面向运载火箭栅格舵的最优操纵效率特征与宽速域气动优化设计方法

doi:10.7527/S1000-6893.2024.29887

Abstract

Abstract:

Wide-speed-range grid fins design is one of the key technologies for re-use of sub-stages of launch vehicle. In the course of a substage return flight， grid fins experience subsonic， transonic， supersonic， and other speed regimes. In different speed regimes， the control efficiency and aerodynamic characteristics of grid fins are completely different， and even contradictory， which makes the aerodynamic design of grid fins with high efficiency face great challenges. To address the above problems， this paper applies the aerodynamic design optimization method based on machine learning surrogate model to carry out aerodynamic optimization design of grid fins in subsonic， transonic and supersonic typical states respectively， and obtains the optimal aerodynamic shape in different speed regimes. The flow mechanism of the optimal control efficiency of the grid fins in different speed regimes is analyzed and revealed， which can provide guidance for the subsequent design. Because of the different optimization mechanisms of different speed regimes， there are contradictions between the optimal designs of different speed regimes. In view of the above contradictions， the multi-objective aerodynamic design optimization of wide-speed-range grid fins is carried out， taking into account the influence of sub， tran and supersonic speed regimes. The optimization results significantly improve the wide-speed-range aerodynamic performance of grid fins and improve the optimal control efficiency of grid fins.

Key words: grid fins, wide speed range, aerodynamic design optimization, surrogate model, computational fluid dynamics

CLC Number:

V211.3

Mingqi LIU, Zhonghua HAN, Tao DU, Chenzhou XU, Han ZENG, Keshi ZHANG, Wenping SONG. Optimal control efficiency characteristics and wide-speed-range aerodynamic design optimization method for grid fins of launch vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(20): 129887.

Figures/Tables 46

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Table 1

Range of design variables for aerodynamic design optimization of grid fins

变量类型	$W / C$	$φ / (°)$	$θ / (°)$
上界	3.3	30	45
下界	0.4	0	0

Table 1

Fig.13

Fig.14

Table 2

Comparison of design variables of grid fins before and after optimization at subsonic regime

外形	$W / C$	$φ / (°)$	$θ / (°)$	$C L$
基准外形	0.67	0	0	0.221 5
优化外形	1.52	25.8	34.8	0.380 8

Table 2

Fig.15

Fig.16

Fig.17

Fig.18

Table 3

Comparison of design variables of grid fins before and after optimization at transonic regime

外形	$W / C$	$φ / (°)$	$θ / (°)$	$C L$
基准外形	0.67	0	0	0.177 9
优化外形	2.94	1.8	6.7	0.483 2

Table 3

Fig.19

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Fig.24

Table 4

Comparison of design variables between baseline and optimized grid fins at supersonic regime

外形	$W / C$	$φ / (°)$	$θ / (°)$	$C L$
基准外形	0.67	0	0	0.197 0
优化外形	0.75	3.0	34.0	0.241 4

Table 4

Fig.25

Fig.26

Table 5

Comparison of surrogate model predictions and CFD numerical simulations of optimal solution lift coefficients for different speed regimes

速域	$C L, s u r r o g a t e m o d e l$	$C L, C F D$	误差/%
亚声速（ $M a = 0.4$ ）	0.380 5	0.380 8	0.080 2
跨声速（ $M a = 0.9$ ）	0.483 0	0.483 2	0.054 3
超声速（ $M a = 3.0$ ）	0.241 3	0.241 4	0.010 8

Table 5

Table 6

Comparison of sub， tran and supersonic lift coefficients for optimal shape in different speed regimes

外形	$C L$
外形	Ma=0.4	Ma=0.9	Ma=3.0
基准外形	0.221 5	0.177 9	0.197 0
亚声速优化外形	0.380 8	0.358 9	0.208 3
跨声速优化外形	0.202 1	0.483 2	0.166 5
超声速优化外形	0.248 5	0.201 4	0.241 4

Table 6

Fig.27

Fig.28

Fig.29

Table 7

Comparison of design variables between baseline shape and Optimized shape 1 at wide speed regimes

外形	$W / C$	$φ / (°)$	$θ / (°)$
基准外形	0.67	0	0
优化外形1	1.715	10.09	41.0

Table 7

Table 8

Comparison of lift coefficient between baseline shape and Optimized shape 1 at wide speed regimes

速域	模型	$C L$	变化/%
亚声速（ $M a = 0.4$ ）	基准外形	0.221 5	+55.9
亚声速（ $M a = 0.4$ ）	优化外形1	0.345 3	+55.9
跨声速（ $M a = 0.9$ ）	基准外形	0.177 9	+139.6
跨声速（ $M a = 0.9$ ）	优化外形1	0.426 2	+139.6
超声速（ $M a = 3.0$ ）	基准外形	0.197 0	-6.5
超声速（ $M a = 3.0$ ）	优化外形1	0.184 3	-6.5

Table 8

Fig.30

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Fig.33

Fig.34

Table 9

Comparison of design variables between baseline shape and Optimized shape 2 at wide speed regimes

外形	$W / C$	$φ / (°)$	$θ / (°)$
基准外形	0.67	0	0
优化外形2	1.65	29.8	24.7

Table 9

Table 10

Comparison of lift coefficient between baseline shape and Optimized shape 2 at wide speed regimes

速域	外形	$C L$	变化/%
亚声速（ $M a = 0.4$ ）	基准外形	0.221 5	+61.1
亚声速（ $M a = 0.4$ ）	优化外形2	0.356 8	+61.1
跨声速（ $M a = 0.9$ ）	基准外形	0.177 9	+108.3
跨声速（ $M a = 0.9$ ）	优化外形2	0.370 5	+108.3
超声速（ $M a = 3.0$ ）	基准外形	0.197 0	+16.8
超声速（ $M a = 3.0$ ）	优化外形2	0.230 1	+16.8

Table 10

Fig.35

Fig.36

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Optimal control efficiency characteristics and wide-speed-range aerodynamic design optimization method for grid fins of launch vehicle

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