摘要
进入段气动热环境的有效预测对火星探测器气动热防护设计具有重要意义。本文基于自研的有限体积计算流体力学(CFD)求解器PHAROS,引入两温度和8组分火星大气化学反应动力学模型,成功实现了对火星进入热化学非平衡流场的数值模拟。PHAROS预测的激波脱体距离和表面热流与HET风洞火星科学实验室(MSL)模型试验数据一致,证实了该求解器的可靠性。计算结果表明,HYPULSE风洞试验模型高温激波层和肩部下游膨胀区内存在显著的热力学非平衡。同时,本文还利用PHAROS对MSL的真实有迎角飞行工况开展三维模拟,该条件下MSL辐射平衡壁面高温分布在球头和下肩部,约1300K,表面高低温差近300K;MSL前体表面具有双环式压强分布,壁面对流传热最大值出现在球头附近,为0.53MW/m^(2),下肩部同样具有较高的气动加热水平。算例测试和应用研究表明,PHAROS求解器可对火星进入段气动热环境实现可靠预测,为未来火星探测器气动加热规律研究和气动热防护设计提供技术支持。
The effective prediction of aerothermal environment at entry is of important significance to the thermal protection system design of Mars rover.This study successfully simulates the Mars entry thermo-chemical nonequilibrium flows using the in-house finite volume CFD solver Parallel Hypersonic Aerothermodynamics and Radiation Optimized Solver(PHAROS)combined with two-temperature and 8-species chemical reaction kinetic models.Both the detached distance of shock wave and wall heat flux of the Mars Science Laboratory(MSL)model calculated by PHAROS are very consistent with those measured in the HET wind tunnel tests,which verifies the PHAROS's fidelity.The results show the visible thermodynamic nonequilibrium phenomena exists in the shock layer and the separation region downstream the shoulder of the test model in the HYPULSE wind tunnel.The present study also employs PHAROS to solve the three-dimensional flow field of a MSL real flight case with an angle of attack of 15.7°,under the entry condition of which,the high radiation-adiabatic wall temperatures of about 1500K distribute around the MSL nose and lower shoulder respectively,and the maximum wall temperature variance reaches nearly 300K;a double-ring pressure distribution pattern appears on the MSL forebody surface;the heat flux peak occurs near the MSL forebody center up to 0.53MW/m^(2),while there is also a high level of aerodynamic heating at the vehicle lower shoulder.The present test and application cases suggest that the PHAROS solver is reliable to predict the aerothermal environment for Mars entry,which can contribute to the study of aerodynamic heating and design of thermal protection system for the future Mars probe.
作者
杨星链
王京盈
郝佳傲
孙柯
Yang Xinglian;Wang Jingying;Hao Jia'ao;Sun Ke(Shandong University,Jinan 250061,China;Hong Kong Polytechnic University,Hong Kong 999077,China)
出处
《航空科学技术》
2022年第7期86-94,共9页
Aeronautical Science & Technology
基金
国家自然科学基金(12002193)
山东省自然科学基金(ZR2019QA018)。
