【作者】 刘佳；

【导师】 朱清华；

【作者基本信息】 南京航空航天大学 ， 飞行器设计， 2022， 硕士

【摘要】 为了提高水平飞行速度,两侧带有辅助推力装置的复合式直升机近年来成为了直升机发展的热点方向,而常规复合式直升机一般采用降转速的过渡方式由低速飞行向飞行过渡。本文提出了一种旋翼由驱转状态变为自转状态的过渡方式,并对自转复合式直升机总体及飞行特性开展了研究。首先,本文设计了一款100kg级样机,并对该构型飞行器的各系统进行了总体初步设计,提出了一套可行的总体设计方案。并在后文以此为基础进行分析。根据复合式直升机的特点,建立了各部件气动力模型,然后采用数值仿真分析的方式对全机干扰特性进行了分析计算,在气动力模型上添加了干扰模型。最终建立了准确性较高的飞行动力学方程,为后续进行全机的平衡计算奠定了基础。针对本文提出的驱转-自转平滑过渡,本文对自转状态的旋翼进行分析,确定了过渡模式的速度范围,对不同扭度的旋翼特性进行了对比,从功率匹配、升力和桨盘迎角匹配的角度进行了详细分析,证明旋翼由驱转到自转可以平滑过渡。针对复合式直升机存在操纵冗余的问题,本文建立了复合式直升机的操纵混合模型,有效减少了冗余操纵量。并以此为基础对全飞行阶段进行了平衡计算和稳定性分析,确定了其在飞行过程中各操纵量和姿态量的变化情况和稳定性特点。最后,基于配平,对本文样机的基本性能进行了计算。并且对采用降转速过渡方式和采用自转过渡方式的复合式直升机的飞行性能进行了对比分析。发现自转复合式直升机不仅可以进行前飞,且由于采用自转过渡的复合式直升机降低了旋翼需用功率,其最大飞行速度可以进一步增加。更多还原

【Abstract】 In order to increase the level of speed,the compound helicopter with auxiliary thrust devices on both sides has been a hot spot in the development of helicopters in recent years.Conventional compound helicopters generally adopt a transition mode of reduced speed from low-speed flight to flight.A transition method is proposed for the rotor to change from the drive state to the autorotation state,and the overall and flight characteristics of the autorotation compound helicopter are studied.First of all,this paper designs a 100 kg compound helicopter,and conducts an overall preliminary design of each system of the configuration aircraft,and proposes a set of feasible overall design schemes.And analyze it on this basis later.According to the characteristics of the compound helicopter,the aerodynamic model of each component is established,and then the interference characteristics of the whole aircraft are analyzed and calculated by means of CFD,and the interference model is added to the aerodynamic model.Finally,a highly accurate flight dynamics equation was established,which laid the foundation for the subsequent balance calculations of the entire aircraft.In view of the smooth transition between drive rotor and autorotating rotor proposed in this paper,this paper analyzes the rotor in the autorotating state,determines the speed range of the transition state,and analyzes the characteristics of the rotor with different torsion.In contrast,a detailed analysis was carried out from the perspective of power matching,lift and paddle angle of attack,and it was found that the rotor can be smoothly transitioned from drive rotor to autorotating rotor.In view of the redundant control problem of the compound helicopter,this paper establishes the control hybrid model of the compound helicopter,which effectively reduces the amount of redundant control.Based on this,balance calculation and stability analysis were carried out for the entire flight phase,and the changes and stability characteristics of the various maneuvering and attitude variables during the flight were determined.Finally,based on the trim,the basic performance of this helicopter is calculated.In addition,a comparative analysis of the flight performance of the compound helicopter using the deceleration transition mode and the autorotation transition mode is carried out.It is found that the compound helicopter can carry out forward flight,and because the compound helicopter adopting the rotation transition reduces the power required by the rotor,its maximum flight speed can be further increased.更多还原