摘要
应用自由尾迹方法和旋翼配平模型,建立了一个悬停和前飞状态旋翼在导弹发射线上的诱导速度计算模型。基于该模型,以AH-1G直升机缩比模型为算例,计算了悬停和低速前飞状态导弹在发射线上受到的气流诱导影响,并通过与可得到的试验结果对比验证了计算方法的有效性;以Z-9直升机为算例,计算了悬停和前飞时的旋翼尾迹边界,分析了导弹在发射线上受到的下洗影响随直升机前进比的变化规律,表明了在大于某一前进比后,旋翼下洗流场对导弹发射线的诱导影响很小。
Based on the rotor free-wake model and the rotor trim model, an analytical method is developed for the prediction of helicopter rotor induced velocities on missile trajectory. As numerical examples, the helicopter AH-1G model rotor is used and its induced effects on missile trajectory are calculated for hover and low-speed forward flight. The comparisons between the calculated results and available experimental data are made and the capability of the present method is demonstrafed. Also, helicopter Z-9 is taken as an example, and the rotor wake boundaries are calculated and the variations of the rotor-induced effects on missile trajectory with the advance ratio are analyzed. It is shown that the rotor has little downwash influence on missile trajectory when the advance ratio is larger than some value.
出处
《空气动力学学报》
EI
CSCD
北大核心
2005年第4期449-454,共6页
Acta Aerodynamica Sinica
关键词
自由尾迹
下洗流场
旋翼
直升机
导弹
free wake
downwash flow field
rotor
helicopter
missile
