本文關鍵詞：超聲速進氣道起動特性研究　出處：《航天動力技術研究院》2016年碩士論文　論文類型：學位論文

  更多相關文章： 超聲速進氣道 起動性能 進氣道堵蓋 出口反壓 固體火箭沖壓發(fā)動機

【摘要】：固體火箭沖壓發(fā)動機具有比沖高、工作時間長、結構簡單、機動性強等優(yōu)點,是先進導彈動力系統(tǒng)的重要發(fā)展方向之一。超聲速進氣道作為沖壓發(fā)動機的核心部件之一,其起動性能決定了發(fā)動機的工作包絡。因此,確定超聲速進氣道的起動特性至關重要。地面仿真和飛行試驗中多次證實,發(fā)動機轉級裝置——進氣道堵蓋對起動性能影響顯著。某次飛行試驗中,由于轉級時進氣道不起動,造成飛行失敗�？梢�,確定進氣道起動特性和堵蓋影響機制已成為沖壓發(fā)動機技術發(fā)展和工程應用中亟需解決的關鍵問題。本文基于工程實際需求,針對典型沖壓發(fā)動機的雙下側二元混壓式進氣道起動特性,開展了數(shù)值仿真研究。本文首先建立了彈體/進氣道一體化三維仿真模型,研究了雙下側二元進氣道在轉級工況下起動狀態(tài)的流場特性。結果表明:隨反壓增加,結尾激波系逐漸向上游移動,到達喉道后,繼續(xù)增大反壓,在一定范圍內,結尾激波系可以穩(wěn)定在收縮通道內,即存在穩(wěn)定的亞臨界狀態(tài)。然后,本文研究了Ma=2.5~3.5、α=-2o~8o、β=0o~6o工況下進氣道的流場特性和抗反壓性能,擬合了極限反壓比預估公式。結果表明:進氣道極限反壓與來流總壓、喉道總壓恢復系數(shù)和流量系數(shù)相關;隨來流馬赫數(shù)增大,自由流總壓和流量系數(shù)均提高,喉道總壓恢復系數(shù)降低,綜合影響下,進氣道抗反壓能力增強;隨攻角增大,總壓恢復系數(shù)和流量系數(shù)均提高,進氣道極限反壓升高;在側滑情況下,背風側進氣道性能參數(shù)和抗反壓能力均優(yōu)于迎風側進氣道;隨側滑角增大,兩側性能參數(shù)變化趨勢不同,背風側進氣道總壓恢復系數(shù)、流量系數(shù)先升高后降低,迎風側持續(xù)降低;當迎風側不起動后,迎風側脫體激波會干擾背風側的外壓縮波系,甚至可能使背風側也不起動。其次,本文仿真分析了不同工況下進氣道的不起動/再起動過程。分析結果表明:進氣道入口前氣流總壓是決定進氣道再起動反壓的主要因素;來流馬赫數(shù)越大,氣流總壓越高,再起動反壓越高;攻角越大,彈體干擾越弱,入口前氣流總壓越高,再起動反壓越高,α≥2o后彈體干擾極弱,再起動反壓不再隨攻角增大而變化;在側滑情況下,兩側進氣道再起動不同步;背風側進氣道受彈體干擾小,再起動反壓基本不隨側滑角變化;對于迎風側進氣道,當側滑角β≤2o時,彈體干擾較弱,再起動反壓接近背風側,當側滑角β≥4o時,隨側滑角增大,彈體干擾增強,再起動反壓降低,明顯滯后于背風側。最后,本文重點研究了固體火箭沖壓發(fā)動機轉級裝置——進氣道堵蓋對進氣道起動特性的影響。根據(jù)不同轉級時序,分別對入口堵蓋和出口堵蓋開啟過程進行非穩(wěn)態(tài)流場仿真。結果表明:入口堵蓋有利于進氣道起動,可使進氣道起動馬赫數(shù)從Ma=2.31降到Ma=2.29;在入口開啟,出口封堵時,進氣道流場出現(xiàn)周期性振蕩,頻率與一階聲模態(tài)一致,進氣道越下游位置壓力峰值越高;出口堵蓋開啟時刻對進氣道起動性能有較大影響,充填階段開啟更有利于進氣道起動;在釋放階段開啟,進氣道會出現(xiàn)短時間的低頻、大幅喘振。
[Abstract]:Solid rocket ramjet engine has high specific impulse, long working time, simple structure, flexibility, is one of the important development direction of advanced missile power system. As one of the core components of supersonic inlet of ramjet engine, its starting performance determines the working envelope of engine. Therefore, it is of great importance to determine the starting characteristics of supersonic inlet. Repeatedly confirmed ground simulation and flight test, engine level switching device, inlet blocking effect on the cover was starting performance. One of the flight tests, due to the unstart transfer, causing flight failure. Obviously, determine the inlet starting characteristics and cover influence mechanism has become a key issue in the urgent need for the development of ramjet technology and engineering the application in solution. In this paper, based on the demand of engineering, aiming at the typical double downside ramjet inlet two yuan starting characteristics And carry out numerical simulation. This paper established a three-dimensional simulation model of missile / engine integration, flow characteristics of the double side two yuan in transfer under the condition of inlet starting. The results show that with increasing back pressure at the end of the shock wave system gradually moves upstream to the throat, continue to increase the back pressure in the within a certain range, at the end of shock wave can stabilize the contraction in the channel, there is a stable subcritical state. Then, this paper studies the Ma=2.5~3.5, alpha =-2o~8o, beta =0o~6o under the condition of flow characteristics of the inlet and the anti pressure performance, fitting the limit back pressure ratio prediction