摘要
从旋翼桨叶的实际气动环境出发导出了桨叶的非定常挥舞运动方程，其中考虑了影响旋翼桨叶非定常挥舞运动的各种因素，包括旋翼入流的时滞效应及前行桨叶的压缩性和后行桨叶的失速特性。给出了计算桨叶非定常挥舞运动的递推公式，并进而描述了雄翼的整体挥舞运动。最后以某型直升机为例，计算了直升机悬停及前飞中施加变距操纵后族双桨叶挥舞运动响应的过渡过程。结果表明：用本文所述方法能合理地计算旋翼桨叶挥舞运动的非定常过渡过程，而且其最终稳态值与经典桨盘平面方法得到的结果相同。本方法尤其适合于直升机机动飞行的分析计算。
This paper presents an unsteady flapping motion equation of rotor blades. The influence of some factors including rotor dynamic inflow, retreating blade dynamic stall and advancing blade compressibility on flapping motion was considered. A recurrence formula of blade unsteady flapping motion was developed and as a result the rotor flapping was described. Finally, a typical helicopter was taken as an example to calculate the transition process of blade flapping motion response to pilot step inputs in hoyer and forward flight. It was shown that the method of this paper can reasonablly calculate the transition process of blade unsteady flapping motion and the stable value of transition process is the same as the results obtained from the classical method based on the rotor disc concept. The method presented in the paper is especially suitable for the analysis and calculation of helicopter maneuver flight.
出处
《空气动力学学报》
CSCD
北大核心
1997年第3期406-414,共9页
Acta Aerodynamica Sinica
