Investigation of base load characteristics during aerodynamic reentry phase of super heavy starship
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摘要:
垂直返回可重复使用火箭在返回气动减速阶段由于火箭底部为迎风面，对底部发动机喷管的力、热特性产生显著影响。采用计算流体力学方法对超重星舰一子级火箭底部的流动特性进行数值模拟，获得了火箭在典型气动减速段工况马赫数为3.5、攻角为0°～15°范围的流场结构及底部喷管的载荷分布。结果表明：火箭返回时底部形成了随攻角变化的弓形激波，在背风侧形成了大尺度的流动分离；外圈、中圈和内圈喷管所受侧向载荷之比为335∶19∶1，呈指数级下降；随着攻角增加，喷管侧向载荷从背风侧向迎风侧逐渐减小。气动热对火箭底部以及外圈喷管的影响显著。研究结果可为垂直返回火箭底部发动机的布局及气动减速阶段的姿态控制方案提供理论支撑。
Abstract:During the aerodynamic deceleration phase of a vertically landing reusable rocket, the vehicle’s base serves as the windward surface, exerting a significant influence on thrust, nozzle side forces, and the thermal environment of the bottom-mounted engines. The reentry flow field is highly complex. Computational fluid dynamics (CFD) simulations were conducted to investigate the flow characteristics of the Starship lower stage, while the flow structure together with the pressure and thermal loads on the base nozzles was analyzed for Mach number of 3.5 at attack angles ranging from 0° to 15°. The side loads acting on the outer, middle, and inner nozzles exhibited an exponential decay, with a ratio of approximately 335∶19∶1. As the attack angle increased, the side load on the windward nozzles decreased, whereas that on the leeward nozzles increased. The base region and outer nozzles were strongly affected by aerodynamic heating. These results provide a theoretical guidance for the layout of base-mounted engines in vertical-landing rockets and for attitude control strategies during the aerodynamic deceleration phase.
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Key words:
- bottom flow /
- bottom loads /
- reusable rocket /
- compressible flow /
- supersonic flow
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图 1 星舰第5次试验助推器返回时速度剖面
Figure 1. Velocity profile of the starship booster during the fifth test flight
图 8 在Z = −3.5 截面处的Lamb矢量散度云图
Figure 8. Contours of Lamb vector divergence on thez = −3.5 plane
图 9 根据${\lambda _2}$准则绘制的涡结构
Figure 9. Vortex structures described based on ${\lambda _2}$ criterion
图 10 子级火箭底部温度分布
Figure 10. Temperature distribution on the base of the Starship lower stage
图 11 喷管侧向载荷$ {\tilde f_{{\text{side}}}} $分布
Figure 11. Side loads $ {\tilde f_{{\text{side}}}} $ distribution on the nozzle
图 12 喷管轴向载荷$ {\tilde f_{{\text{axial}}}} $分布
Figure 12. Axial loads $ {\tilde f_{{\text{axial}}}} $ distribution on the nozzle
图 13 不同攻角下喷管壁面压力分布
Figure 13. Pressure distribution on the nozzle wall at different angles of attack
图 18 底面无量纲温度分布曲线
Figure 18. Non-dimensional temperature distribution curve on the bottom
表 1 几何参数表
Table 1. Geometry parameters
m 几何参数 数值 火箭直径D 9.00 内圈半径${r_3}$ 0.78 中圈半径${r_2}$ 2.36 外圈半径${r_1}$ 4.03 喷管高度h 0.69 喷管出口半径r 0.58 喷管突出距离ΔL 0.30 
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