高超声速气动加热下战斗部装药热-点火响应与典型结构热防护特性

doi:10.12382/bgxb.2024.0401

摘要/Abstract

摘要：

高超声速战斗部飞行时表面通常承受严重的气动加热,并经过结构传热影响内部装药的热安全性。为此,整体采用有限体积法,流固边界上采用双向耦合,模拟高超声速战斗部气动加热和结构传热问题。结合炸药化学反应动力学模型,开展了不同速度和攻角下的高超声速战斗部气动加热温度场分布规律和装药热-点火响应分析。研究结果表明:高超声速气动加热和结构传热下战斗部飞行时弹体和装药温度最高处主要集中在头部,并向后、向内递减,不同攻角下温度呈现不对称分布,迎风面温度随攻角的增大而升高,背风面温度随攻角的增大而降低;引入化学反应动力学模型,马赫数6高超声速战斗部装药约35.4s在装药顶部发生点火,温度为574K,战斗部飞行速度越快,所受气动加热越严重,其装药点火时间越短;设计了一种典型热防护结构,使得战斗部在以高超声速飞行100s的过程中,外壳和装药温度平均降低79.12%和71.45%,并保证内部装药不点火;研究结果可为高超声速战斗部热安全性评估提供技术支撑。

关键词: 气动加热, 结构传热, 点火响应, 温度场, 数值模拟

Abstract:

Hypersonic warheads usually induce serious aerodynamic heating during flying,and the warhead charge also bears a harsh thermal environment because of the structural heating which may affect its thermal safety.The finite volume method and the two-way fluid-structure interaction method are used to simulate the aerodynamic heating and structural heat transfer processes of hypersonic warheads.The temperature field distribution of pneumatic heating of hypersonic warhead and the thermal-ignition response of charge at different speeds and angles of attack are analyzed based on the chemical reaction kinetics model of explosive.The results reveale that the highest temperature occurs at the head of the warhead under aerodynamic heating and structural heating transferduring the hypersonic flight of warhead,and then it decreases backwards and inward.The temperature distribution is asymmetrical at different angles of attack,the temperature on the windward side increases with the increase in the angle of attack,and the temperature on the leeward side decreases with the increase of the angle of attack.After introducing the chemical reaction kinetics model,the ignition of the charge appears on its head at 35.4s and 574K.the faster the warhead’s speed is,the more severe the aerodynamic heating it experiences is,and the shorter the ignition time of charge is.A thermal protection structure is designed,which can effectively increase the temperatures of warhead’s shell and charge by 79.12% and 71.45% during its 100s flight process as well as ensure that the internal charge does not ignite.This study is of great significance in addressing the thermal safety issues of hypersonic warhead charges.

Key words: aerodynamic heating, structural heat transfer, ignition response, temperature field, numerical simulation

中图分类号:

TJ410

闫铭, 王昕捷, 黄风雷, 尤飒. 高超声速气动加热下战斗部装药热-点火响应与典型结构热防护特性[J]. 兵工学报, 2025, 46(6): 240401-.

YAN Ming, WANG Xinjie, HUANG Fenglei, YOU Sa. Thermal-ignition Response of Warhead Charge and Characteristics of Typical Thermal Protection Structure under Hypersonic Aerodynamic Heating[J]. Acta Armamentarii, 2025, 46(6): 240401-.

图/表 30

图1 几何模型

Fig.1 Geometric model

图2 1:1.25缩比尖卵型战斗部截面图

Fig.2 Cross-sectional view of 1:1.25 scaled warhead

图3 网格划分示意图

Fig.3 Mesh division

表1 边界层网格无关性

Table 1 Grid independence of boundary layer

边界层第1层法向网格高度/ mm	边界层网格增长率	边界层网格层数	全域网格总数/万	计算时长/h	y⁺
0.1	1.3	14	281	24	48.00
0.05		16	487	48	8.94
0.01		22	553	52	1.09
0.005		25	666	64	0.50

图4 UDF流程图

Fig.4 Flowchart of user-defined function

表2 流体域物性参数

Table 2 Physical parameters of fluid zone

参数	量热完全空气数值	热完全空气数值^[14]
r/(kg·m^-3)	理想气体	理想气体
C_p/(J·kg^-1·K^-1)	1006.43	Nasa-9
λ/(W·m^-1·K^-1)	0.0242	欧肯关系
μ/(kg·m^-1·s^-1)	1.7894×10^-5	布洛特内曲线

图5 不同气体模型驻点温度变化

Fig.5 Temperature variation curves of stagnation points for different gas models

表3 反应动力学参数[21]

Table 3 Reaction kinetic parameters[21]

