吸气式高超声速飞行器通气模型测力试验技术研究  

Research on Experimental Technique of Force Test with Ducted Models for Air-Breathing Hypersonic Vehicles

作　　者：王泽江[1] 宋文萍[1] 杨波[2] 曾学军[2] 孙鹏[2] 唐小伟[2] WANG Ze-jiang;SONG Wen-ping;YANG Bo;ZENG Xue-jun;SUN Peng;TANG Xiao-wei(School of Aeronautics,Northwestern Polytechnical University,Xi＇an 710072,China;China Aerodynamic Research and Development Center,Mianyang 621000,China)

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《推进技术》2018年第10期2394-2400,共7页Journal of Propulsion Technology

摘　　要：由于内阻测量方法限制,来流Ma_∞>4时常规通气模型测力试验精度无法满足吸气式高超声速飞行器设计和性能评估需求。为解决上述问题,确保试验精度满足飞行器研究需要,探索了将天平测量内阻技术引入常规通气模型测力试验的可行性。从改进试验方法角度提出了一种回避内阻测量难题的新型试验方法:采用"尾支+六分量天平"直接测量通气模型的气动特性(机体控制体产生的气动力载荷),并开展了试验验证。结果表明:由于减少了内阻测量环节,新型测力试验技术的精度高,Ma_∞=6时的阻力系数误差小于2%,远低于常规通气模型测力试验误差,具有精度高、模型相对简单、技术复杂程度较低、推广应用可能性大的优势。Due to the limitation of the method of internal drag measurement,the accuracy of traditional aerodynamic experiments of force test with ducted models（TFTDM）is unable to meet the demands of airframepropulsion integrated design and aerodynamic performance estimation for air-breathing hypersonic vehicles at Ma∞4.0. To solve this problem and ensure the aerodynamic accuracy experiments meet the demands of hypersonic vehicles development,the feasibility of introducing the internal drag measurement with the balance into TFTDM is explored firstly. After that,a new technique of force direct-test with ducted models（FDTDM）is proposed from improving the experimental method of TFTDM,to avoid the problem of internal drag measurement,which principle is the balance measurement of aerodynamic forces acting on the external component（airframe control volume）of ducted models with sting-supported model. A verification test is conducted and the accuracy of the technique is estimated. The results indicate that,due to cutting down the testing link of internal drag measurement,the accuracy of FDTDM is very high with the errors of drag coefficients less than 2% at Ma∞=6 and far below that of TFTDM. FDTDM has many advantages,such as high accuracy,simpler model structure,low technical complexity,large possibility of spread and application etc..

关 键 词：高超声速 风洞试验技术 测力试验 通气模型 天平 气动力 内阻 

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]