直升机旋翼对尾桨非定常气动载荷的影响

doi:10.7527/S1000-6893.2015.0024

Abstract

Abstract:

Helicopter main rotor tip vortex will penetrate into the tip path plane of tail rotor under hover and side-slip conditions, which results in marked variation of tail rotor unsteady aerodynamic loads. In order to more accurately simulate the variation of tail rotor unsteady aerodynamic loads due to main rotor/tail rotor interaction, time-varying item induced by rotor tip vortex is added into pressure term of panel method, which is used to reflect the influence of the velocity impulse and time-varying geometry of rotor tip vortex on unsteady pressure of rotor blades. Meanwhile, viscous effect of vortex particles method is modified through vortex mirror technique to ensure that the rotor vorticity near blades is constant. Thus, the model of unsteady aerodynamic interaction of rotor wake and tail rotor blade is established, and coupled into panel/viscous vortex particle hybrid method to found the analytical method of tail rotor unsteady airloads under main rotor/tail rotor interaction. The unsteady aerodynamic load of AH-1G rotor blade is predicted and compared with the experiment and computational fluid dynamics (CFD) results to validate the effectiveness of the present unsteady aerodynamic interaction model. The influence of main rotor on unsteady aerodynamic loads of tail rotor blade under hover, crosswind, 60° starboard sideslip is analyzed base on NASA ROBIN (Rotor Body Interaction) model. It is shown that the influence of main rotor wake on unsteady aerodynamic loads of tail rotor blade is significant. The average of tail rotor thrust is decreased and the unsteady airload is increased markedly under the main rotor/tail rotor interaction in hover. The "vortex ring" of tail rotor in portside crosswind is weakened by the main rotor/tail rotor interaction, and the tail rotor thrust and unsteady airloads are significantly increased. The damage of tail rotor thrust is the most prominent in 60° starboard sideslip, a phenomenon called "rapid recovery" is observed under low speed sideslip condition, and the amplitude of unsteady airloads of tail rotor is markedly increased due to the main rotor/tail rotor interaction.

Key words: unsteady aerodynamic interaction, aerodynamic loads, viscous vortex particle method, main rotor, tail rotor

CLC Number:

V211.52

TAN Jianfeng. Influence of helicopter rotor on tail rotor unsteady aerodynamic loads[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3228-3240.

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Influence of helicopter rotor on tail rotor unsteady aerodynamic loads

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