马鸿儒, 穆志韬, 李洪伟, 孙文胜. 基于桨盘倾角的直升机涡环状态边界修正计算方法[J]. 空气动力学学报, 2018, 36(1): 31-34. DOI: 10.7638/kqdlxxb-2015.0203
引用本文: 马鸿儒, 穆志韬, 李洪伟, 孙文胜. 基于桨盘倾角的直升机涡环状态边界修正计算方法[J]. 空气动力学学报, 2018, 36(1): 31-34. DOI: 10.7638/kqdlxxb-2015.0203
MA Hongru, MU Zhitao, LI Hongwei, SUN Wensheng. Revised calculation method for helicopter vortex-ring state boundary based on flight attitude[J]. ACTA AERODYNAMICA SINICA, 2018, 36(1): 31-34. DOI: 10.7638/kqdlxxb-2015.0203
Citation: MA Hongru, MU Zhitao, LI Hongwei, SUN Wensheng. Revised calculation method for helicopter vortex-ring state boundary based on flight attitude[J]. ACTA AERODYNAMICA SINICA, 2018, 36(1): 31-34. DOI: 10.7638/kqdlxxb-2015.0203

基于桨盘倾角的直升机涡环状态边界修正计算方法

Revised calculation method for helicopter vortex-ring state boundary based on flight attitude

  • 摘要: 首先对模型试验直升机和实飞直升机下滑角进行了对比,明确了桨盘倾角是使理想涡环曲线存在误差的主要原因,分析了斜下滑时直升机各姿态角随前飞速度增大的变化趋势,结合平衡方程和高-辛涡环判据,提出了计入桨盘倾角的实飞涡环状态边界计算方法,最后通过算例对计算方法进行了验证和分析。结果表明,基于桨盘倾角修正的涡环边界与试飞数据基本吻合,桨盘倾角对旋翼涡环临界值影响较大,且影响程度因机型而异。

     

    Abstract: Vortex-ring state (VRS) is hazardous for helicopter flight, which can cause the vehicle being out of control in some cases. It is important to accurately predict the occasion when helicopter getting into this dangerous state, called vortex-ring boundary. The currently existing calculation model for the boundary is considerably precise but still has error being compared with flight test data. Firstly, glide angles of helicopter in model test and real flight were compared to find out that panel obliquity is the main factor to cause the inaccuracy of ideal vortex-ring boundary. The trend of helicopter attitudes with forward speed increase was analysed in helicopter inclined descent. The calculation model of rotor vortex-ring boundary was found in consideration of panel obliquity. Based on helicopter balance equation and Gao-Xin criterion, the algorithm vortex-ring state boundary for real flight was pointed out, in which the panel obliquity was reckoned in. Then, being taken for instance, the revised boundary curve of a helicopter was numerically figured out. Finally, the calculation results were verified and analyzed in contrast with flight test data. Results show that, the revised vortex-ring boundary curve for real flight is located below the ideal one, which has a more favorable agreement with flight test data. Thus, panel obliquity has high influence on rotor VRS boundary. On account of the difference in panel obliquity with different helicopter, however, the level of the influence also depends on the helicopter type.

     

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