火箭整流罩半罩再入过程连续流区气动特性数值研究  

Numerical study on the aerodynamics of a rocket fairing half in the continuum regime of the reentry process

作　　者：冯瑞 刘宇 张章 何青松 吴卓[1,2] 滕海山 贾贺[1,2] FENG Rui;LIU Yu;ZHANG Zhang;HE Qingsong;WU Zhuo;TENG Haishan;JIA He(Beijing Institute of Space Mechanics&Electricity,Beijing 100094,China;Laboratory of Aerospace Entry,Descent and Landing Technology,China Aerospace Science and Technology Corporation,Beijing 100094,China)

机构地区：[1]北京空间机电研究所,北京100094 [2]中国航天科技集团有限公司航天进入、减速与着陆技术实验室,北京100094

出　　处：《清华大学学报（自然科学版）》2023年第3期414-422,共9页Journal of Tsinghua University(Science and Technology)

基　　金：国家重大科技专项。

摘　　要：针对整流罩半罩与运载火箭分离后再入落点预测难的问题,结合再入实测飞行弹道数据,采用计算流体力学(computational fluid dynamics, CFD)方法对某型常用火箭整流罩半罩再入过程在连续流区的气动特性进行了全面研究,得到了再入速度在Ma为0.20~5.95和攻角为0°~360°范围内的气动参数。计算结果表明:半罩再入过程存在2个配平攻角,超音速和亚跨音速流域的第1个配平攻角分别约为95°和88°,第2个配平攻角均约为255°;在第1个和第2个配平攻角处,半罩在0°滚转角位置分别表现出在滚转方向上静稳定与非静稳定特性;沿半罩轴线方向调节其质心位置,可有效改变其配平飞行攻角,从而显著改变配平飞行升阻比。研究结果对运载火箭半罩再入落区可靠预测或一定范围内的落区调节控制具有重要价值。[Objective] Recently, a trend has been developed toward the high-density launches of launch rockets, and unprecedented attention has been paid to the impact zone safety of rocket’s separated fairings. Great pressure on controlling the environmental safety of the rocket’s fairing half results from the low accuracy and large uncertainty in reentry trajectory calculation using the traditional mass point ballistic model. The main reason for the difficulty in reliably calculating the reentry ballistics of the fairing half is the lack of comprehensive studies on the half fairing’s aerodynamic characteristics under various reentry flight conditions. This study aims to deal with the problem of reliable prediction of the reentry impact point of fairing half after separation from the launch vehicle.[Methods] By using the computational fluid dynamics(CFD) approach, a comprehensive study is conducted here on the aerodynamics of the fairing half of a common rocket in the continuum regime of its reentry process. The incoming flow parameters for multiple computational conditions are extracted from the measured ballistic data of a certain flight mission. The calculation of various conditions is set and controlled by a parametric automated script. To obtain the relevant aerodynamic coefficients, the steady-state numerical solution for three-dimensional Reynolds-averaged Navier-Stokes(RANS) equations is obtained using the finite volume method. The Roe scheme and the implicite lower-upper symmetric Gauss-Seidel(LU-SGS) solution algorithms are used to obtain the discretization solution of the flow control equations. A numerical model uses an unstructured mesh structure, with a total mesh number approximating 15 million, and generates enough prismatic layers on the surface. The turbulence model is a two-equation realizable k-ε model. [Results] Aerodynamic coefficients of the fairing half were obtained under various flight conditions, where the Mach number varied from 0.20 to 5.95, while the angle of attack(AOA) varied from 0°

关 键 词：火箭整流罩半罩 再入连续流区 气动特性 计算流体力学 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]