本文選題：吸氣式飛行器 + 升力體��； 參考：《空氣動力學(xué)學(xué)報》2016年01期

【摘要】：尾噴流對升力體高超聲速飛行器的氣動特性影響顯著,風(fēng)洞噴流模擬測力試驗是研究升力體飛行器尾噴流干擾效應(yīng)的重要手段。在尾噴流模擬氣動力試驗中,選取恰當(dāng)?shù)膰娏髂M參數(shù),以及克服噴流供氣管路對天平測力的干擾以提高測量精準(zhǔn)度,是需要解決的關(guān)鍵技術(shù)。在CARDC的Ф1米高超聲速風(fēng)洞中,研究了采用冷噴流模擬、飛行器整體模型測力的升力體飛行器尾噴流模擬測力試驗方法。通過優(yōu)化模型結(jié)構(gòu)設(shè)計、選用小干擾的噴管分斷縫隙密封措施,解決了帶尾噴流模擬條件下的升力體飛行器氣動力精確測量問題,提高了帶噴流氣動力試驗數(shù)據(jù)精度,接近常規(guī)氣動力試驗的水平。
[Abstract]:The effect of tail jet on aerodynamic characteristics of lift hypersonic vehicle is significant. Wind tunnel simulation test of jet force measurement is an important means to study the effect of tail jet interference on lift body vehicle. In the aerodynamic test of tail jet simulation, the key technology to be solved is to select appropriate parameters of jet simulation, and to overcome the interference of jet supply line to the balance force measurement to improve the accuracy of measurement. In a 1 meter hypersonic wind tunnel of CARDC, a method for simulating the force measurement of the tail jet of a lift vehicle by using a cold jet simulation and a global model of the vehicle is studied. By optimizing the structural design of the model and selecting the small interference nozzle break slot sealing measures, the precise measurement of the aerodynamic force of the lift vehicle under the condition of simulation with tail jet flow is solved, and the accuracy of the aerodynamic test data with the jet flow is improved. Close to the level of conventional aerodynamic tests.
【作者單位】： 中國空氣動力研究與發(fā)展中心超高速空氣動力研究所;中國空氣動力研究與發(fā)展中心高超聲速沖壓發(fā)動機技術(shù)國防科技重點實驗室;
【分類號】：V211.7
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本文編號：1868017