本文關鍵詞：大展弦比機翼氣動彈性分析　出處：《沈陽航空航天大學》2017年碩士論文　論文類型：學位論文

  更多相關文章： 大展弦比 氣彈扭轉(zhuǎn) 大變形 顫振 靜氣彈發(fā)散

【摘要】：本文以大展弦比機翼為研究對象,對機翼靜氣動彈性和顫振進行了分析,同時研究了大變形對機翼顫振特性的影響。首先,基于經(jīng)典升力線理論,通過求解力矩平衡方程,計算了大展弦比小后掠角的兩種機翼的靜氣彈扭轉(zhuǎn):一是對展向結構參數(shù)不變的矩形翼,通過直接求解平衡方程,得到了不同飛行條件下機翼的扭轉(zhuǎn)角分布;二是對展向參數(shù)變化的梯形翼利用伽遼金法進行求解。該方法可以為機翼初步設計中結構參數(shù)的確定提供參考。其次,按照質(zhì)量、剛度等效原則,建立了某型無人機機翼零平衡位置下的結構有限元模型,通過加載極限飛行載荷,得到了機翼非零平衡位置下的結構模型。對兩平衡位置下的機翼結構進行動力學特性分析,通過比較發(fā)現(xiàn),由于大變形,機翼的各階固有頻率相應降低,而且提前出現(xiàn)耦合振型。最后,利用MSC Nastran進行了無人機機翼顫振特性及靜氣彈發(fā)散速度的計算。顫振分析選用PK法,以動力學分析結果為基礎,計算了不同條件下機翼的顫振速度和顫振頻率。對零平衡位置下的機翼氣動力模型進行了不同升力面劃分,比較顫振分析結果,發(fā)現(xiàn)舵面間隙對機翼顫振速度產(chǎn)生了較大影響;對零平衡位置和非零平衡位置下的機翼進行顫振分析,比較發(fā)現(xiàn)結構大變形導致了機翼顫振速度和顫振頻率降低。靜氣彈分析以顫振分析模型為基礎,利用顫振法對機翼進行了發(fā)散速度計算。
[Abstract]:In this paper, the static Aeroelasticity and flutter of the wing with high aspect ratio are analyzed, and the influence of large deformation on the flutter characteristics of the wing is studied. Firstly, based on the classical lift line theory. By solving the moment balance equation, the hydrostatic elastic torsion of two kinds of wing with large aspect ratio and small sweep angle is calculated. One is the rectangular wing with invariable span structural parameters, and the equilibrium equation is solved directly. The distribution of the wing torsion angle is obtained under different flight conditions. Second, the trapezoidal wing with varying span parameters is solved by Galerkin method, which can provide a reference for the determination of structural parameters in the preliminary design of the wing. Secondly, according to the principle of mass and stiffness equivalence. The finite element model of a certain UAV wing with zero balance position is established, and the ultimate flight load is loaded. The structural model of the wing in non-zero equilibrium position is obtained. The dynamic characteristics of the wing structure in the two equilibrium positions are analyzed. It is found that the natural frequencies of each order of the wing are reduced due to the large deformation. Finally, MSC Nastran is used to calculate the flutter characteristics of UAV wing and the divergence velocity of aerostatic missile. The competition method is used for flutter analysis. Based on the dynamic analysis results, the flutter velocity and flutter frequency of the wing under different conditions are calculated. The aerodynamic model of the wing at zero equilibrium position is divided into different lift surfaces, and the flutter analysis results are compared. It is found that the rudder clearance has a great influence on the flutter velocity of the wing. The flutter analysis of the wing at zero balance position and non-zero balance position shows that the large deformation of the structure results in the reduction of the flutter velocity and flutter frequency of the wing. The hydrostatic elastic analysis is based on the flutter analysis model. The divergence velocity of the wing was calculated by flutter method.
【學位授予單位】：沈陽航空航天大學
【學位級別】：碩士
【學位授予年份】：2017
【分類號】：V211.47

【相似文獻】

相關期刊論文 前10條

1 丁千,王冬立;結構和氣動非線性機翼顫振分析[J];動力學與控制學報;2004年03期

2 謝長川;胡薇薇;楊超;;顫振分析中的特征值排序問題[J];數(shù)學的實踐與認識;2007年18期

3 楊智春;谷迎松;;應用H_∞-范數(shù)的頻域顫振分析[J];控制理論與應用;2009年06期

4 陳q，

本文編號：1427464