[发明专利]一种在低空风切变中飞机临界规避参数的确定方法

权利要求书

1.一种在低空风切变中飞机临界规避参数的确定方法，需要确定的飞机临界规避参数如下：飞机坡度φ(°)，飞机转弯半径R(m)，飞机转弯角速度ω(°/s)，飞机转弯法向过载系数n_z(g)，飞机转弯时间t(s)，飞机最小安全高度H_s(m)；其特征在于，飞机临界规避低空风切变的步骤如下：

1.1、计算规避转弯半径R：按照下式计算飞机的规避转弯半径R，

R=L2+LDD···················································································(1)]]>

式中，L是雷达探测的距离(m)，D是风切变尺度(m)；

1.2、计算法向过载系数n_z：将规避转弯半径R代入下式得到法向过载系数n_z，

R=V2gnz2-1······································································(2)]]>

式中，V是当前飞机的飞行速度(m/s)；则：

nz=((V2R*g)2+1)·····································································(3)]]>

式中：g为重力加速度(m/s²)；

1.3、计算飞机转弯时间t：

将法向过载系数n_z代入下式得到飞机转弯时间t，

t=arcsin((L+0.5*D)/(R+0.5*D))/2π*Vgnz2-1····························································(4)]]>

1.4、计算飞机转弯角速度ω和飞机坡度φ：

将当前飞机飞行速V和法向过载系数n_z，代入公式(5)得到飞机转弯角速度ω，代入公式(6)得到飞机坡度φ，

ω=gnz2-1V×57.3···················································(5)]]>

φ=arccos(1/nz)×57.3···················································(6)]]>

1.5、计算飞机最小飞行安全高度H_s：

已知翼展l和计算得到的飞机坡度φ，根据下式计算得到最小飞行安全高度H_s，

H_s＝(15+l*sin(φ/57.3)/2)………………………………………………(7)

式中，l为翼展(m)；至此，确定了低空风切变中飞机临界规避参数。