庞润, 等. 机翼热气防冰及冰脊形成数值模拟[J]. 气体物理, 2019, 4(4): 41-49.
[13] TIRUMALA R, BENARD N, MOREAU E, et al. Temperature characterization of dielectric barrier discharge actuators: Influence of electrical and geometric parameters[J]. Journal of Physics D: Applied Physics, 2014, 47(25): 255203.
[14] POPOV N A. Fast gas heating in a nitrogen-oxygen discharge plasma: Ⅰ. Kinetic mechanism[J]. Journal of Physics D: Applied Physics, 2011, 44(28): 285201.
[15] LIU Y, KOLBAKIR C, HU H Y, et al. An explorative study to use thermal effects of duty-cycled plasma actuation for aircraft icing mitigation[C]//2018 Atmospheric and Space Environments Conference. Reston: AIAA, 2018.
[16] PETRENKO V F. Plasma-based de-icing: US200201709-09[P]. 2002-11-21.
[17] MENG X, CHEN Z, SONG K. AC-and NS-DBD plasma flow control research[C]//Proceedings of the 2nd NPU-DLR Workshop on Aerodynamics. Cologne: German Aerospace Center (DLR), 2014.
[18] CAI J S, TIAN Y Q, MENG X S, et al. A dielectric barrier discharge plasma deicing device and method[P]. 2015-09-09 (in Chinese). 蔡晋生, 田永强, 孟宣市, 等. 一种介质阻挡放电等离子体除积冰装置及方法[P]. 2015-09-09.
[19] JAKOB VAN DEN B. De-icing using ns-DBD plasma actuators[D]. Delft: Delft University of Technology, 2016.
[20] LIU Y, KOLBAKIR C, HU H. A parametric study to explore ns-DBD plasma actuation for aircraft icing mitigation[C]//2018 Flow Control Conference. Reston, AIAA, 2018.
[21] ZHOU W W, LIU Y, HU H Y, et al. Utilization of thermal effect induced by AC-DBD plasma generation for aircraft icing mitigation[C]//2018 AIAA Aerospace Sciences Meeting. Reston: AIAA, 2018.
[22] MENG X S, HU H Y, LI C, et al. Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing[J]. Physics of Fluids, 2019, 31(3): 037103.
[23] WEI B, WU Y, LIANG H, et al. Flow control on a high-lift wing with microsecond pulsed surface dielectric barrier discharge actuator[J]. Aerospace Science and Technology, 2020, 96: 105584.
[24] FISH F E, BATTLE J M. Hydrodynamic design of the humpback whale flipper[J]. Journal of Morphology, 1995, 225(1): 51-60.
[25] MIKLOSOVIC D S, MURRAY M M, HOWLE L E, et al. Leading-edge tubercles delay stall on humpback whale (Megaptera novaeangliae) flippers[J]. Physics of Fluids, 2004, 16(5): L39-L42.
[26] WANG G F. Study on FlowSeparation control and application of bionic wavy edge airfoil[D]. Beijing: Chinese Academy of Sciences, 2014: 33-77 (in Chinese). 王国付. 仿鲸鱼鳍凹凸前缘翼型流动分离控制及应用研究[D]. 北京: 中国科学院研究生院, 2014: 33-77.
[27] WU Y, WEI B, LIANG H, et al. Novel plasma ice shape regulation and control device and method and anti-icing aircraft: CN110481792A[P]. 2019-11-22 (in Chinese). 吴云, 魏彪, 梁华, 等. 一种新型等离子体冰形调控装置, 方法及防结冰型飞行器: CN110481792A[P]. 2019-11-22.
[28] SHIN J, CHEN H, CEBECI T. A turbulence model for iced airfoils and its validation[C]//30th Aerospace Sciences Meeting and Exhibit. Reston: AIAA, 1992.
[29] LYU T. Aerodynamic characteristics analysis of icing aircraft wing[D]. Harbin: Harbin Engineering University, 2015: 38-52 (in Chinese). 吕涛. 结冰情况下机翼的气动特性研究[D]. 哈尔滨: 哈尔滨工程大学, 2015: 38-52.
[30] LI X K, LIU W, ZHANG T J, et al. Experimental and numerical analysis of the effect of vortex generator installation angle on flow separation control[J]. Energies, 2019, 12(23): 4583.
[31] CHEN W J, ZHANG D L. Numericalsimulation of ice accretion on airfoils[J]. Journal of Aerospace Power, 2005, 20(6): 1010-1017 (in Chinese). 陈维建, 张大林. 飞机机翼结冰过程的数值模拟[J]. 航空动力学报, 2005, 20(6): 1010-1017.
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