本文選題：變結(jié)構(gòu) + 無人飛行器�。� 參考：《機(jī)械設(shè)計與制造》2016年04期

【摘要】：針對現(xiàn)有的四旋翼直升機(jī)存在飛行速度低、航程短等問題,綜合考慮了四旋翼可以垂直起降和固定翼能夠長距離航行的特點(diǎn),提出一種在四旋翼的基礎(chǔ)上添加一對固定翼和渦扇推力電機(jī)的變結(jié)構(gòu)無人飛行器,并給出三維建模;在水平飛行時機(jī)身兩側(cè)的雙涵道渦扇和機(jī)翼共同向前傾斜以產(chǎn)生向后的推力和向上的升力。開發(fā)出該變結(jié)構(gòu)無人飛行器樣機(jī),對飛行器固定翼進(jìn)行流固耦合力學(xué)仿真分析,最后對變結(jié)構(gòu)飛行器動力學(xué)建模。固定翼的單向流固耦合計算結(jié)果顯示,設(shè)計的機(jī)翼升力滿足設(shè)計要求。從截面翼型位置上分析有一定意義,證明最大應(yīng)力并非在翼型的前緣或后緣,而是在上表面,同時也驗證了CLARK Y翼面形狀產(chǎn)生的升力在飛行過程中起主要作用。
[Abstract]:In view of the problems of low flying speed and short range of the existing four-rotor helicopter, the characteristics of the four-rotor can take off and land vertically and the fixed-wing can navigate long distance are considered comprehensively. A variable structure unmanned aerial vehicle (UAV) with a pair of fixed wings and a turbofan thrust motor is proposed on the basis of four rotors, and the 3D modeling is given. In horizontal flight, the double ducted vortex fan and the wing both sides of the fuselage incline forward to generate backward thrust and upward lift. The prototype of the variable structure unmanned aerial vehicle (UAV) is developed, and the fluid-solid coupling mechanics of the fixed wing of the vehicle is simulated and analyzed. Finally, the dynamic model of the variable structure unmanned aerial vehicle is established. The results of unidirectional fluid-solid coupling of the fixed wing show that the lift of the designed wing meets the design requirements. It is significant to analyze the position of the section airfoil. It is proved that the maximum stress is not on the front edge or the rear edge of the airfoil, but on the upper surface. It is also proved that the lift generated by the shape of the CLARK Y wing plays a major role in the flight process.
【作者單位】： 安徽理工大學(xué)機(jī)械工程學(xué)院;中國科學(xué)院合肥智能機(jī)械研究所;中國科學(xué)技術(shù)大學(xué)自動化系;
【基金】：國家自然科學(xué)基金資助項目(61340016)
【分類號】：V279

【相似文獻(xiàn)】

相關(guān)期刊論文 前10條

1 曹義華;旋翼渦尾流與下洗流場的計算方法[J];北京航空航天大學(xué)學(xué)報;2000年02期

2 李新民;劉正江;;在旋翼試驗中實現(xiàn)同方位采集數(shù)據(jù)的方法[J];直升機(jī)技術(shù);2002年02期

3 陳維芹,徐國華,梅衛(wèi)勝;懸停狀態(tài)直升機(jī)剪刀式旋翼的試驗研究[J];流體力學(xué)實驗與測量;2002年01期

4 高亞東,張曾，

本文編號：1834187