行星探测用柔性降落伞跨/超声速气动特性及耦合机理

doi:10.7527/S1000-6893.2024.30369

Abstract

Abstract:

Further missions of China’s planetary exploration projects to the Venus， the Jupiter and others have been initiated， and the key technical research is underway. However， these planets have significantly different atmospheric environments from those of the Earth and the Mars， with dense atmospheres and higher atmospheric pressures. Previous successful planetary explorations reveal that the aerodynamic deceleration process in such complex planetary atmospheric environments requires multi-stage parachutes and transonic/supersonic conditions for parachute opening and operation. Meanwhile， the nominal diameter of the first stage guide parachute is significantly smaller than that of the main parachute and the forebody diameter. With few related research reports， the fluid structure interaction mechanism and the aerodynamic characteristics between two-stage parachutes of different sizes and the forebody are still unclear. In this research， based on conical ribbon parachutes and disk-band-gap parachutes suitable for dense atmospheric planetary exploration missions， the fluid structure interaction mechanism of flexible parachutes in different planetary atmospheric environments is numerically studied using the immersion boundary method， and the aerodynamic characteristics with different freestream Mach numbers， canopy types， atmospheric components， and parameter to diameter ratios are investigated.Results show that in the atmospheric environment of the Titan， the conical ribbon canopy （with a diameter ratio of 0.3） steadily descends at transonic speeds， and the projected area of the canopy increases over time. The drag coefficient reaches its maximum at Mach number 1.5， while its fluctuation monotonically increases with the increase of the Mach number. In addition， at Mach number 0.95， the canopies exhibit extremely severe oscillation when the diameter ratios are 0 and 1. In contrast， in the atmospheric environment of the Jupiter， when the freestream Mach number is transonic， the change in the projected area of the conical ribbon canopy becomes smaller over time. The drag coefficient and its fluctuation will monotonically increase with the increase of the Mach number， and the lateral force coefficient and its fluctuation reach their maximum at Mach number 1.5. Finally， a comparison is made between the stable descent process of parachutes in the atmospheric environments of the Titan， the Venus， and the Jupiter， showing that the conical ribbon canopy in the Jupiter atmospheric environment has the best performance， a larger drag coefficient， and better stability.

Key words: deep space exploration, transonic/supersonic parachutes, aerodynamic characteristics, fluid-structure interaction mechanism, aerodynamic decelerating technology

CLC Number:

V411.3

He JIA, Wei JIANG, Wenlong BAO, Xin XU, Wei RONG, Li YU. Transonic/supersonic aerodynamic characteristics and fluid-structure interaction mechanism of flexible parachutes for planetary exploration[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(1): 630369.

Figures/Tables 33

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探测任务	年份	大气主要成分	降落伞类型	名义直径/m²	工作马赫数
Pioneer Venus （金星）	1978	二氧化碳	（1）无肋导向面伞（2）锥形带条伞	（1） 0.76 （2） 4.94	（1） 0.80 （2） 0.80
Galileo （木星）	1995	氢气氦气	（1）锥形带条伞（2）锥形带条伞	（1） 1.14 （2） 3.80	（1） 0.95 （2） 0.95
Huygens （土卫六）	2004	氮气	（1）盘缝带伞（2）盘缝带伞（3）盘缝带伞	（1） 2.59 （2） 8.31 （3） 3.00	（1） 1.47 （2） 1.36 （3） 0.15
MSL （火星）	2010	二氧化碳	盘缝带伞	21.5	1.75

参数	数值	参数	数值
名义面积/m²	0.8	名义直径/m	1.009
伞衣幅数量	12	伞衣幅顶角/（°）	27.64
伞衣幅高度/m	0.521	伞衣幅底边宽度/m	0.256
顶孔三角幅高度/m	0.116	顶孔带长度/m	0.208
顶孔三角幅宽度/m	0.057	水平带数量	11
水平带宽度/mm	25	缝隙宽度/mm	13
伞绳长度/m	1.600	连接带长度/m	8
结构透气量/%	21.3

伞型	模型	最小网格尺度/m	网格数量
锥形带条伞	锥形带条伞模型	0.01	7 984
	Galileo前体（直径比0.3）	0.01	18 952
	Galileo前体（直径比1.0）	0.01	31 416
	流场域模型	0.04	345×10⁴
盘缝带伞	盘缝带伞模型	0.012	3 408
	MSL前体（直径比0.3）	0.018	272
	MSL前体（直径比1.0）	0.030	640
	流场域模型	0.02	562×10⁴

大气环境	大气成分	来流马赫数	来流速度/ （m·s^-1）	来流压强/ Pa	来流密度/ （kg·m^-3）	来流温度/ K	等压比热容/（J·（kg·K）^-1）	等容比热容/（J·（kg·K）^-1）	动力黏度/ （Pa·s）
木星	氢气	0.95	941.1	1.6✕10⁵	0.228	193	14 550	10 390	6.58✕10^-6
木星	氢气	1.1	1 089.7	1.6✕10⁵	0.228	193	14 550	10 390	6.58✕10^-6
木星	氢气	1.5	1 485.9	1.6✕10⁵	0.228	193	14 550	10 390	6.58✕10^-6
木星	氢气	2	1 981.3	1.6✕10⁵	0.228	193	14 550	10 390	6.58✕10^-6
金星	二氧化碳	1.5	433.2	1.6✕10⁵	1.7	350	756	567	1.73✕10^-5
土卫六	氮气	0.95	245.1	6.25✕10⁴	1.31	160	1 039	742	1.07✕10^-5
土卫六	氮气	1.1	283.8	6.25✕10⁴	1.31	160	1 039	742	1.07✕10^-5
土卫六	氮气	1.5	387	6.25✕10⁴	1.31	160	1 039	742	1.07✕10^-5
土卫六	氮气	2	516	6.25✕10⁴	1.31	160	1 039	742	1.07✕10^-5

模型	阻力系数	误差/%
试验结果	0.53
数值模拟结果（0.015 m）	0.50	5.7
数值模拟结果（0.02 m）	0.57	7.5
数值模拟结果（0.03 m）	0.59	11.3
数值模拟结果（0.04 m）	0.60	13.2

Transonic/supersonic aerodynamic characteristics and fluid-structure interaction mechanism of flexible parachutes for planetary exploration

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