直升机尾桨涡环边界的计算  

Calculation of helicopter tail rotor vortex ring boundary

作　　者：孙文胜[1] 马鸿儒[1] 

机构地区：[1]海军航空工程学院青岛分院,山东青岛266041

出　　处：《飞行力学》2014年第2期126-128,共3页Flight Dynamics

摘　　要：为避免直升机进入尾桨涡环状态,分析了直升机尾桨涡环状态的特点,将高-辛判据应用于直升机尾桨涡环边界的计算,分别计算了进入尾桨涡环的各临界速度,并绘制了尾桨涡环边界曲线。针对计算结果的分析表明,直升机的飞行高度和地面温度对尾桨涡环的临界速度有一定影响,直升机侧飞或转弯时有可能进入尾桨涡环,应加以避免。最后对进一步的研究工作提出了建议。To prevent helicopters from turning into tail rotor vortex ring state, the characteristics of vortex ring state for helicopter tail rotor was analyzed. With Gao-Xin criterion being used in the calculation of vortex ring state boundary for helicopter tail rotor, critical rates of helicopter tail rotor vortex ring were fig- ured out and boundary curve of tail rotor vortex ring was drawn. Analysis on the results showed that flight height of helicopter as well as temperature on ground have an effect on the critical rates and the helicopter should be prevented from turning into tail rotor vortex ring state in lateral flight or turning. Finally, the suggestions for further study is offered.

关 键 词：直升机尾桨 涡环判据 临界速度 边界曲线 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]