小型复合式共轴无人直升机动力学模型研究  

Research on dynamics model of the small compound coaxial unmanned helicopter

作　　者：徐安安 王放[1] 高成 XU Anan;WANG Fang;GAO Cheng(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《飞行力学》2021年第4期52-56,共5页Flight Dynamics

基　　金：国家重点研发计划资助(2017YFD0701004)。

摘　　要：以加装尾推的小型复合式共轴无人直升机为研究对象,重点研究直升机在一定的前飞速度下俯仰角的变化情况。首先建立了直升机气动模型,得到前飞时的平衡方程组,并使用Newton法对方程组进行求解,从而得到仿真配平结果;其次对样例直升机未加装尾推螺旋桨和加装尾推螺旋桨情况下进行一定速度下的前飞试验,采集试飞数据;最后对仿真结果和试验数据进行比较和分析。结果表明:在较低速度时,直升机气动模型与实际结果符合性较好,加装尾推能够减小直升机稳定前飞时的俯仰角,同时还能降低双旋翼消耗的总功率。Based on the small compound coaxial unmanned helicopter with a tail thruster, the change of the helicopter’s angle of pitch at a certain forward flight speed was studied. Firstly, the aerodynamic model of the helicopter was established, the equation set of equations in forward flight was obtained, and the Newton method was used to solve the equation group to obtain the simulation data. Next, the sample helicopter was tested in forward flight at a certain speed without tail thruster and with tail thruster, obtaining the experimental data. Finally, the simulation data was compared with experimental data and analyzing of the results. The results show that the aerodynamic model of the helicopter is almost fit to the reality at a lower speed, and the addition of tail thruster not only reduces the helicopter’s angle of pitch during stable forward flight, but also reduces the power consumption of the coaxial rotors.

关 键 词：共轴直升机 尾推 旋翼气动力 俯仰角 

分 类 号：V279[航空宇航科学与技术—飞行器设计] V212