【摘要】：通過為高超聲速飛行器加裝整流錐的方法,可以有效地使飛行器頭部脫體激波形狀發(fā)生改變,從而實(shí)現(xiàn)減阻降熱的作用。加裝串聯(lián)整流錐后鈍頭體的流場中包含有多個激波、膨脹扇區(qū)以及回流區(qū),它們相互作用導(dǎo)致波系結(jié)構(gòu)較為復(fù)雜,為研究飛行器減阻帶來了困難。目前,相關(guān)研究主要集中在單級整流錐方向。因此,對在高超聲速流場下加裝串聯(lián)整流錐的飛行器的波系結(jié)構(gòu)以及渦系結(jié)構(gòu)等重要流場特性進(jìn)行分析和對其減阻特性進(jìn)行探究有著重要的作用。本文以高超聲速飛行的鈍頭體飛行器為研究對象,對分別加裝單級整流錐和串聯(lián)整流錐的鈍頭體進(jìn)行數(shù)值模擬,深入地研究了整流錐的減阻作用及影響因素。比較了單級整流錐與串聯(lián)整流錐對流場的影響作用,研究了不同長度分布的串聯(lián)整流錐的減阻效果,分析了飛行攻角與整流錐減阻效果的關(guān)系。其主要內(nèi)容包括以下部分:針對高超聲速飛行器繞流的問題,通過求解Navier-Stokes方程的方法分別對加裝串聯(lián)整流錐和單級整流錐鈍頭體的飛行過程進(jìn)行數(shù)值模擬,分析了串聯(lián)整流錐特有的流場特征,探究了二者的減阻機(jī)理。通過比較發(fā)現(xiàn)串聯(lián)整流錐的減阻效果優(yōu)于單級整流錐。在保證串聯(lián)整流錐其余特征相同的前提下,對分別加裝圓錐釘、平面釘、半球釘以及半球盤等四種不同頭錐的整流錐進(jìn)行了數(shù)值模擬,確定了最優(yōu)頭錐類型。之后,在保證頭錐和后錐為最優(yōu)頭錐的條件下,對不同整流錐長度以及不同撐桿長度分布進(jìn)行數(shù)值模擬。發(fā)現(xiàn)了整流錐長度和撐桿長度分布對減阻效果的影響規(guī)律。研究了加裝串聯(lián)整流錐的鈍頭體在不同攻角下的流場特征,通過對壓力和流線的分析,發(fā)現(xiàn)其減阻效果和流場特征隨攻角增大的變化情況,綜合減阻效果和氣動升力的數(shù)據(jù)分析,確定了在所考慮條件下的最佳飛行攻角。本文的研究為高超聲速下整流錐設(shè)計(jì)提供了重要的參考,具有一定的理論意義和工程應(yīng)用價值。
[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.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V211

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本文編號：2213794