飞机巡航阶段尾涡遭遇安全性多参数评估方法

分析了飞机遭遇尾涡后的响应机理，综合考虑飞机滚转阻尼特性及操纵品质等因素，建立了飞机滚转角加速度计算模型；因飞机遭遇尾涡后飞行轨迹及飞行姿态发生改变，选择了多个扰动参数评估尾涡遭遇安全性，建立了飞机动力学参数计算模型；为确定尾涡遭遇可接受安全水平，基于国内现行尾流间隔标准，统计了中低空典型机型组合的尾流遭遇受扰参数计算数据；分析了高空尾涡流场演化特性，计算了高空巡航状态下的尾流安全间隔，分析了不同因素对飞行安全的影响。研究结果表明：与中低空相比，高空尾涡流场的初始强度大，持续距离长，飞行高度超过9 000 m后，尾涡消散随高度的增大而加快；当前机为超级重型机、重型机，现行尾流间隔无法保证飞行安全，需增加安全间隔1.4~2.1 km，飞行高度分别超过13 800、14 400 m后，尾涡遭遇严重度降低；当前机为一般重型机时，尾流安全间隔可缩减1.5 km以提高空域利用效率；当前机为中型机时，尾涡遭遇安全性较高，但此时受最小雷达间隔限制，无法进一步缩减前后机间距；后机的飞行速度越低，发生尾涡遭遇的严重程度越高；在后机初始滚转坡度角由0增加到10°的过程中，尾涡安全间隔增加1.3 km，增加幅度约为8.61%。可见，采用多个受扰参数能有效评估高空尾涡遭遇严重程度。

Multi-parametric evaluation method of aircraft wake vortex encounter safety in cruise phase

The response mechanism of aircraft after encountering wake vortices was analyzed. Considering the factors such as roll damping characteristics and handling qualities of aircraft, the calculation model for the roll angular acceleration of aircraft was constructed. Due to the change in the flight path and attitude after wake vortex encounters, several disturbance parameters were selected to evaluate the safety of wake vortex encounters, and the calculation model for aircraft dynamics parameters was built. For the determination of the acceptable safety level of wake vortex encounters, the computation data of the disturbance parameters for wake vortex encounters of aircraft combinations at medium and low altitudes were obtained on the basis of the current domestic standard of wake separation. The evolutionary characteristics of the flow fields of wake vortices at high altitudes were analyzed, the wake safety separation at high altitudes was studied, and the influence of different factors on flight safety was analyzed. Research results show that compared with the results at medium and low altitudes, the flow fields of wake vortices at high altitudes are characterized by larger initial strength and duration. Beyond the flight altitude of 9 000 m, the speed of wake vortex dissipation increases with the rise in height. When the leading aircraft is a super heavy aircraft or heavy aircraft, flight safety cannot be guaranteed by current wake separation, and the safety separation should increase by 1.4-2.1 km. When the flight altitude is beyond 13 800 and 14 400 m, the severity of wake vortex encounters reduces. When the leading aircraft is a general heavy aircraft, the wake safety separation can reduces by 1.5 km to improve airspace utilization efficiency. In the case of a medium-size leading aircraft, the safety of wake vortex encounters is high, but due to the limitation of the minimum radar separation, the distance between the leading and following aircraft cannot further reduce. A lower flight speed of the following aircraft is accompanied by more serious wake vortex encounters. When the initial roll bank angle of the following aircraft raises from 0 to 10°, the safety separation of wake vortices raises by 1.3 km, an increase of about 8.61%. It can be seen that the use of multiple disturbance parameters is effective in evaluating the severity of high-altitude wake vortex encounters. 4 tabs, 15 figs, 30 refs.