基于融合代理策略的超声速降落伞气动优化设计

doi:10.7527/S1000-6893.2024.30471

Abstract

Abstract:

Supersonic parachutes， as crucial aerodynamic deceleration systems providing drag and stability， directly impact the success of lander missions. The structural parameters of parachutes that meet different aerodynamic performance requirements are often contradictory. To address the issues of structural parameter conflicts in the shape design of Mars parachutes， as well as the errors of lengthy design cycles and high calculation， this study proposes a fusion surrogate optimization strategy for the two-body model of the canopy-capsule system. The fusion surrogate model integrates the advantages of interpolation-based and regression-based surrogate models， and achieves higher prediction accuracy of aerodynamic coefficients under the same sample conditions. By employing the fusion surrogate model to replace the time-consuming Computational Fluid Dynamics （CFD） calculation process， the design cycle can be shortened， and design efficiency can be improved. The two-body model of the capsule- DGB parachute is optimized using a multi-objective genetic algorithm. The results show that the fusion surrogate optimization strategy can balance the drag and stability performance of the canopy， and enhance the overall deceleration capability of the disk-gap-band parachute under structural parameters and aerodynamic constraints， demonstrating good practicality and feasibility. The research findings can provide theoretical reference and technical reserves for the design and development of a new generation of supersonic parachutes for future Mars exploration missions.

Key words: fusion strategy, Mars parachute, optimization design, surrogate model, supersonic

CLC Number:

V476.4

Lulu JIANG, Xin PAN, Wei JIANG, Rui FENG, Gang CHEN. Optimization shape design of capsule-supersonic parachute system based on fusion surrogate strategy[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(1): 630471.

Figures/Tables 22

Table 1

Structural parameters of initial model B

X/d	d/D	H_B	H_G	H_D	S_B/S_D	$λ g$
2.5	0.311	2.383 7	0.827 4	4.457	0.447	12.095%

Table 1

Fig.1

Table 2

Fig.2

Table 3

Parachute canopy structural parameters and aerodynamic coefficients changes with different band widths HB

模型	H_B	H_G	H_D	S₀	$λ g$ /%	S_B/S_D	$C ¯ D$	$σ (C Y)$
B1	3.902 2	0.827 4	4.456 6	404.055	10.213	0.670 4	0.382 4	0.081 83
B	2.601 5	0.827 4	4.456 6	341.178	12.095	0.446 9	0.467 2	0.054 75
B2	1.300 8	0.827 4	4.456 6	278.302	14.828	0.223 5	0.246 2	0.023 86

Table 3

Table 4

Parachute canopy structural parameters and aerodynamic coefficients changes with different disk depths HD

模型	H_B	H_G	H_D	S₀	$λ g$ /%	S_B/S_D	$C ¯ D$	$σ (C Y)$
D1	2.601 5	0.827 4	6.684 9	448.891	9.193	0.298 0	0.160 5	0.018 47
B	2.601 5	0.827 4	4.456 6	341.178	12.095	0.446 9	0.467 2	0.054 75
D2	2.601 5	0.827 4	2.228 3	233.466	17.675	0.893 9	0.656 2	0.085 51

Table 4

Table 5

Parachute canopy structural parameters and aerodynamic coefficients changes with different geometry porosities λg

模型	H_B	H_G	H_D	S₀	$λ g$ /%	S_B/S_D	$C ¯ D$	$σ (C Y)$
K1	2.601 5	0.600 0	4.456 6	341.178 4	8.771	0.447 0	0.433 4	0.052 9
K2	2.601 5	0.750 0	4.456 6	341.178 4	10.964	0.447 0	0.443 2	0.029 9
B	2.601 5	0.827 4	4.456 6	341.178 4	12.095	0.447 0	0.467 2	0.054 8
K3	2.601 5	0.950 0	4.456 6	341.178 4	13.887	0.447 0	0.420 5	0.038 8
K4	2.601 5	1.100 0	4.456 6	341.178 4	16.080	0.447 0	0.407 5	0.050 8
K5	2.601 5	1.200 0	4.456 6	341.178 4	17.542	0.447 0	0.432 0	0.050 4
K6	2.601 5	1.300 0	4.456 6	341.178 4	19.004	0.447 0	0.431 3	0.032 3
K7	2.601 5	1.500 0	4.456 6	341.178 4	21.927	0.447 0	0.445 9	0.063 1

Table 5

Table 6

Parachute canopy structural parameters and aerodynamic coefficients changes with different band-disk ratios SB/SD

模型	H_B	H_G	H_D	S₀	$λ g$ /%	S_B/S_D	$C ¯ D$	$σ (C Y)$
BD1	1.352 8	0.827 4	5.708 9	341.178 4	12.095	0.181 4	0.454 9	0.057 7
BD2	1.717 0	0.827 4	5.341 2	341.178 4	12.095	0.246 1	0.444 7	0.033 0
BD3	2.081 2	0.827 4	4.977 0	341.178 4	12.095	0.320 2	0.422 8	0.055 3
B	2.601 5	0.827 4	4.456 6	341.178 4	12.095	0.446 9	0.467 2	0.054 8
BD4	2.965 7	0.827 4	4.092 5	341.178 4	12.095	0.554 9	0.409 8	0.055 8
BD5	3.329 9	0.827 4	3.728 3	341.178 4	12.095	0.683 9	0.469 5	0.058 5
BD6	3.694 2	0.827 4	3.364 1	341.178 4	12.095	0.840 8	0.422 9	0.046 4
BD7	3.902 3	0.827 4	3.164 2	341.178 4	12.095	0.944 3	0.439 8	0.069 2

Table 6

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Table 7

Structural parameters and aerodynamic performances of different optimal models

模型	H_B	H_G	H_D	S₀	$λ g$ /%	S_B/S_D	$C ¯ D$	A（C_D ）	$σ (C Y)$
Opt₁	2.315 3	0.438 5	4.322 9	320.883	6.816	0.410 1	0.492 2	989.05	0.047 34
Opt₂	1.891 8	1.046 7	5.597 5	362.022	14.419	0.258 8	0.446 5	1183.25	0.025 21
Opt₃	1.430 8	0.604 0	5.749 0	347.063	8.680	0.190 6	0.470 2	1094.53	0.046 86

Table 7

Fig.13

Fig.14

Fig.15

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Optimization shape design of capsule-supersonic parachute system based on fusion surrogate strategy

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