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

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

【摘要】：共軸反槳直升機(jī)在前飛時(shí)既要保持升力,同時(shí)又要提供前行所需要的推力。則上下旋翼的間距勢(shì)必要增加,旋翼的轉(zhuǎn)動(dòng)平面也會(huì)有所前傾導(dǎo)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(yán)重而導(dǎo)致的碰撞問(wèn)題,同時(shí)也會(huì)增加動(dòng)力系統(tǒng)的功率損耗。因此本文提出加裝兩個(gè)尾部推進(jìn)涵道配合前置短翼以平衡機(jī)身的復(fù)合式氣動(dòng)布局方案。提出采用兩個(gè)尾部推進(jìn)涵道來(lái)提供前飛推力,為保持機(jī)身的整體平衡在機(jī)身前部加裝短翼,同時(shí)又可提供輔助升力,這樣一來(lái)主旋翼只需要產(chǎn)生升力,避免了碰撞危險(xiǎn)的發(fā)生達(dá)減小了發(fā)動(dòng)機(jī)的功耗。首先對(duì)該無(wú)人機(jī)的整體氣動(dòng)布局進(jìn)行描述,繪制主要結(jié)構(gòu)三維SolidWorks模型,對(duì)具體參數(shù)進(jìn)行計(jì)算。然后對(duì)尾部推進(jìn)涵道以及前置短翼進(jìn)行理論分析,為后文分析推進(jìn)涵道的氣動(dòng)特性奠定理論基礎(chǔ),分析機(jī)翼產(chǎn)生升力的原理。在對(duì)尾部推進(jìn)涵道的理論基礎(chǔ)之上結(jié)合CFD仿真分析方法對(duì)涵道風(fēng)扇的推力特性進(jìn)行分析,分析得出不同變量以及不同螺旋槳環(huán)境對(duì)其氣動(dòng)特性的影響。運(yùn)用CFD仿真方法分析機(jī)翼對(duì)尾部推進(jìn)涵道在前飛時(shí)的氣動(dòng)干擾特性,對(duì)機(jī)翼流場(chǎng)特性分析得出機(jī)翼翼尖部分在前飛時(shí)會(huì)產(chǎn)生漩渦。通過(guò)改變不同涵道安裝位置得出,翼尖的漩渦進(jìn)入涵道風(fēng)扇的位置也會(huì)有所不同。針對(duì)這種現(xiàn)象分別分析不同涵道安裝位置時(shí)推進(jìn)涵道的氣動(dòng)特性,并與不受短翼影響時(shí)的氣動(dòng)特性做分析對(duì)比。結(jié)果表明這種雙尾部推進(jìn)涵道配合前置短翼的氣動(dòng)布局不但會(huì)為無(wú)人機(jī)提供前飛的推力,同時(shí)涵道風(fēng)扇的氣動(dòng)特性不會(huì)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(xué)位授予單位】：吉林大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類(lèi)號(hào)】：V211

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