【摘要】：直升機(jī)旋翼轉(zhuǎn)速的變化將對(duì)直升機(jī)的飛行性能和動(dòng)力學(xué)特性產(chǎn)生重要的影響。為了提高直升機(jī)的性能,旋翼轉(zhuǎn)速優(yōu)化的應(yīng)用是當(dāng)前國(guó)內(nèi)外的一個(gè)研究熱點(diǎn)。通過(guò)理論分析表明,合理地改變直升機(jī)旋翼的轉(zhuǎn)速,可以有效地降低直升機(jī)工作過(guò)程中的需用功率。而旋翼轉(zhuǎn)速的改變,會(huì)極大地增加旋翼結(jié)構(gòu)動(dòng)力學(xué)的復(fù)雜程度,這將對(duì)旋翼槳葉和槳轂的設(shè)計(jì)提出更高的要求。本文探索了變轉(zhuǎn)速剛性旋翼系統(tǒng)的結(jié)構(gòu)設(shè)計(jì),設(shè)計(jì)了具有高剛度、輕質(zhì)量的模型槳葉,以及剛性無(wú)鉸式模型槳轂。模型槳葉采用變翼型、變弦長(zhǎng)、帶負(fù)扭,帶尖削的幾何外形,內(nèi)部結(jié)構(gòu)設(shè)計(jì)采用了碳纖維加玻璃纖維蒙皮、碳纖維“C型”大梁、碳纖維后緣條等構(gòu)型。無(wú)鉸式剛性旋翼槳轂以槳轂中央件承受離心力載荷和彎矩載荷,并設(shè)計(jì)了槳轂柔性片來(lái)增加槳轂揮舞方向的彎曲剛度,并對(duì)模型旋翼系統(tǒng)進(jìn)行了強(qiáng)度、剛度的校核,進(jìn)行優(yōu)化設(shè)計(jì)。最后將模型旋翼加工出來(lái)以進(jìn)行變轉(zhuǎn)速剛性旋翼性能及振動(dòng)載荷試驗(yàn)研究。本文開(kāi)展了多風(fēng)速、多轉(zhuǎn)速、多拉力載荷的風(fēng)洞試驗(yàn)。通過(guò)六分量天平和應(yīng)變片測(cè)量了模型旋翼的槳轂載荷以及小拉桿、柔性片上的載荷,并結(jié)合理論知識(shí)對(duì)試驗(yàn)中測(cè)量載荷的變化規(guī)律進(jìn)行了分析。此外,本文通過(guò)旋翼氣彈綜合模型,分析了旋翼模型槳葉的剖面載荷,分析其規(guī)律,為變轉(zhuǎn)速剛性旋翼振動(dòng)載荷的進(jìn)一步研究打下基礎(chǔ)。
[Abstract]:The change of helicopter rotor speed will have an important impact on the helicopter flight performance and dynamic characteristics. In order to improve the performance of helicopter, rotor speed optimization is a research hotspot at home and abroad. The theoretical analysis shows that changing the rotor speed reasonably can effectively reduce the required power in the helicopter working process. The change of rotor speed will greatly increase the complexity of rotor structure dynamics, which will put forward higher requirements for the design of rotor blade and hub. In this paper, the structural design of the rigid rotor system with variable rotational speed is explored. The model blades with high stiffness and light mass are designed, and the rigid non-hinged model propeller hub is designed. The model blade adopts the geometric shape of variable airfoil, variable chord length, negative torsion and sharp cutting. The internal structure is designed with carbon fiber with glass fiber skin, carbon fiber "C" beam, carbon fiber rear edge strip and so on. Non-hinged rigid rotor hub is subjected to centrifugal load and bending moment load with the center of the hub. The flexible blade of the hub is designed to increase the bending stiffness in the swing direction of the hub, and the strength and stiffness of the model rotor system are checked. Optimize the design. Finally, the model rotor is machined to study the performance and vibration load of the rigid rotor with variable rotational speed. In this paper, wind tunnel tests with multi wind speed, multi-speed and multi-tension load are carried out. The load on the propeller hub of the model rotor and the load on the small rod and flexible sheet were measured by the six-component balance and strain gauge. The variation of the measured load in the experiment was analyzed by combining the theoretical knowledge. In addition, based on the aero-elastic model of rotor, the profile load of rotor blade is analyzed and its law is analyzed, which lays a foundation for further research on vibration load of rigid rotor with variable rotational speed.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V275.1

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本文編號(hào)：2389884