本文關(guān)鍵詞：槳根彈性約束剛度對(duì)直升機(jī)飛行動(dòng)力學(xué)特性的影響　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 直升機(jī) 旋翼動(dòng)力學(xué) 飛行動(dòng)力學(xué) 飛行品質(zhì) 槳根彈性支承件 彈性約束剛度

【摘要】：“翼扇涵體”無(wú)人直升機(jī)是一種新構(gòu)型飛行器,其升力系統(tǒng)由“蹺蹺板”式旋翼和涵道風(fēng)扇上下共軸布置構(gòu)成。由于“蹺蹺板”式旋翼操縱功效不足,所以在旋翼槳葉根部加裝一彈性支承件來(lái)增加操縱功效,并開(kāi)展了槳葉根部彈性約束剛度對(duì)直升機(jī)飛行動(dòng)力學(xué)特性和飛行品質(zhì)影響的分析研究,對(duì)槳根彈性支承件的主要參數(shù)進(jìn)行了設(shè)計(jì)。首先將槳根彈性支承件簡(jiǎn)化成一鉸鏈彈簧,建立旋翼動(dòng)力學(xué)模型。同時(shí)建立旋翼、涵道風(fēng)扇、機(jī)身氣動(dòng)力模型,并完成全機(jī)飛行動(dòng)力學(xué)建模。以槳根加裝了彈性支承件和未加裝彈性支承件的“翼扇涵體”無(wú)人直升機(jī)為例,計(jì)算了兩者的配平特性、穩(wěn)定性和操縱響應(yīng),并據(jù)此比較分析了槳根彈性約束剛度對(duì)直升機(jī)配平特性、穩(wěn)定性和操縱響應(yīng)的影響。其次基于美國(guó)陸軍航空設(shè)計(jì)標(biāo)準(zhǔn)ADS-33E-PRF,并結(jié)合無(wú)人直升機(jī)的飛行操縱特點(diǎn),對(duì)穩(wěn)定性、操縱性和軸間耦合的內(nèi)容做了適用性剪裁。以槳根加裝了彈性支承件和未加裝彈性支承件的樣例直升機(jī)為例,計(jì)算了兩者的飛行品質(zhì)參數(shù),并據(jù)此比較分析了槳根彈性約束剛度對(duì)直升機(jī)飛行品質(zhì)的影響。最后在前面工作的基礎(chǔ)上,以槳根加裝了彈性支承件的樣例直升機(jī)為例,計(jì)算不同彈性約束剛度下的配平特性和飛行品質(zhì)參數(shù),結(jié)合飛行品質(zhì)評(píng)價(jià)方法,做各方面的妥協(xié)和折衷,找到了使樣例直升機(jī)飛行品質(zhì)達(dá)到最佳狀態(tài)所需的彈性支承件等效剛度值。彈性支承件選用橡膠材料,利用有限元分析軟件ANSYS對(duì)其計(jì)算分析,找出了與最佳等效剛度值相對(duì)應(yīng)的橡膠件硬度。
[Abstract]:The "wing fan culvert" unmanned helicopter is a new configuration aircraft, its lift system is composed of "seesaw" rotor and culvert fan up and down coaxial arrangement. Therefore, an elastic support is added to the root of rotor blade to increase the maneuverability, and the influence of elastic restraint stiffness on the flight dynamics and flight quality of helicopter is analyzed and studied. The main parameters of the elastic support of propeller root are designed. Firstly, the elastic support of propeller root is simplified into a hinge spring, and the dynamic model of rotor is established. At the same time, the aerodynamic model of rotor, culvert fan and fuselage is established. The flight dynamics modeling of the whole aircraft is completed. Taking the "wing fan culvert" unmanned helicopter with elastic support and without elastic support as an example, the leveling characteristics, stability and control response of the two helicopter are calculated. Based on this, the effects of elastic restraint stiffness of propeller root on the flattening characteristics, stability and maneuvering response of the helicopter are compared and analyzed. Secondly, it is based on the US Army Aviation Design Standard (ADS-33E-PRF). Combined with the flight control characteristics of unmanned helicopter, the applicability of stability, maneuverability and coupling between axes is tailored. The flight quality parameters of the two systems are calculated, and the effects of the elastic restraint stiffness of the propeller root on the flight quality of the helicopter are compared and analyzed. Finally, based on the previous work. Taking the sample helicopter with elastic support as an example, the flattening characteristics and flight quality parameters under different elastic restraint stiffness are calculated. Combined with the method of flight quality evaluation, compromises and compromises are made in all aspects. The equivalent stiffness of the elastic support is found to be needed to make the flight quality of the sample helicopter reach the best condition. The rubber material is selected for the elastic support and the finite element analysis software ANSYS is used to calculate and analyze it. The hardness of rubber parts corresponding to the optimum equivalent stiffness is found out.
【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)：1396543