本文關(guān)鍵詞： 風(fēng)洞實(shí)驗(yàn) 大振幅耦合運(yùn)動(dòng) 非定�？諝鈩�(dòng)力 外插 遲滯特性　出處：《南京航空航天大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：本文在NH-2低速風(fēng)洞中對(duì)某背景機(jī)標(biāo)模進(jìn)行了大振幅運(yùn)動(dòng)動(dòng)態(tài)實(shí)驗(yàn),實(shí)驗(yàn)測(cè)量了該模型單自由度俯仰運(yùn)動(dòng)、俯仰滾轉(zhuǎn)耦合運(yùn)動(dòng)、不同支撐攻角下的單自由度滾轉(zhuǎn)運(yùn)動(dòng)以及50°支撐攻角下橫向耦合運(yùn)動(dòng)時(shí)的非定常氣動(dòng)力,分析了上述各種運(yùn)動(dòng)下該模型的非定常氣動(dòng)特性。采用模型動(dòng)態(tài)運(yùn)動(dòng)風(fēng)洞試驗(yàn)結(jié)果作為樣本數(shù)據(jù),提出了基于攻角變化的??縱向氣動(dòng)模型和基于側(cè)滑角變化的?橫向氣動(dòng)模型,分析了該模型的“外插”特性,提出了一種線性“外插”的方法,并通過經(jīng)典的風(fēng)洞試驗(yàn)數(shù)據(jù)進(jìn)行了驗(yàn)證。在此基礎(chǔ)上完善了建模方法,完成了背景機(jī)標(biāo)模的縱向運(yùn)動(dòng)和橫向運(yùn)動(dòng)非定常氣動(dòng)力數(shù)學(xué)模型。采用上述非定常氣動(dòng)力數(shù)學(xué)模型,基于單自由度滾轉(zhuǎn)運(yùn)動(dòng)的樣本數(shù)據(jù),計(jì)算了俯仰滾轉(zhuǎn)耦合運(yùn)動(dòng)時(shí)的橫向非定常氣動(dòng)力;基于單自由度俯仰運(yùn)動(dòng)的樣本數(shù)據(jù),計(jì)算了俯仰滾轉(zhuǎn)耦合運(yùn)動(dòng)的縱向非定常氣動(dòng)力;基于偏航滾轉(zhuǎn)耦合運(yùn)動(dòng)的樣本數(shù)據(jù),計(jì)算了旋轉(zhuǎn)流場(chǎng)下單自由度偏航運(yùn)動(dòng)和滾轉(zhuǎn)運(yùn)動(dòng)的非定常氣動(dòng)力。計(jì)算結(jié)果表明與試驗(yàn)結(jié)果吻合較好,驗(yàn)證了數(shù)學(xué)模型的準(zhǔn)確性。
[Abstract]:In this paper, the large amplitude motion dynamic experiment of a background machine model is carried out in NH-2 low speed wind tunnel. The single degree of freedom pitch motion and pitch roll coupling motion of the model are measured experimentally. The unsteady aerodynamic force of the single degree of freedom rolling motion at different angles of attack and the transverse coupled motion at 50 擄supporting angle of attack, The unsteady aerodynamic characteristics of the model under the above motions are analyzed. The dynamic motion wind tunnel test results of the model are used as the sample data, and the change of attack angle is proposed. ? Longitudinal aerodynamic model and based on lateral slip angle variation? In this paper, the "extrapolation" characteristic of the model is analyzed, and a linear "extrapolation" method is proposed, which is verified by classical wind tunnel test data. In this paper, the unsteady aerodynamic mathematical models of longitudinal and transverse motion of the background machine model are completed. The above unsteady aerodynamic mathematical model is adopted, and the sample data of the rolling motion of single degree of freedom are used. The transverse unsteady aerodynamic force of the pitching roll coupled motion is calculated, the longitudinal unsteady aerodynamic force of the pitch roll coupled motion is calculated based on the sample data of the single degree of freedom pitch motion, and the sample data of the yaw roll coupled motion are calculated. The unsteady aerodynamic forces of yaw motion and rolling motion of degree of freedom issued by rotating flow field are calculated. The results show that the results are in good agreement with the experimental results and the accuracy of the mathematical model is verified.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V211.74

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本文編號(hào)：1494798