加装格尼襟翼旋翼直升机性能研究

发布时间：2018-05-03 07:28

本文选题：直升机 + 旋翼　；参考：《南京航空航天大学》2016年硕士论文

【摘要】：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等参数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。为最大幅度的提升旋翼性能,设计了格尼襟翼安装角变化规律。确定了格尼襟翼安装角以正弦形式变化的方案,并得到了旋翼性能最优时的安装角变化对应正弦函数的幅值和相位。分析了格尼襟翼安装角按高阶正弦形式变化时的旋翼需用功率变化情况,结果表明二阶和三阶正弦形式的变化也能降低旋翼需用功率。
[Abstract]:In order to study the flight performance of the helicopter with the Gini flap rotor, the helicopter flight dynamics model with the Gini flap rotor was established. The validity of the model is verified by the flight test data of UH-60A helicopter. On this basis, the influence of the factors such as the weight coefficient, the height of the Gini flap, the radial position and the mounting mode on the rotor power requirement and the angle of attack distribution of the rotor blade after the installation of the Gini flap are analyzed. Rotor control and fuselage attitude angle change. The results show that when the helicopter flies forward at high speed under the condition of high weight coefficient, the required power of the helicopter can be significantly reduced when the rotor is equipped with the Grigni flap, and the effect of installing the rotated Grigni flap is better than that of the fixed Gini flap. The power reduction amplitude increases first and then decreases with the increase of the height of the Grigni flap. The closer the edge of the blade to the tip of the blade, the greater the influence on the required power. When the helicopter flies forward at high speed under the condition of high weight coefficient, the maximum angle of attack on the rear side of the rotor can be significantly reduced with the addition of the Grigni flap. The rotor total distance and the longitudinal and transverse periodic variation distance are reduced after the installation of the Gini flap. In order to maximize the performance of rotor, the rule of angle change of Gini flap was designed. The scheme that the installation angle of the Grigni flap changes in sinusoidal form is determined and the amplitude and phase of the sinusoidal function corresponding to the installation angle change when the rotor performance is optimized are obtained. The change of rotor power requirement is analyzed when the installation angle of Grigni flap varies according to the higher sinusoidal form. The results show that the change of the second and third order sinusoidal forms can also reduce the rotor power requirement.
【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】：V212.4

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