formula. The results show that the inlet pressure and flow limit total pressure, total pressure recovery coefficient and flow coefficient of throat; with the Mach number increases, the free flow total pressure and flow coefficient were increased, the total pressure recovery coefficient decreased throat, under the combined effects of inlet of the anti pressure ability enhancement Strong; with the angle of attack increases, the total pressure recovery coefficient and flow coefficient were increased, the inlet pressure in the limit of anti sideslip; under the condition of the leeward side of the inlet performance parameters and anti pressure ability are better than the windward side inlet; with the increase of sideslip angle, different change trend on both sides of the performance parameters, the total pressure recovery coefficient of the inlet flow on the leeward side. The coefficient increased first and then decreased, the windward side continues to decrease; when the windward side does not start after the windward leeward side will interfere with the detached shock compression wave, even to the leeward side is not starting. Secondly, this paper analyzed the unstart / restart process under different conditions. The analysis results show that the inlet port in front of the entrance flow total pressure is decided to start the main factors of back pressure inlet; flow Maher number increases, the total air pressure is higher, then starting back pressure is high; the bigger the attack angle, body interference is weak in front of the entrance of air pressure The higher, then starting back pressure higher than 2O, alpha after body interference is very weak, and then starting back pressure is no longer with the angle of attack increases and changes in sideslip; under the condition of side inlet restarting is not synchronized; the leeward side inlet by projectile interference, then starting pressure almost does not change with the sideslip angle on the windward side; when the inlet, the sideslip angle beta = 2O, body interference is weak, then starting back pressure close to the leeward side, when the sideslip angle beta is greater than or equal to 4O, with the increase of the sideslip angle, body interference enhancement, then starting back pressure decreased, obvious lag in the leeward side. Finally, this paper focuses on the research of solid rocket ramjet transfer device inlet cover effect on inlet starting characteristics. According to different level timing of entrance closure and export cover opening process of unsteady flow simulation. The results show that the entrance cover for inlet starting, the inlet starting from the Maher number Ma=2.31 reduced to Ma=2.29; in the open entrance, exit plugging, inlet flow periodic oscillation frequency and first order acoustic mode, the inlet position downstream of the peak pressure is high; export cover opening time has great influence on the performance of inlet starting, the filling stage of opening more conducive to open the inlet starting in the release phase of low frequency; there will be a short period of time, the inlet surge sharply.

【學位授予單位】：航天動力技術研究院
【學位級別】：碩士
【學位授予年份】：2016
【分類號】：V211.48

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