本文關(guān)鍵詞：復(fù)合式飛行器前飛狀態(tài)氣動干擾特性分析　出處：《吉林大學》2016年碩士論文　論文類型：學位論文

  更多相關(guān)文章： 推進涵道 固定翼 涵道螺旋槳 氣動特性 復(fù)合式飛行器

【摘要】：共軸反槳直升機在前飛時既要保持升力,同時又要提供前行所需要的推力。則上下旋翼的間距勢必要增加,旋翼的轉(zhuǎn)動平面也會有所前傾導致一側(cè)間距大而一側(cè)間距小,間距比較小的一側(cè)容易產(chǎn)生因揮舞嚴重而導致的碰撞問題,同時也會增加動力系統(tǒng)的功率損耗。因此本文提出加裝兩個尾部推進涵道配合前置短翼以平衡機身的復(fù)合式氣動布局方案。提出采用兩個尾部推進涵道來提供前飛推力,為保持機身的整體平衡在機身前部加裝短翼,同時又可提供輔助升力,這樣一來主旋翼只需要產(chǎn)生升力,避免了碰撞危險的發(fā)生達減小了發(fā)動機的功耗。首先對該無人機的整體氣動布局進行描述,繪制主要結(jié)構(gòu)三維SolidWorks模型,對具體參數(shù)進行計算。然后對尾部推進涵道以及前置短翼進行理論分析,為后文分析推進涵道的氣動特性奠定理論基礎(chǔ),分析機翼產(chǎn)生升力的原理。在對尾部推進涵道的理論基礎(chǔ)之上結(jié)合CFD仿真分析方法對涵道風扇的推力特性進行分析,分析得出不同變量以及不同螺旋槳環(huán)境對其氣動特性的影響。運用CFD仿真方法分析機翼對尾部推進涵道在前飛時的氣動干擾特性,對機翼流場特性分析得出機翼翼尖部分在前飛時會產(chǎn)生漩渦。通過改變不同涵道安裝位置得出,翼尖的漩渦進入涵道風扇的位置也會有所不同。針對這種現(xiàn)象分別分析不同涵道安裝位置時推進涵道的氣動特性,并與不受短翼影響時的氣動特性做分析對比。結(jié)果表明這種雙尾部推進涵道配合前置短翼的氣動布局不但會為無人機提供前飛的推力,同時涵道風扇的氣動特性不會受到翼尖漩渦的影響,證明了此布局的合理性。
[Abstract]:The coaxial reverse propeller helicopter must maintain the lift and provide the thrust required for the forward flight, and the distance between the upper and lower rotor is bound to increase. The rotating plane of the rotor will also have a forward tilt, which will lead to a large distance between one side and a small distance. The side with small spacing will easily cause a collision problem caused by serious flapping. At the same time, the power loss of the power system will be increased. Therefore, this paper proposes a compound aerodynamic layout with two rear propulsion ducts to balance the fuselage and two rear propulsion ducts to provide the front. Flying thrust. In order to maintain the overall balance of the fuselage, a short wing is installed at the front of the fuselage, while at the same time providing auxiliary lift, so that the main rotor only needs to produce lift. The collision hazard is avoided and the power consumption of the engine is reduced. Firstly, the overall aerodynamic layout of the UAV is described, and the 3D SolidWorks model of the main structure is drawn. The specific parameters are calculated. Then the rear propulsion ducts and the front wing are theoretically analyzed, which lays a theoretical foundation for the later analysis of the aerodynamic characteristics of the propulsion ducts. Based on the theory of rear propulsion ducts, the thrust characteristics of ducted fans are analyzed by CFD simulation. The effects of different variables and different propeller environments on its aerodynamic characteristics are obtained. The aerodynamic interference characteristics of the wing to the rear propulsion ducts are analyzed by using CFD simulation method. By analyzing the flow field characteristics of the wing, it is found that the wing tip will produce swirl in the forward flight, which is obtained by changing the installation position of the different ducts. According to this phenomenon, the aerodynamic characteristics of propulsion ducts with different culvert installation positions are analyzed respectively. Compared with the aerodynamic characteristics of the UAV without the influence of the short wing, the results show that the double tail propulsion ducts and the front short wing will not only provide the forward thrust for the UAV. At the same time, the aerodynamic characteristics of the culvert fan are not affected by the wingtip vortex, which proves the rationality of the layout.
【學位授予單位】：吉林大學
【學位級別】：碩士
【學位授予年份】：2016
【分類號】：V211

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