翼伞后缘偏转过程的流固耦合动力学特性  

Fluid-structure interaction dynamic characteristics of parafoil under trailing-edge deflection

作　　者：高兴龙[1] 陈钦[1] 张青斌[2] 李志辉[1] GAO Xinglong;CHEN Qin;ZHANG Qingbin;LI Zhihui(China Aerodynamics Research and Development Center,Mianyang 621000,China;College of Aeronautics and Astronautics,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]中国空气动力研究与发展中心,绵阳621000 [2]国防科技大学空天科学学院,长沙410073

出　　处：《空气动力学学报》2023年第5期68-75,I0002,共9页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(11902331,11772353)。

摘　　要：深入研究翼伞后缘偏转过程的气动与结构耦合动力学问题是解决大型翼伞精确空投系统机动转弯和雀降等操纵动作设计分析的重点内容。首先基于ALE算法和罚函数耦合方法对翼伞后缘偏转过程进行流固耦合动力学建模,之后基于结构化的ALE求解方法和瞬态非线性求解器对翼伞三维模型的单个气室后缘偏转进行仿真验证,预测了后缘偏转运动引起的周围流场流动分离现象。分别针对翼伞后缘单侧下偏和双侧下偏过程的流固耦合行为进行仿真分析,获得全时域内翼伞结构场和周围流场特性动态演化结果,以及翼伞气动性能参数时间历程曲线,发现了后缘下偏过程的操纵延迟现象。最后通过风洞试验对仿真结果进行验证,证明了方法的有效性,为大型冲压翼伞的设计和应用提供理论和技术支撑。A deep understanding of the fluid-structure interaction(FSI)problem of the parafoil under trailing-edge deflection is crucial for the maneuvering and landing design of large parafoils’precision airdrop system.Based on the ALE(arbitrary Lagrangian Eulerian)algorithm and the penalty coupling method,the FSI modeling of parafoils under trailing-edge deflection is firstly proposed,then the structured ALE(S-ALE)method and the transient nonlinear dynamics solver are used to simulate a single cell 3D model of the parafoil under trailing-edge deflection,and the flow separation phenomenon due to the trailing-edge deflection is captured.The FSI characteristics of the parafoil under both single and double deflections are simulated and analyzed.The structural and surrounding flow fields evolution in the time domain are obtained,as well as the time history profiles of various parafoil aerodynamics.It is found that there is a delay in the manipulation under trailing-edge deflection.Finally,the simulation results are verified by a wind tunnel test,which suggests the efficiency of our method.The present results provide good support for the design and application of large parafoils.

关 键 词：翼伞 流固耦合 后缘偏转 ALE方法 流动分离 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V445.23V244.216