No.	材料	Z/s^-1	E/(J·mol^-1)	Q/(J·kg^-1)	ΔS_f/(J·mol^-1·K^-1)	E_f/(J·mol^-1)	ΔS_r/(J·mol^-1·K^-1)
1	DNAN	1.2×10¹¹	1.72×10⁵	4.92×10⁶
2	HMX		1.89×10⁵	-2.5×10⁴	123.00	2.04×10⁵	89
3	HMX		8.65×10⁴	-2.5×10⁴	-40.37	1.02×10⁵	-75.2
4	HMX	3.16×10¹⁶		-1.2×10⁵		2.0×10⁵
5	HMX	2.00×10¹⁵		3.2×10⁶		1.731×10⁵
6	NTO	9.93×10¹⁷	2.72×10⁵	5.87×10⁶
7	Binder	1.1×10¹²	1.675×10⁵	6.005×10⁵

表4 装药的物理性质参数[21]

Table 4 Physical property parameters of charge[21]

材料	ρ/(kg·m^-3)	Cp/(J·kg^-1·K^-1)	λ/(W·m^-1·K^-1)	L/(J·kg^-1)	T_s/K	T_e/K
DNAN(solid)	1450	315.3+2.65T	0.25	175000	370
DNAN(liquid)	1330	1250	0.17			375
HMX	1850	92.93+3.305T	0.4368-0.000444T
NTO	1850	1088	0.27
Binder	2020	1000.43	0.0527
Al	2719	871	1.39

图6 边界条件示意图

Fig.6 Diagram of boundary conditions

图7 外流场压力、密度和温度分布云图

Fig.7 Nephograms of pressure,density and temperature distribution of external flow field

图8 马赫数6下战斗部壳体和装药温度分布云图

Fig.8 Nephogram of warhead shell and charge temperature distribution

图9 战斗部壳体和装药温度分布

Fig.9 Temperature distribution of warhead shell and charge

图10 战斗部壳体和装药底部温度分布

Fig.10 Bottom temperature distribution of warhead shell and charge

图11 不同攻角计算域温度分布云图

Fig.11 Nephogram of computational domain interface temperature at different angles of attack

图12 以不同攻角飞行的战斗部壳体温度等值线图

Fig.12 Temperature contour plot of warhead shell at different angles of attack

图13 不同攻角战斗部壳体和装药表面温度分布数值

Fig.13 Surface temperature distribution of warhead shell and charge at different angles of attack

图14 不同马赫数下计算域温度分布云图

Fig.14 Nephogram of computational domain interface temperature under different Mach numbers

图15 点火时刻战斗部装药剖面温度分布图

Fig.15 Distribution of temperature on the section of charge at the moment of ignition

图16 战斗部装药点火位置温度历史曲线

Fig.16 Temperature-time curve at the ignition position of charge

图17 不同时刻战斗部装药剖面DNAN液相分数分布云图

Fig.17 Distribution of liquid-phase DNAN on the section of charge at different times

图18 不同时刻战斗部装药DNAN液相分数统计分布

Fig.18 Liquid-phase DNAN statistical distribution of charge at different moments

图19 不同时刻战斗部装药剖面δ-HMX分布云图

Fig.19 Distribution of δ-HMX on the section of charge at different times

图20 战斗部装药点火位置HMX质量分数-时间曲线

Fig.20 Mass fraction-time curve of β-HMX,δ-HMX and gaseous products at the ignition position of charge

图21 战斗部装药点火位置处生热速率

Fig.21 Heat generation rate at the ignition position of charge

图22 不同马赫数战斗部装药点火位置温度

Fig.22 Temperature-time curves of ignition position of charge under different Mach numbers

图23 高超声速战斗部热防护结构

Fig.23 Thermal protection structure for hypersonic warhead

表5 热防护层材料物理性质参数

Table 5 Physical parameters of insulation zone

材料	r/(kg·m^-3)	C_p/(J·kg^-1·K^-1)	λ/(W·m^-1·K^-1)
超高温陶瓷^[24]	5330	C_p₁	λ₁
气凝胶^[25-26]	220	800	0.0232(293K), 0.0252(1073K), 0.0317(1273K)

表6 各马赫数下有无热防护结构战斗部各区域最高温度

Table 6 Maximum temperature at each region of warhead with or without heat insulation under different Mach numbers K

马赫数	有无热防护层	超高温陶瓷	气凝胶	外壳	装药
5	有	1015.22	991.817	311.07	303.45
5	无			1032.89	705.98
6	有	1442.50	1412.51	318.41	305.61
6	无			1446.58	994.48
7	有	1962.09	1950.02	329.56	309.18
7	无			1908.76	1350.52
8	有	2643.60	2635.01	342.39	313.62
8	无			2424.84	1783.84

图24 战斗部各区域最高温度对比

Fig.24 Temperature comparison of warhead’s each region

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