运载火箭跨音速气动阻尼数值分析  

Numerical Analysis on Transonic Aerodynamic Damping of Carrier Rockets

作　　者：宣传伟 王吉飞 王亚博 李鑫 刘锦凡 孙阳 XUAN Chuanwei;WANG Jifei;WANG Yabo;LI Xin;LIU Jinfan;SUN Yang(Institute of Aerospace System Engineering,Shanghai 201109,China)

机构地区：[1]上海宇航系统工程研究所,上海201109

出　　处：《上海航天（中英文）》2024年第4期44-50,共7页Aerospace Shanghai（Chinese&English）

摘　　要：运载火箭跨音速飞行时气动阻尼的评估(即是否会出现负阻尼现象)是型号研制流程中至关重要的一环。传统气动阻尼风洞试验耗时耗力,严重制约新型火箭的研制,亟须一种快速高效的气动阻尼评估算法。基于计算流体动力学(CFD)/计算结构动力学(CSD)耦合迭代对某型火箭模型跨音速气动阻尼特性进行分析。其中,非定常气动力通过求解纳维-斯托克斯(N-S)方程获得,结构动响应通过模态叠加法求解,流固界面间数据的传递通过逆距离插值技术实现。在寻找最近邻节点时使用高效kD-Tree数据结构大幅提高插值效率。数值仿真结果与风洞试验结果趋势一致,说明了本文数值算法的有效性。本文工作可用于型号研制方案阶段的快速评估,相比于常规气动阻尼风洞试验,能够显著加快型号研制流程。最后,针对仿真值与试验值之间存在的偏差,本文从计算模型处理、仿真算法和动力学特性3个角度对偏差存在的原因进行了分析,为后续提高仿真精度指明了方向。The transonic aerodynamic damping characteristics of a rocket model is analyzed by the coupled iterations of computational fluid dynamics(CFD)/computational structural dynamics(CSD).The unsteady aerodynamic forces on a rocket model are obtained by solving the Navier-Stokes(N-S)equations,the structural dynamic responses are achieved by the modal superposition method,and the data transfer between the solid and fluid domains are realized by the inversed distance interpolation technique.The efficient kD-tree data structure is used to find the nearest neighbors for fluid wall nodes,which improves the interpolation efficiency greatly.The numerical simulation results have a consistent trend with the wind tunnel test results,which illustrates the effectiveness of the numerical algorithm in this paper.The work in this paper can be used for rapid evaluation in the model development plan stage.Compared with conventional aerodynamic damping wind tunnel testing,it can significantly speed up the model development process.Finally,regarding the deviation between the simulation value and the experimental value,this paper analyzes the reasons for the deviation from three perspectives:computational model processing,simulation algorithm and dynamic characteristics,pointing out the direction for subsequent improvement of simulation accuracy.

关 键 词：运载火箭 跨音速 数值仿真 气动阻尼 阻尼辨识 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]