等离子体合成射流激励器阵列破除翼前缘三维冰特性  

Characteristics of 3D ice breaking on leading edge of wing by plasma synthetic jet actuator array

作　　者：程盼 景向嵘 罗振兵[1] 高天翔 周岩[1] 邓雄[1] 孙乾 CHENG Pan;JING Xiangrong;LUO Zhenbing;GAO Tianxiang;ZHOU Yan;DENG Xiong;SUN Qian(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha410073,China;Key Laboratory of Icing and Anti/De-icing,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]中国空气动力研究与发展中心结冰与防除冰重点实验室,绵阳621000

出　　处：《航空学报》2024年第12期43-53,共11页Acta Aeronautica et Astronautica Sinica

基　　金：中国空气动力研究与发展中心结冰与防除冰重点实验室基金(IADL20220410);湖南省自然科学基金(2021JJ40672);国家自然科学基金(12002377,12072352);国家科技重大专项(J2019-Ⅲ-0010-0054);沈阳市飞机结冰与防除冰重点实验室基金(YL2022XFX03)。

摘　　要：无人机结冰将严重影响其安全性,机翼前缘更容易结冰及积冰,对无人机气动性能影响更为严重,而机翼前缘结冰形状具有三维特性,亟须发展有效破除机翼前缘三维冰的低能耗、快响应除冰技术。分别根据NACA0012、NACA0018及NACA00243种翼型前缘曲率制作了3种不同弧度的冰型,基于等离子体合成射流激励器响应快、能耗低、射流强度高等优点,开展了单个及阵列布置激励器破除三维形态冰特性研究,分析了45°和90°两种不同方向出口对破冰特性的影响,阐明了等离子体合成射流激励器的破除冰机理及规律。结果表明:放电总能量为16.66 J时,在单个激励器作用下,对于翼前缘类似NACA0012的曲率半径较小的冰,射流冲击应力易在前缘驻点处集中,在翼前缘驻点线处能产生长达20 cm的贯穿裂纹,从而实现有效破除冰;对于曲率半径较大的冰,破冰半径约5 cm。保持放电总能量16.66 J不变,激励器采用沿驻点线的“一字型”阵列布置时对3种弧度的冰都能产生贯穿裂纹实现破除冰,表明激励器阵列能有效拓展破除冰面积,具备低能耗、大面积破除冰能力。研究成果可为无人机低能耗、大面积破除冰提供理论及实践参考。Icing on Unmanned Aerial Vehicles will seriously affect their aerodynamic performance,particularly that on the wing leading edge which is more likely to occur and accumulate.In addition,the shape of icing on the wing leading edge is three-dimensional,making it urgent to develop low energy consumption and fast-response anti-icing technol-ogy to effectively remove the ice.According to the leading edge curvature of NACA0012,NACA0018 and NACA0024 airfoils,three ice shapes with different radians were fabricated.The characteristics of breaking three-dimensional ice shapes by single and array actuators were studied based on the advantages of fast response,low energy consumption and high jet strength of plasma synthetic jet actuators.The effect of outlets at 45°and 90°on the ice-breaking charac-teristics was analyzed,and the ice-breaking mechanism and rule of plasma synthetic jet actuators were clarified.The results show that,when the total discharge energy reaches 16.66 J,under the effect of a single actuator,for ice simi-lar to NACA0012 with a small curvature radius on the wing leading edge,the jet impact stress is prone to concentration at the front vertex,and can produce through cracks up to 20 cm at the wing leading edge stagnation point line to real-ize effective ice breaking,while for ice with larger curvature radiuses,the ice breaking radius is about 5 cm;when the total discharge energy is kept constant at 16.66 J,the"single line"array arrangement near the stagnation point line of the actuator can produce through cracks for ice of three arcs to achieve ice breaking,indicating that the exciter array can effectively expand the ice breaking area with the ability to break ice in a large area with low energy consumption.The research results can provide theoretical and practical reference for UAVs with low energy consumption and large area icebreaking capability.

关 键 词：无人机除冰 等离子体合成射流激励器 激励器阵列 破除冰特性 三维冰 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]