【摘要】：為了探尋變后掠翼飛行器最佳后掠角的變化規(guī)律,基于計算流體力學計算技術(shù),對變后掠翼身組合體進行了氣動計算,結(jié)合遺傳算法對計算結(jié)果進行全局尋優(yōu),探索最優(yōu)變后掠規(guī)律。首先基于變后掠飛行器設(shè)計的要求與方法,建立了"旋轉(zhuǎn)式"變后掠翼身組合體三維模型;其次通過在寬廣速域繞流流場的CFD數(shù)值模擬,得到了氣動數(shù)據(jù);最后結(jié)合遺傳算法對氣動數(shù)據(jù)進行全局尋優(yōu),得出了升阻比最佳的后掠角變化規(guī)律。仿真結(jié)果表明,采用遺傳算法對變后掠飛機最佳后掠角進行全局尋優(yōu),可以得到合理的最佳后掠角變化規(guī)律曲線:在亞聲速速域內(nèi)隨著速度的增大,為了降低誘導阻力,提高升阻比,最優(yōu)后掠角平緩增大;在跨聲速速域內(nèi),為了延緩激波阻力的形成,最優(yōu)后掠角急劇上升。
[Abstract]:In order to find out the change rule of the optimal sweep angle of VRP, based on the computational fluid dynamics (CFD) calculation technology, the aerodynamic calculation of the VRP wing assembly is carried out, and the global optimization of the calculation result is carried out by combining the genetic algorithm (GA). To explore the optimal law of backward sweep. Firstly, based on the design requirements and methods of VRP, a three-dimensional model of "rotary" variable swept wing is established, and then the aerodynamic data are obtained by CFD numerical simulation of the flow field around a wide speed range. Finally, the global optimization of aerodynamic data is carried out with genetic algorithm, and the rule of skimming angle with the best lift-to-drag ratio is obtained. The simulation results show that the optimal sweep angle curve can be obtained by using genetic algorithm for global optimization of the optimal sweep angle of a variable swept aircraft. In order to reduce the induced resistance, the optimal sweep angle curve can be obtained in the subsonic velocity domain with the increase of velocity. In order to delay the formation of shock resistance, the optimal back sweep angle rises sharply in the transonic velocity domain with the increase of lift-to-drag ratio.
【作者單位】： 上海航空測控技術(shù)研究所故障診斷與健康管理技術(shù)航空科技重點實驗室;西安航空學院飛行器學院;
【基金】：航空科學基金資助(2011ZA56001)
【分類號】：V211.41

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