直升机铝合金机身弹伤形态快速预测方法

doi:10.7527/S1000-6893.2025.32015

Abstract

Abstract:

For the rapid prediction and repair requirements of helicopter combat damage morphologies， a database for aluminum alloy body structures subjected to conical-cup-shaped armor-piercing bullets was established based on the Johnson-Cook constitutive model and impact finite element models. A double elliptic function model was developed to describe non-symmetric damage characteristics， incorporating key parameters such as bullet caliber， velocity， and incident angle to establish a relationship function for non-symmetric damage halves. A rapid prediction method for combat damage morphologies was proposed and compared against finite element numerical simulations， support vector machine mode optimized by genetic algorithm models（GA-SVR mode）， and experimental results. Subsequently， investigate the effects of projectile caliber， impact velocity， and incidence angle on wound ballistics morphology. The results demonstrate good agreement with experimental measurements， achieving maximum errors of 12.04% in width and 7.03% in length. Compared to finite element numerical simulations and the GA-SVR model， the rapid prediction method achieved MAPE （Mean Absolute Percentage Error） values of 2.87%， 4.32%， and 0.62% for the left semi-length， right semi-length， and width of the projectile hole， respectively， while the comparative methods yielded 2.92%， 2.67%， and 0.64% respectively. The MAE （Mean Absolute Error） for eccentricity was 0.554 and 0.35 respectively. The computational accuracy of the rapid prediction method is comparable to both finite element numerical method and the GA-SVR model. However， the computation time was reduced by approximately 88% and 97.7% respectively， demonstrating significantly improved computational efficiency. Compared to bullet caliber and velocity， incident angle has a greater impact on combat damage morphologies. The relationship between the incident angle and the left and right halves of perforation diameter is described by a two-term exponential function， while its relationship with offset distance is given by a three-term polynomial equation.

Key words: helicopter, armor-piercing bullet, aluminum alloy fuselage, bullet damage morphologies, rapid prediction method

CLC Number:

V229⁺.6

Zhen ZHANG, Jianfeng TAN, Jinglong ZHAO, Linhai CHEN, Yuze YAN, Changliang LIN. Rapid prediction method of bullet damage morphology of helicopter aluminum alloy fuselage[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(1): 232015.

Figures/Tables 25

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Table 1

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Table 2

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Fig.5

Table 3

Table 4

Fig.6

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Table 5

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Fig.11

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Table 6

RMSE for different speeds

项目	RMSE
项目	$v$ =900 m/s	$v$ =1 000 m/s		$v$ =1 100 m/s
左半长	0.725 2	0.624 3	0.543 6
右半长	0.608 7	0.508 2	0.217 4

Table 6

Fig.16

Fig.17

Fig.18

Table 7

RMSE for different calibers

项目	RMSE
项目	$d$ =25 mm	$d$ =30 mm	$d$ =35 mm
左半长	0.624 3	0.704 7	0.891 4
右半长	0.586 9	0.544 4	0.632 8

Table 7

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参数		数值
密度ρ/（kg·m^-3）		2 790
剪切模量G/GPa		27.6
弹性模量E/GPa		73.416
泊松比μ		0.33
屈服应力A/MPa		265
应变硬化常数B/MPa		426
应变硬化指数n		0.34
应变率常数C		0.015
热软化系数m		1
熔点T_m/K		775
室温T_r/K		300
断裂常数	D₁	0.130
	D₂	0.130
	D₃	-1.500
	D₄	0.011
	D₅	0

入射角度/ （°）	偏心距/ mm	宽度/mm	左半长/ mm	右半长/ mm
0	0	26.84	13.89	13.62
5	0.82	26.61	13.62	13.98
10	1.60	26.39	14.13	14.69
15	1.92	26.54	14.58	15.30
20	2.82	26.30	14.00	15.85
25	3.87	26.61	14.14	16.90
30	4.32	26.89	14.66	17.02
35	4.12	26.41	15.76	17.90
40	4.48	26.49	16.52	20.02
45	4.58	26.80	18.02	21.18
50	5.17	26.75	19.97	22.61
55	5.87	26.43	21.29	26.21
60	6.44	26.73	23.51	27.75
65	8.32	26.79	25.07	34.85
70	11.7	26.28	29.24	45.44
75	13.76	26.41	36.79	60.73

工况类型	偏心距/ mm	宽度/mm	左半长/ mm	右半长/ mm
有限元①	6.02	31.33	21.82	26.56
预测方法①	5.81	31.46	22.05	25.63
有限元②	3.81	36.47	23.40	26.31
预测方法②	4.05	36.65	22.56	24.96
有限元③	2.88	31.00	17.32	19.36
预测方法③	2.72	31.55	16.84	18.87
有限元④	5.58	31.13	20.57	23.77
预测方法④	5.71	31.51	19.96	23.34

参数	R²	MAE	RMSE
偏心距	0.982 1	0.350 1	0.437 9
宽度	0.996 7	0.192 1	0.240 3
左半长	0.987 4	0.572 9	0.732 4
右半长	0.994 2	0.593 9	0.740 4

序号	宽度/mm×长度/mm	误差/%
1，2	143.08×160.98，129.803×149.668	9.28，7.03
3，4	147.50×164.75，129.784×162.002	12.04，2.75
5，6	144.28×172.18，129.686×163.052	10.12，5.30

Rapid prediction method of bullet damage morphology of helicopter aluminum alloy fuselage

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