Study on the dynamic characteristics of MSL ballistic range test configuration

BI Lin; YUAN Xianxu; WU Bojiao; CHEN Hao; TANG Zhigong

doi:10.7638/kqdlxxb-2018.0239

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Study on the dynamic characteristics of MSL ballistic range test configuration

更新时间：2026-05-28

- Study on the dynamic characteristics of MSL ballistic range test configuration
- Vol. 37, Issue 5, Pages: 785-794(2019)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0239
  CLC： V211.3
- Published：2019
- 稿件说明：
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毕林, 袁先旭, 吴波佼, 陈浩, 唐志共. 弹道靶火星探测器试验模型动态特性研究[J]. 空气动力学学报, 2019, 37(5): 785-794.

BI Lin, YUAN Xianxu, WU Bojiao, et al. Study on the dynamic characteristics of MSL ballistic range test configuration[J]. 2019, 37(5): 785-794.
毕林, 袁先旭, 吴波佼, 陈浩, 唐志共. 弹道靶火星探测器试验模型动态特性研究[J]. 空气动力学学报, 2019, 37(5): 785-794. DOI： 10.7638/kqdlxxb-2018.0239.

BI Lin, YUAN Xianxu, WU Bojiao, et al. Study on the dynamic characteristics of MSL ballistic range test configuration[J]. 2019, 37(5): 785-794. DOI： 10.7638/kqdlxxb-2018.0239.

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

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

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

变化的原因是不同比热比

条件下流场的压缩性不同，与弹道靶试验结论一致。

Abstract

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

Keywords

references

WAY D W, POWELL R W, CHEN A, et al. Mars science laboratory: entry, descent, and landing system performance[C]//IEEE Aerospace Conference Proceedings, Big Sky, MT, USA, 2007. 03. 3-10, IEEE: 1-19.

EDQUIST K T, HOLLIS B R, DYAKONOV A A, et al. Mars science laboratory entry capsule aerothermodynamics and thermal protection system[C]//IEEE Aerospace Conference Proceedings, Big Sky, MT, USA, 2007, 03, 3-10, IEEE: 1-13.

ALKANDRY H, BOYD I D, REED E M, et al. Numerical study of hypersonic wind tunnel experiments for mars entry aeroshells: AIAA 2009-3918[R]. Reston: AIAA, 2009.

STELTZNER A, KIPP D, CHEN A, et al. Mars science laboratory entry, descent, and landing system[C]//Aerospace Conference, 2006 IEEE.

贾贺, 荣伟.火星探测器减速着陆技术分析[J].航天返回与遥感, 2010, 31(3):6-14.

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赵海洋.返回舱动态稳定性物理机理分析及被动/主动控制方法研究[D].长沙: 国防科学技术大学, 2007.

SCHOENENBERGER M, HATHAWAY W, YATES L, et al. Ballistic range testing of the mars exploration rover entry capsule[C]//43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005.

BROWN J, YATES L, BOGDANOFF D, et al. Free-flight testing in support of the mars science laboratory aerodynamics database[J]. Journal of Spacecraft and Rockets, 2006, 43(2):293-302.

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VIVIANI A, PEZZELLA G. Aerodynamic analysis of a capsule vehicle for a manned exploration mission to mars[C]//AIAA/dlr/dglr International Space Planes Hypersonic Systems Technologies Conference, 2011.

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