后缘舵机身干扰区气动加热机理及局部外形优化设计  

Study on Heating Mechanism and Geometry Optimization of Trailing-edge-rudder/Body Slot Flow Interference Zone

作　　者：艾邦成[1,2] 陈智 江娟[1,2] 聂春生 易仕和[4] Ai Bang-cheng;Chen Zhi;Jiang Juan;Nie Chun-sheng;Yi Shi-he(China Academy of Aerospace Aerodynamics,Beijing,100074;Laboratory of Aero-thermal Protection Technology for Aerospace Vehicles,Beijing,100074;Science and Technology on Space Physics Laboratory,Beijing,100076;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha,410073)

机构地区：[1]中国航天空气动力技术研究院,北京100074 [2]航天飞行器气动热防护实验室,北京100074 [3]空间物理重点实验室,北京100076 [4]国防科技大学空天科学学院,长沙410073

出　　处：《导弹与航天运载技术》2022年第4期98-103,共6页Missiles and Space Vehicles

基　　金：国家重点研发计划项目(2019YFB1704202);国家自然科学基金(11402254)。

摘　　要：后缘舵在机翼的遮挡下其热流峰值明显低于全动舵,但因其与机身、机翼均会发生干扰,其局部流动结构和热环境特性更为复杂。基于数值模拟方法及风洞试验开展了后缘舵/机身缝隙干扰区的气动加热机理研究,发现后缘舵在机身上的投影线处形成一条高热流条带,该热流条带上的热流干扰因子远大于压力干扰因子。数值模拟结果及风洞试验的纳米示踪的平面激光散射技术均表明产生这一现象的原因是气流在翼面迎背风压差的作用下穿过缝隙对机身与舵之间的漩涡产生抽吸,高温气体向机体下方运动在机身上再附形成高热流带。基于此分析,提出通过底面局部倒圆角、减小漩涡再附角度进而降低机身干扰热流峰值的局部外形优化方法。3个典型工况的数值计算结果表明,优化后的模型较原始模型峰值热流降热幅度达到了27%~31%,降热效果显著。The peak heating rate of the trailing edge rudder is significantly lower than that of the all-movable rudder because of the shelter of the wing.However,due to its interference with the fuselage and wing,the local flow structure and aero dynamic heating characteristics are more complex.The aerodynamic heating mechanism of the trailing edge rudder/fuselage gap interference zone is studied based on the numerical simulation method and wind tunnel experiment.It is found that a high heat flux strip is formed at the projection line of the trailing edge rudder on the fuselage,and the heating augmentation factor on the heat flow band is much larger than the pressure augmentation factor.The numerical simulation results and NPLS(Nano-Traced Planar Laser Scattering Technique)results of wind tunnel test show that the reason for this is that the pressure difference between the windward and leeward surface of the rudder causes the vortex is pulled toward the gap,and the distance between the high temperature air and the wall surface is reduced and a high heat flux strip is formed.Based on this analysis,a geometry optimization method is proposed to reduce the peak heating rate of high heat flux strip by reducing the reattachment angle of vortex.The numerical calculation of three typical conditions shows that the peak heating rate of the optimized model is 27%-31%lower than that of the original model,and the heating reduction effect is remarkable.

关 键 词：缝隙流动 气动加热 外形优化 

分 类 号：O355[理学—流体力学]