基于无翼载荷的火箭橇多场耦合特性分析

doi:10.12382/bgxb.2024.0394

摘要/Abstract

摘要：

无翼有效载荷是火箭橇试验系统的常见载荷类型,在宽速域水平滑跑时由于非定常气动力、振动与噪声等多场耦合在分离时易出现抬头、低头现象。以双轨火箭橇的无翼有效载荷试验系统为研究对象,对宽速域(马赫数0.4~2.0)水平助推滑跑的声振力耦合进行高精度数值模拟。研究结果表明:在滑跑过程中,有效载荷与助推器中间产生低压区,且随滑跑速度不断扩大作用范围;高速流场的气动载荷会逐渐使火箭橇在有效载荷头部和尾部位置处产生较大变形,主要表现为抬头现象;宽速域水平助推滑跑的气动噪声随滑跑速度增大,高声压级区域由中心逐渐向外扩展;相关研究可为新一代高超声速火箭橇试验系统设计与高精度地面动态测试提供技术支持。

关键词: 火箭橇, 水平滑跑, 多场耦合, 气动特性, 噪声特性

Abstract:

Wingless payload is a common type of payload in the rocket sled test system,which is susceptible to head-up and head-down phenomena during separation due to the multi-field coupling of unsteady aerodynamics,vibration and aeroacoustic noise during the horizontal running in a wide speed domain.The,acoustic-vibration force coupling of horizontal boost glide in a wide speed domain ( Mach number of 0.4-2.0) is numerically simulated by taking a wingless payload test system of double-track rocket sled as the research object.The results show that a low-pressure region is generated between the payload and the booster during running,and the range of action is continuously expanded with the running speed.The aerodynamic load of high-speed flow field gradually makes the rocket sled produce large deformation at the head and tail positions of the payload,which is mainly manifested as a “head-up” phenomenon.The aerodynamic noise of the horizontal booster running in the wide speed domain increases with the running speed,and the high sound pressure level region gradually expands from the center to the periphery.The relevant research can provide technical support for the design of new generation of hypersonic rocket sled test system and the high-precision ground dynamic test.

Key words: rocket sled, horizontal running, multi-field coupling, aerodynamic characteristics, aeroacoustic noise characteristics

中图分类号:

V211.3

王文杰, 马鑫雨, 赵旭, 李濠君, 向粤, 杨龙. 基于无翼载荷的火箭橇多场耦合特性分析[J]. 兵工学报, 2025, 46(4): 240394-.

WANG Wenjie, MA Xinyu, ZHAO Xu, LI Haojun, XIANG Yue, YANG Long. Analysis of Multi-field Coupling Characteristics of Rocket Sled with a Wingless Payload[J]. Acta Armamentarii, 2025, 46(4): 240394-.

图/表 22

图1 火箭橇系统侧视图

Fig.1 Side view of rocket sled system

图2 AGARD HB-2标准模型

Fig.2 AGARD HB-2 standard model

图3 全局网格

Fig.3 Global mesh

图4 局部网格

Fig.4 Local mesh

图5 网格无关性验证

Fig.5 Mesh independence validation

图6 不同滑跑速度火箭橇周围流场压力分布

Fig.6 Pressure distributions of flow field at different running speeds

图7 火箭橇周围流场流线分布

Fig.7 Streamline distribution of flow field around the rocket sled

图8 不同滑跑速度阻力系数与升力系数变化

Fig.8 Variation of resistance coefficient and lift coefficient at different running speeds

图9 不同滑跑速度有效载荷俯仰力矩变化

Fig.9 Variation of payload pitching moment at different running speeds

图10 有效载荷头部压力分布

Fig.10 Payload head pressure distribution

图11 有效载荷薄壁结构尺寸

Fig.11 Payload thin-walled structure dimensions

图12 助推器薄壁结构尺寸

Fig.12 Booster thin-walled structure dimensions

图13 固体结构计算网格

Fig.13 Solid structure computational mesh

表1 火箭橇橇体结构材料参数

Table 1 Structural material parameters of rocket skid

参数	数值
密度/(kg·m^-3)	7850
弹性模量/MPa	2.1×10⁵
剪切模量/MPa	7.7×10⁴
泊松比	0.3
压缩屈服强度/MPa	250
压缩极限屈服强度/MPa	460

图14 不同滑跑速度下橇体总变形分布

Fig.14 Total deformation distribution of rocket sled at different running speeds

表2 不同速度下两种方向最大变形量

Table 2 Maximum deformations in both directions at different running speeds

Ma	最大竖向变形/mm	最大横向变形/mm
0.6	0.18	0.10
1.2	0.62	0.35
2.0	2.03	0.98

图15 不同滑跑速度橇体等效应力分布

Fig.15 Equivalent stress distribution of rocket sled at different running speeds

表3 不同工况下橇体最大等效应力与最大变形量

Table 3 The maximum equivalent stress and maximum deformation of the sled under different working conditions

滑跑速度 Ma	最大应力/ MPa	最大应力位置	最大变形量/mm	最大变形位置
0.6	30.6	后连接与助推器接触处	0.22	有效载荷尾部
1.2	156.0	后连接与助推器接触处	1.03	有效载荷尾部
2.0	329.4	前连接与助推器接触处	2.21	有效载荷头部

图16 噪声接收器所在平面

Fig.16 Noise receiver on a plane

图17 不同滑跑速度时特征接收点SPSD分布

Fig.17 Sound power spectral density distribution at characteristic receiving points at different running speeds

图18 不同滑跑速度对称面总声压云图

Fig.18 Cloud image of total sound pressure on symmetric surface at different running speeds

图19 监测平面声指向性图

Fig.19 Sound directivity on the monitoring plane

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