高超声速飞行器串联整流锥减阻的数值研究

发布时间：2018-08-30 17:40

【摘要】：通过为高超声速飞行器加装整流锥的方法,可以有效地使飞行器头部脱体激波形状发生改变,从而实现减阻降热的作用。加装串联整流锥后钝头体的流场中包含有多个激波、膨胀扇区以及回流区,它们相互作用导致波系结构较为复杂,为研究飞行器减阻带来了困难。目前,相关研究主要集中在单级整流锥方向。因此,对在高超声速流场下加装串联整流锥的飞行器的波系结构以及涡系结构等重要流场特性进行分析和对其减阻特性进行探究有着重要的作用。本文以高超声速飞行的钝头体飞行器为研究对象,对分别加装单级整流锥和串联整流锥的钝头体进行数值模拟,深入地研究了整流锥的减阻作用及影响因素。比较了单级整流锥与串联整流锥对流场的影响作用,研究了不同长度分布的串联整流锥的减阻效果,分析了飞行攻角与整流锥减阻效果的关系。其主要内容包括以下部分:针对高超声速飞行器绕流的问题,通过求解Navier-Stokes方程的方法分别对加装串联整流锥和单级整流锥钝头体的飞行过程进行数值模拟,分析了串联整流锥特有的流场特征,探究了二者的减阻机理。通过比较发现串联整流锥的减阻效果优于单级整流锥。在保证串联整流锥其余特征相同的前提下,对分别加装圆锥钉、平面钉、半球钉以及半球盘等四种不同头锥的整流锥进行了数值模拟,确定了最优头锥类型。之后,在保证头锥和后锥为最优头锥的条件下,对不同整流锥长度以及不同撑杆长度分布进行数值模拟。发现了整流锥长度和撑杆长度分布对减阻效果的影响规律。研究了加装串联整流锥的钝头体在不同攻角下的流场特征,通过对压力和流线的分析,发现其减阻效果和流场特征随攻角增大的变化情况,综合减阻效果和气动升力的数据分析,确定了在所考虑条件下的最佳飞行攻角。本文的研究为高超声速下整流锥设计提供了重要的参考,具有一定的理论意义和工程应用价值。
[Abstract]:By adding a rectifier cone to a hypersonic vehicle, the shape of the detached shock wave in the head of the vehicle can be changed effectively, thus reducing the drag and reducing the heat. There are many shock waves, expansion sectors and reflux regions in the flow field of the blunt body with series rectifier cone. The interaction between them leads to the complex structure of the wave system, which makes it difficult to study the drag reduction of the aircraft. At present, the research focuses on the direction of single stage rectifier cone. Therefore, it is very important to analyze the wave system structure and vortex system structure of the aircraft with series rectifier cone in hypersonic flow field and to study its drag reduction characteristics. In this paper, the passive body with a single stage rectifier cone and a series rectifier cone are numerically simulated, and the drag reduction of the rectifier cone and its influencing factors are deeply studied. The effect of flow field between single-stage rectifier cone and series rectifier cone is compared, the drag reduction effect of series rectifier cone with different length distribution is studied, and the relation between flight angle of attack and drag reduction effect of rectifier cone is analyzed. The main contents are as follows: aiming at the problem of the flow around hypersonic vehicle, the flight process of the blunt body with series rectifier cone and single stage rectifier cone is numerically simulated by solving the Navier-Stokes equation. The flow field characteristics of series rectifier cone are analyzed, and the drag reduction mechanism of them is discussed. By comparison, it is found that the drag reduction effect of series rectifier cone is better than that of single stage rectifier cone. On the premise that the other characteristics of series rectifier cone are the same, four kinds of rectifier cones with different head taper, such as conical nail, plane nail, hemispherical nail and hemispherical disc, are numerically simulated, and the optimal head cone type is determined. Then, under the condition that the head cone and the rear cone are the optimal head cone, the distribution of the different rectifier cone length and the different strut length is numerically simulated. The influence of the length of the rectifier cone and the length of the brace on the drag reduction effect is found. The flow field characteristics of a blunt body with a series rectifier cone at different attack angles are studied. Through the analysis of pressure and streamline, it is found that the drag reduction effect and flow field characteristics change with the increase of attack angle. According to the data analysis of drag reduction effect and aerodynamic lift, the optimal flight angle of attack is determined. The research in this paper provides an important reference for the design of the rectifier cone under hypersonic velocity and has certain theoretical significance and engineering application value.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V211

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