| 引用本文: | 张晨曦,林三春,李易,唐硕.反向射流作用下可回收火箭升阻特性[J].哈尔滨工业大学学报,2024,56(4):24.DOI:10.11918/202303040 |
| ZHANG Chenxi,LIN Sanchun,LI Yi,TANG Shuo.Lift-to-drag characteristics of the propulsive descent stage of reusable rockets[J].Journal of Harbin Institute of Technology,2024,56(4):24.DOI:10.11918/202303040 |
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| 反向射流作用下可回收火箭升阻特性 |
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张晨曦1,2,林三春3,李易1,2,唐硕1,2
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(1.西北工业大学 航天学院,西安 710072; 2.陕西省空天飞行器设计重点实验室(西北工业大学), 西安 710072; 3.北京宇航系统工程研究所,北京 100076)
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| 摘要: |
| 可回收火箭动力减速过程中反向射流将大幅改变箭体气动特性,为获得反向射流对箭体气动特性的影响,利用数值模拟方法获得箭体升阻力系数,分析升阻特性变化规律并提出升阻特性表征参数。首先,对反向射流钝体构型进行数值模拟,将得到的结果与已公开的实验数据进行对比,验证了数值模拟方法的有效性。其次,采用RANS方法模拟了单喷管构型火箭多种典型飞行状态,得到箭体升阻力系数随迎角变化曲线以及升阻特性变化规律,通过对回流区内流动状态进行分析得到升阻特性改变的机理。最后,由反向射流对箭体气动特性影响程度提出表征参数。结果表明:反向射流会对箭体形成遮挡作用并影响箭体升阻力特性。有射流时升阻力特性受飞行高度影响较大,受飞行马赫数影响较小,与无射流时的规律恰好相反。大部分飞行工况下阻力系数小于0.1,部分高空飞行工况将出现负阻力。本研究提出以反向射流与箭体宽度比作为气动特性表征参数,可以较好地反映反向射流对箭体的遮挡作用并表征箭体在反向射流作用下的气动特性变化规律。 |
| 关键词: 火箭垂直回收 可回收火箭 反向射流 气动布局 气动特性 |
| DOI：10.11918/202303040 |
| 分类号:V211.3 |
| 文献标识码:A |
| 基金项目: |
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| Lift-to-drag characteristics of the propulsive descent stage of reusable rockets |
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ZHANG Chenxi1,2,LIN Sanchun3,LI Yi1,2,TANG Shuo1,2
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(1.School of Astronautics, North-western Polytechnical University, Xian 710072, China; 2.Shaanxi Aerospace Flight Vehicle Design Key Laboratory (North-western Polytechnical University), Xian 710072, China; 3.Beijing Institute of Astronautical Systems Engineering,Beijing 100076, China)
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| Abstract: |
| The opposing jet flow significantly alters the aerodynamic characteristics of the rocket body during the power deceleration process of the recoverable rocket. In order to obtain the influence of the opposing jet flow on the aerodynamic characteristics of the rocket body, the lift-drag coefficient of the rocket body is obtained by numerical simulation method. The change law of the lift-drag characteristic is analyzed and the representative parameters of lift-drag characteristic are propsed. Firstly, the numerical simulation of the opposing jet of blunt body was carried out, and the obtained results were compared with the published experimental data to verify the effectiveness of the numerical simulation method. Secondly, the RANS method was used to simulate various typical flight states of single-nozzle configuration rockets. The lift-drag coefficient of the rocket body changed with the angle of attack and the change law of lift-drag characteristics were obtained. The lift-drag characteristics were obtained by analyzing the flow state in the recirculation zone. Finally, the representative parameters are proposed according to the degree of influence of the opposing jet on the aerodynamic characteristics of the rocket body. Research findings indicate that the opposing jet forms a shielding effect on the rocket body and affects the lift-drag characteristics. In the presense of opposing jet, the lift-drag characteristics are greatly affected by the flight height, while the effect of flight Mach number is relatively minor, which is opposite to that observed without the opposing jet. The drag coefficient is less than 0.1 in most flight conditions, and negative drag may occur in some high-altitude flight conditions. To characterize the aerodynamic effects of the opposing jet on the rocket body, a parameter is proposed that represents the ratio of the opposing jet width to the rocket body width. This parameter effectively reflects the shielding effect of the opposing jet on the rocket body and characterizes the variations in its aerodynamic characterics of the opposing jet. |
| Key words: vertical recovery rockets reusable rockets opposing jet aerodynamic layout aerodynamic characteristics |
