加装格尼襟翼旋翼的直升机飞行性能

为研究加装格尼襟翼旋翼的直升机飞行性能，建立了加装格尼襟翼旋翼的直升机飞行动力学模型。采用UH-60A直升机试飞数据验证了计算模型的正确性。在此基础上，分析了样例直升机加装格尼襟翼后重量系数、格尼襟翼高度、沿径向位置和加装方式对旋翼需用功率的影响，以及加装格尼襟翼后旋翼桨叶剖面迎角分布、旋翼操纵量和机身姿态角的变化等。研究表明，直升机在重量系数较大的状态下高速前飞时，旋翼加装格尼襟翼能够明显降低直升机的需用功率，且加装转动格尼襟翼的效果优于加装固定格尼襟翼。功率降低幅值随格尼襟翼高度的增加先增加后减小。格尼襟翼在桨叶上布置的位置越靠近桨尖，其对需用功率的影响越大。直升机在重量系数较大的状态下高速前飞时，加装格尼襟翼能够使旋翼后行侧最大迎角显著减小。加装格尼襟翼后旋翼总距和纵横向周期变距减小。

Flight performance of helicopter rotors with Gurney flaps

To investigate the helicopter performance with the rotor deployed with Gurney flaps, a helicopter flight dynamics model is coupled with a Gurney flap model to analyze the fight performance. The flight test data of UH-60A helicopter is utilized to validate the modeling. The influence of the helicopter weight coefficient, Gurney flap height, deployment position and type on the rotor power is investigated. The distributions of the angle of attack over the rotor disk, rotor pitch controls and fuselage attitude angles are also analyzed. The results indicate that the Gurney flap can significantly reduce the required rotor power with larger takeoff gross weight at higher speed forward flight. The moveable Gurney flap can achieve better performance improvement than the fixed height Gurney flap. The power reduction increases with the height of Gurney flap and then decreases. The Gurney flap can introduce a larger power reduction when the position of Gurney flap is near the blade tip. The deployment of Gurney flap can distinctly decrease the maximum angle of attack in the retreating side with larger takeoff gross weight at higher speed forward flight. The collective, longitudinal and lateral cyclic pitches decrease with the deployment of Gurney flaps.