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太陽(yáng)能無(wú)人機機翼顫振動(dòng)力學(xué)建模與分析
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成都飛機工業(yè)集團有限責任公司

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V215.34

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Aeroelastic Modeling and Flutter Analysis of Solar UAV Wings
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    摘要:

    太陽(yáng)能無(wú)人機作為一種大展弦比輕質(zhì)飛行器,其機翼的氣動(dòng)彈性效應顯著(zhù),其中顫振問(wèn)題尤為關(guān)鍵。此類(lèi)飛機具有大尺寸和低剛度特點(diǎn),通過(guò)風(fēng)洞試驗研究機翼顫振問(wèn)題,成本高而且難度大,難以實(shí)現,因此仿真計算是分析此類(lèi)飛機顫振問(wèn)題的主要手段。針對國內某翼展為40米的太陽(yáng)能無(wú)人機大展弦比機翼,首先對機翼有限元模型進(jìn)行工程化處理,在此基礎上開(kāi)展結構動(dòng)力學(xué)分析和顫振計算,重點(diǎn)計算了機翼上不同吊艙布置下的顫振速度。經(jīng)過(guò)仿真計算,得到該太陽(yáng)能無(wú)人機機翼顫振速度為26m/s, 滿(mǎn)足設計要求,進(jìn)一步分析表明,可以通過(guò)增加發(fā)動(dòng)機連桿的長(cháng)度、在發(fā)動(dòng)機上增加配重以及改變吊艙在機翼上的展向站位等手段來(lái)提高此無(wú)人機的顫振速度。

    Abstract:

    Solar-powered UAV is a lightweight aircraft with high aspect ratio, and its wing has significant aeroelastic effect, especially flutter. This kind of aircraft has the characteristics of large size and low stiffness. It is costly and difficult to realize to study wing flutter through wind tunnel test. Therefore, simulation calculation is the main means to analyze the flutter problem of this kind of aircraft. Aiming at the high aspect ratio wing of a solar UAV with wingspan of 40 meters, the finite element model of the wing was firstly treated by engineering. On this basis, the structural dynamics analysis and flutter calculation were carried out, and the flutter velocity under different pod arrangements on the wing was mainly calculated. The simulation results show that the flutter speed of the solar UAV wing is 26m/s, which meets the design requirements. Further analysis shows that the flutter speed of the UAV can be improved by increasing the length of the engine connecting rod, increasing the counterweight on the engine and changing the spanwise position of the pod on the wing.

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冒森,張斌,肖良華,陳斌,王玨.太陽(yáng)能無(wú)人機機翼顫振動(dòng)力學(xué)建模與分析計算機測量與控制[J].,2023,31(9):183-189.

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歷史
  • 收稿日期:2023-02-19
  • 最后修改日期:2023-06-14
  • 錄用日期:2023-04-04
  • 在線(xiàn)發(fā)布日期: 2023-09-18
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