火星探测器再入RCS喷流干扰效应数值模拟研究  

Numerical simulation of RCS jet interference effect in the re-entry process of a Mars probe

作　　者：孙瑞斌 黄育群[1] 马继魁[1] 刘耀峰[1] 柳煜玮 倪招勇[1] SUN Ruibin;HUANG Yuqun;MA Jikui;LIU Yaofeng;LIU Yuwei;NI Zhaoyong(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《航天器环境工程》2023年第4期331-337,共7页Spacecraft Environment Engineering

摘　　要：针对火星大气环境下的反作用力控制系统(RCS)喷流干扰问题,采用自研CFD软件数值模拟“火星科学实验室”(MSL)外形在火星大气环境中的喷流干扰效应;并与文献中的高超声速喷流干扰风洞试验和计算结果进行对比验证;继而完成了火星大气环境高超声速(M_(∞)=5~10)条件下的偏航方向喷流干扰效应数值模拟,获得了不同攻角(α=0°~-30°)、不同马赫数条件下的喷流干扰气动规律:负攻角增大将导致喷流干扰效应增强以及附加偏航力矩增加;来流马赫数对附加干扰力矩的影响较小。研究结果可为火星探测器喷流控制设计提供参考。Aiming at the problem of reaction control system(RCS) jet interference in Mars atmosphere,a self-developed CFD software was used to numerically simulate the jet interference effect of Mars Science Laboratory(MSL) shape in Mars atmosphere,and the results were compared and verified with those from calculation and from hypersonic jet interference wind tunnel test in the reference.Then,the numerical simulation of the yaw direction jet interference effect under hypersonic velocity(M_∞=5-10) in Mars atmosphere was completed.The aerodynamic laws of jet interference under different attack angles(from 0° to -30°) and different Mach numbers were obtained:a.The increase of negative attack angle leads to the increases both in jet interference effect and additional yaw moment;b.The incoming Mach number has little effect on additional moment.Those research may provide some reference for the design of Mars probe jet control.

关 键 词：火星大气 高超声速流 火星探测器 喷流干扰 数值模拟 CFD软件 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计] V529.1V411.3