Numerical simulation research on opposing jet interaction characteristics of rocket inverse flight
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摘要:
有动力垂直回收是实现运载火箭可重复使用的关键技术之一。垂直回收过程中，火箭倒飞产生的大分离非规则流动，以及发动机逆向喷流与主流相互作用导致的复杂气动干扰，对数值模拟方法提出了严峻挑战。基于NNW-FlowStar软件和非结构混合网格技术，采用球头逆向喷流标模，以及自主开展的火箭倒飞逆向喷流风洞试验标模，对数值模拟方法进行了验证，研究不同双喷喷流状态对火箭倒飞逆向喷流干扰特性的影响。结果表明：NNW-FlowStar软件可以较好模拟火箭倒飞逆向喷流干扰特性，数值模拟结果与试验结果吻合较好，计算得到的流场结构与风洞试验一致；不同组合喷流形式呈现出不同的喷流干扰特性和流场结构，不同喷流方案轴向力差异明显，对力矩特性影响也较大，甚至会导致全箭本体的纵向静稳定性发生变化，在超声速来流状态采用双喷状态2即2个水平喷管的方案减速效果较好。
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关键词:
- 火箭倒飞 /
- 逆向喷流 /
- 干扰特性 /
- NNW-FlowStar /
- 数值模拟
Abstract:Powered vertical recovery is one of the key technologies to realize the reusable launch vehicles. The rocket's backward flight will create a huge separation irregular flow throughout the vertical recovery process, and complicated aerodynamic interference will result from the engine's reverse jet interacting with the mainstream. These pose serious challenges to numerical simulation methods. Based on NNW-FlowStar software and unstructured hybrid grid technology, the numerical method was validated using the ball head opposing jet model and the self-developed rocket opposing jet wind tunnel test model. The interference characteristics of different double jet states on the opposing jet flow of the rocket are studied. The study demonstrates that the NNW-FlowStar is more capable of simulating the interference features of a rocket's reverse flight, and the findings of the numerical simulations correlate well with the test results. Different combined jet forms show different jet interference characteristics and flow field structures. The axial force of different jet schemes varies significantly, which also has a great impact on torque characteristics and even leads to changes in the longitudinal static stability of the whole rocket body. In the supersonic flow state, the deceleration effect is best in the second double injection state.
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图 2 球头表面压力分布计算与风洞试验对比
Figure 2. Comparison between calculation and experimental pressure distribution on surface of ball head and wind tunnel tests
图 4 计算与试验流场结构对比
Figure 4. Comparison between computational and experimental flow field structure
图 7 火箭子级垂直回收构型网格分布
Figure 7. Grid distribution of rocket vertical recovery configuration
图 8 Ma=2.0，双喷状态计算与试验结果对比
Figure 8. Comparison between numerical and experimental for double jet state of Ma=2.0
图 9 α=0°时，计算得到的流场结构与风洞试验比较
Figure 9. Comparison between numerical and experimental when α=0° with wind tunnel tests
图 10 Ma=0.4，双喷状态喷流对气动特性影响
Figure 10. Influence of double jet state on aerodynamic characteristics of Ma=0.4
图 11 Ma=4.0，双喷状态喷流对气动特性影响
Figure 11. Influence of double jet state on aerodynamic characteristics of Ma=4.0
图 12 Ma=0.4，双喷状态喷流对流动结构影响
Figure 12. Influence of double jet state on flow structure of Ma=0.4
图 13 Ma=0.4，双喷状态喷流对迎风端面压力分布影响
Figure 13. Influence of double jet state on pressure distribution for windward surface of Ma=0.4
图 14 Ma=4.0，双喷状态喷流对流动结构影响
Figure 14. Influence of double jet state on flow structure of Ma=4.0
图 15 Ma=4.0，双喷状态喷流对迎风端面压力分布影响
Figure 15. Influence of double jet state on pressure distribution for windward surface of Ma=4.0
表 1 计算状态参数
Table 1. Parameters of simulation conditions
参数 数值 来流马赫数 2.5 来流总温/K 294.4 来流总压/kPa 275.8 喷流马赫数 1.0 喷流总压比 6.54 喷流总温/K 294.4 
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