桨根弹性约束刚度对直升机飞行动力学特性的影响

发布时间：2018-01-08 09:25

  本文关键词：桨根弹性约束刚度对直升机飞行动力学特性的影响　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

  更多相关文章： 直升机 旋翼动力学 飞行动力学 飞行品质 桨根弹性支承件 弹性约束刚度

【摘要】：“翼扇涵体”无人直升机是一种新构型飞行器,其升力系统由“跷跷板”式旋翼和涵道风扇上下共轴布置构成。由于“跷跷板”式旋翼操纵功效不足,所以在旋翼桨叶根部加装一弹性支承件来增加操纵功效,并开展了桨叶根部弹性约束刚度对直升机飞行动力学特性和飞行品质影响的分析研究,对桨根弹性支承件的主要参数进行了设计。首先将桨根弹性支承件简化成一铰链弹簧,建立旋翼动力学模型。同时建立旋翼、涵道风扇、机身气动力模型,并完成全机飞行动力学建模。以桨根加装了弹性支承件和未加装弹性支承件的“翼扇涵体”无人直升机为例,计算了两者的配平特性、稳定性和操纵响应,并据此比较分析了桨根弹性约束刚度对直升机配平特性、稳定性和操纵响应的影响。其次基于美国陆军航空设计标准ADS-33E-PRF,并结合无人直升机的飞行操纵特点,对稳定性、操纵性和轴间耦合的内容做了适用性剪裁。以桨根加装了弹性支承件和未加装弹性支承件的样例直升机为例,计算了两者的飞行品质参数,并据此比较分析了桨根弹性约束刚度对直升机飞行品质的影响。最后在前面工作的基础上,以桨根加装了弹性支承件的样例直升机为例,计算不同弹性约束刚度下的配平特性和飞行品质参数,结合飞行品质评价方法,做各方面的妥协和折衷,找到了使样例直升机飞行品质达到最佳状态所需的弹性支承件等效刚度值。弹性支承件选用橡胶材料,利用有限元分析软件ANSYS对其计算分析,找出了与最佳等效刚度值相对应的橡胶件硬度。
[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.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V275.1
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本文编号：1396543