单旋翼直升机气动布局对飞行性能的影响  

Influences of aerodynamic layout of single main rotor helicopter on flight performance

作　　者：苏媛[1] 吕少杰[1] 曹义华[1] 李国知[1] 

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：《北京航空航天大学学报》2014年第5期591-595,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为研究单旋翼直升机气动布局对直升机飞行性能的影响,以直升机飞行动力学模型为基础,在原始气动布局下分别对平飞、爬升与下滑和稳定协调转弯情况下的旋翼需用功率进行了配平,并计算了飞行性能指标,计算结果与参考数据吻合较好,证明模型可用.以UH-60A直升机为例,研究了不同气动布局参数下的直升机飞行性能,结果表明,在变化范围内,旋翼位置参数对前飞和垂直飞行性能影响都很大,减小旋翼纵向距离有利于提高飞行性能,尾桨倾斜角在悬停和小速度情况下对飞行性能影响较大,平尾水平位置的后移有助于提升最大飞行速度.To investigate flight performance of the signal main rotor helicopters with different aerodynamic configurations based on helicopter nonlinear flight dynamic model,trim calculation of main rotor required power in case of level flight,steady-climb and descent,and steady coordinated-turn under baseline aerodynamic layout were conducted. The flight performance indicators were calculated. The agreement between the computational results and the referenced data indicates that the model is feasible. The flight performance of UH-60A helicopter was calculated and analyzed with variable aerodynamic configuration parameters. The results show that,in the range of variation,main rotor position parameters have significant influence on both level flight and vertical flight performance,the decrement of rotor longitudinal distance can improve flight performance dramatically,tail rotor canted angel has major impact in hover and low speed,moving backward of the longitudinal position of horizontal tail is helpful to improve the maximum level flight velocity.

关 键 词：直升机 飞行力学 需用功率 飞行性能 气动布局 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]