本文關鍵詞：槳根彈性約束剛度對直升機飛行動力學特性的影響　出處：《南京航空航天大學》2016年碩士論文　論文類型：學位論文

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

【摘要】：“翼扇涵體”無人直升機是一種新構型飛行器,其升力系統(tǒng)由“蹺蹺板”式旋翼和涵道風扇上下共軸布置構成。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增加操縱功效,并開展了槳葉根部彈性約束剛度對直升機飛行動力學特性和飛行品質(zhì)影響的分析研究,對槳根彈性支承件的主要參數(shù)進行了設計。首先將槳根彈性支承件簡化成一鉸鏈彈簧,建立旋翼動力學模型。同時建立旋翼、涵道風扇、機身氣動力模型,并完成全機飛行動力學建模。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”無人直升機為例,計算了兩者的配平特性、穩(wěn)定性和操縱響應,并據(jù)此比較分析了槳根彈性約束剛度對直升機配平特性、穩(wěn)定性和操縱響應的影響。其次基于美國陸軍航空設計標準ADS-33E-PRF,并結合無人直升機的飛行操縱特點,對穩(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為例,計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直升機飛行品質(zhì)的影響。最后在前面工作的基礎上,以槳根加裝了彈性支承件的樣例直升機為例,計算不同彈性約束剛度下的配平特性和飛行品質(zhì)參數(shù),結合飛行品質(zhì)評價方法,做各方面的妥協(xié)和折衷,找到了使樣例直升機飛行品質(zhì)達到最佳狀態(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對其計算分析,找出了與最佳等效剛度值相對應的橡膠件硬度。
[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.
【學位授予單位】：南京航空航天大學
【學位級別】：碩士
【學位授予年份】：2016
【分類號】：V275.1
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本文編號：1396543