直升机旋翼对尾桨非定常气动载荷的影响
收稿日期: 2014-10-13
修回日期: 2015-01-16
网络出版日期: 2015-03-10
基金资助
国家自然科学基金 (11502105); 江苏省高校自然科学研究面上项目 (15KJB130004)
Influence of helicopter rotor on tail rotor unsteady aerodynamic loads
Received date: 2014-10-13
Revised date: 2015-01-16
Online published: 2015-03-10
Supported by
National Natural Science Foundation of China (11502105); The Project of Natural Science Research of Higher Education Institutions of Jiangsu Province (15KJB130004)
悬停和侧滑状态的直升机主旋翼桨尖涡将穿透尾桨桨尖平面,由此导致尾桨非定常气动载荷发生明显变化。为更准确地模拟由主旋翼/尾桨干扰产生的尾桨非定常气动载荷变化,通过在面元压力项中增加由旋翼桨尖涡诱导的时变项,体现旋翼桨尖涡速度和几何时变对桨叶非定常压力的影响,同时采用涡面镜像法修正涡粒子法的黏性项,确保桨叶附近区域旋翼涡量守恒,建立旋翼尾迹对尾桨叶的非定常气动干扰模型,并耦合面元/黏性涡粒子法,构建直升机主旋翼/尾桨干扰下的尾桨非定常气动载荷分析方法。通过计算AH-1G旋翼桨叶非定常气动载荷特性,并与实验测量值、计算流体力学(CFD)计算结果对比,验证本文非定常气动干扰模型的有效性。随后基于NASA ROBIN(Rotor Body Interaction)模型分析悬停、侧风和60°右侧滑状态主旋翼对尾桨非定常气动载荷的影响,分析表明主旋翼尾迹对尾桨非定常气动载荷影响显著。悬停状态的主旋翼/尾桨干扰导致尾桨拉力平均值下降、非定常气动载荷显著增加;左侧风状态,主旋翼/尾桨干扰削弱尾桨"涡环"程度,显著增加尾桨拉力和非定常气动载荷;60°右侧滑状态,主旋翼/尾桨干扰导致尾桨拉力损失最大,且在低速侧滑状态出现尾桨拉力"迅速恢复"现象,尾桨非定常气动载荷幅值迅速增加。
谭剑锋 . 直升机旋翼对尾桨非定常气动载荷的影响[J]. 航空学报, 2015 , 36(10) : 3228 -3240 . DOI: 10.7527/S1000-6893.2015.0024
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.
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