[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 2: 129 - 137

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.001

Study on Force-thermal Impacts of Inclined Hot Launch of Mars Ascent Vehicle

  • XIONG Zongjian ,
  • ZHAO Yuchen ,
  • JIANG Yi
Expand
  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2024-11-18

  Online published: 2025-05-15

Fold

Abstract

The launch of the Mars ascent vehicle(MAV) is the first step for ascent from the Martian surface to orbit around Mars, a critical step in the Mars sample return mission. In the MAV's inclined hot launch process, the force-thermal impacts are significant and gas flow structure is complex, so when designing its launch system, it is necessary to consider the complex force-thermal effect in launching process. This study employs computational fluid dynamics to conduct a numerical simulation of the force-thermal impacts of the MAV's inclined thermal launch on the Martian surface, with comparisons to similar launch conditions on earth. The findings reveal that during the inclined hot launch from Mars, the MAV's maximum surface temperature reaches 2 868 K, while the launch platform attains a peak temperature of 2 908 K. Furthermore, during ejection, the platform's pitch-up moment progressively increases, the launch apparatus may topple under Mars' low-gravity conditions. Notable differences are observed between inclined hot launch processes on Mars and Earth; the MAV launch on Mars exhibits greater stability yet endures more severe force-thermal impacts on both the platform and the MAV.

Key words： Mars sample return; inclined hot launch; numerical simulation; force-thermal impacts

Cite this article

XIONG Zongjian , ZHAO Yuchen , JIANG Yi . Study on Force-thermal Impacts of Inclined Hot Launch of Mars Ascent Vehicle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(2) : 129 -137 . DOI: 10.15892/j.cnki.djzdxb.2025.02.001

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
孟林智, 董捷, 许映乔, 等. 无人火星取样返回任务关键环节分析[J]. 深空探测学报, 2016, 3(2): 114-120.

MENG L Z, DONG J, XU Y Q, et al. Analysis of key technologies for unmanned Mars sample return mission[J]. Journal of Deep Space Exploration, 2016, 3(2): 114-120.

DOI

[2]
张扬眉. 国外火星探测发展态势分析[J]. 国际太空, 2020(8): 29-36.

ZHANG Y M. Analysis of the development trend of overseas Mars exploration[J]. Space International, 2020(8): 29-36.

[3]
张胜, 唐晓峰, 刘可平, 等. 火星上升器发射技术综述[J]. 空天防御, 2023, 6(3): 66-76.

ZHANG S, TANG X F, LIU K P, et al. Review on research status of Mars ascent vehicle's launching technology[J]. Air & Space Defense, 2023, 6(3): 66-76.

[4]
MUIRHEAD B K, NICHOLAS A K, UMLAND J, et al. Mars sample return campaign concept status[J]. Acta Astronautica, 2020, 176: 131-138.

[5]
顾苗. 火星表面环境模拟技术[J]. 装备环境工程, 2021, 18(9): 35-42.

GU M. Mars environment simulation technology[J]. Equipment Environmental Engineering, 2021, 18(9): 35-42.

[6]
BOUSLOG S A, BERTIN J, WINGERT II W B. Flowfield produced by rocket exhaust impingement of a multitube launcher[J]. Journal of Spacecraft and Rockets, 2012, 21(4): 323-329.

[7]
姜毅, 郝继光, 傅德彬. 导弹发射过程三维非定常数值模拟[J]. 兵工学报, 2008, 29(8): 911-915.

JIANG Y, HAO J G, FU D B. 3D unsteady numerical simulation of missile launching[J]. Acta Armamentarii, 2008, 29(8): 911-915.

[8]
任克亮, 熊言义. 基于热发射技术的垂直发射装置燃气排导系统分析[J]. 弹箭与制导学报, 2018, 38(5): 5-8.

REN K L, XIONG Y Y. Analysis of the gas exhaust system of vertical launcher based on heat emission technology[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018, 38(5): 5-8.

[9]
NAVE L H, COFFEY G A. Sea level side loads in high-area-ratio rocket engines:AIAA 73-1284[R]. Reston: AIAA, 1973.

[10]
RODRIGUES N S, TYRRELL O K, EBERHART C, et al. Flow visualization for plume surface interaction at Martian-relevant lander environments: AIAA 2024-4914[R]. Reston: AIAA, 2024.

[11]
SUBRAMANIAN S, CRAIG B, WHITE C, et al. Underexpanded jet impingement in near vacuum environment[J]. Physics of Fluids, 2024, 36: 107104.

[12]
林晓辉, 秦曈, 李宗儒, 等. 类火星环境中火箭起降过程喷流影响研究[J]. 宇航总体技术, 2023, 7(6): 12-23.

LIN X H, QIN T, LI Z R, et al. Investigations on the impact of the jet flow during rocket take-off and landing in the Martian-like atmosphere[J]. Astronautical Systems Engineering Technology, 2023, 7 (6):12-23.

[13]
叶青, 饶炜, 刘锋, 等. 火星着陆发动机羽流与火壤的相互作用[J]. 航空学报, 2022, 43(3): 39-46.

YE Q, RAO W, LIU F, et al. Interaction between engine plume and Martian soil during Mars landing[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(3): 39-46.

[14]
时蓬, 范全林, 汤惟玮. 关于2030年前火星采样返回科学任务的展望[J]. 空间科学学报, 2020, 40(3): 301-304.

SHI P, FAN Q L, TANG W W. Prospects for the Mars sample return scientific mission before 2030[J]. Chinese Journal of Space Science, 2020, 40(3): 301-304.

[15]
IANSON E, GRAMLING J, MEYER M. Mars sample return[R]. Washington, D.C.: NASA, 2021.

[16]
MAHAFFY P R, WEBSTER C R, ATREYA S K, et al. Abundance and isotopic composition of gases in the Martian atmosphere from the curiosity rover[J]. Science, 2013, 341(6143): 263-266.

DOI PMID

[17]
WILKE C R. A viscosity equation for gas mixtures[J]. Journal of Chemical Physics, 1950, 18(4): 517-519.

[18]
LINDSAY A L, BROMLY L A. Thermal conductivity of gas mixtures[J]. Industrial and Engineering Chemistry, 1950, 8(42): 1508-1511.

[19]
ALVI F S, IYER K G. Mean and unsteady flowfield properties of supersonic impinging jets with lift plates: AIAA 99-1829[R]. Reston: AIAA, 1999.

[20]
梁晓扬, 苏逸飞, 乐贵高. 导弹从发射箱热发射过程的数值分析[J]. 航空动力学报, 2022, 37(8): 1643-1653.

LIANG X Y, SU Y F, LE G G. Numerical analysis of hot launch of missile from a launch canister[J]. Chinese Journal of Space Science, 2022, 37(8): 1643-1653.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]