弹道靶火星探测器试验模型动态特性研究  

Study on the dynamic characteristics of MSL ballistic range test configuration

作　　者：毕林 袁先旭[1,2] 吴波佼[2] 陈浩 唐志共 BI Lin;YUAN Xianxu;WU Bojiao;CHEN Hao;TANG Zhigong(State Key Laboratory of Aerodynamics,Mianyang 621000,China;Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang 621000,China)

机构地区：[1]空气动力学国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《空气动力学学报》2019年第5期785-794,共10页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(11372341)

摘　　要：火星探测器一般为球冠倒锥构型的钝体飞行器;对于此类飞行器,其后体流动较为复杂,存在大范围的分离与再附、激波/旋涡干扰等;相应地,其动态特性也较为复杂,是设计关键问题之一。本文针对弹道靶火星探测器试验模型,采用近似比热比方法模拟火星大气环境,在验证所开发的数值方法与软件(in-house program FLY3D-Mars)正确性基础上,数值研究了其俯仰动态特性随比热比γ的变化规律。结果表明:在所考察范围内,试验外形均为动稳定,比热比γ越小,压缩性增强,动导数减小,动稳定性增强。分析认为导致动稳定性随γ变化的原因是不同比热比γ条件下流场的压缩性不同,与弹道靶试验结论一致。Mars probe usually is an obtuse vehicle with a spherical-crown/inverted-cone configuration. For this kind of vehicles,the aft-body flow is complex,such as large scale separation and reattachment,shock/vortex interaction. Consequently,the dynamic characteristics are also extremely complex and become one of the key problems during the design process. In this paper,the approximate specific heat ratio method is used to simulate the atmospheric environment of Mars for ballistic range Mars probe test model(MSL model). Based on the verification of the numerical method with in-house software FLY3D-Mars,the variation of pitching dynamic characteristics with specific heat ratio are numerically studied. The results show that the experimental configuration is dynamically stable in all the investigated ranges. As the specific heat ratio decreases,the compressibility becomes stronger,the dynamic derivative reduces and the dynamic stability can be improved accordingly. The reason for the change of dynamic stability with specific heat ratio is that the compressibility of the flow is different under the conditions with different specific heat ratios, which is consistent with that of ballistic range test.

关 键 词：火星探测 俯仰动态特性 近似比热比 压缩性 动导数 

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]