Directional stability during the roll-out phase is crucial to the safety and reusability of the aircraft. Because of the mechanical properties, the wheel-skid aircraft is more prone to produce course instability. To address this issue, the taxiing safe set of the wheel-skid aircraft is discussed based on the reachability theory. A dynamic model of the on-ground aircraft is established firstly, considering the complex condition of the ground loads. Then, the particular Hamilton–Jacobi partial differential equation is used to obtain the safe set. According to the safe set results, the optimal control of the rudder is built in the state space. Its effectiveness is verified by the comparison with other robust methods. In addition, three structural parameters are selected to analyze the influences on the safe set. Results indicate that the maximum safe yaw angle increases from $1°$ to $9°$ at 70 m/s under the optimal control of the rudder when the steering of nose wheel is locked. The safe boundary in the middle–high-speed region expands by 43.5% under the rudder control. Because of the mechanical properties, uncontrollable deflection will appear due to the asymmetric disturbances when the longitudinal velocity is lower than 42 m/s.

推出阶段的方向稳定性对于飞机的安全性和可重复使用性至关重要。由于机械性能，轮滑飞机更容易产生航向不稳定性。为了解决这个问题，基于可达性理论讨论了轮滑飞机的滑行安全装置。首先，考虑了地面载荷的复杂条件，建立了地面飞机的动力学模型。然后，使用特定的汉密尔顿-雅各比偏微分方程获得安全集。根据安全设置结果，在状态空间中建立了舵的最佳控制。通过与其他健壮方法进行比较，验证了其有效性。此外，选择了三个结构参数来分析对安全设置的影响。$\mathrm{1个}°$ 到 $9°$当前轮的转向锁定时，在舵的最佳控制下以70 m / s的速度行驶。在方向舵的控制下，中高速区域的安全边界扩大了43.5％。由于机械性能，当纵向速度低于42 m / s时，由于不对称的干扰，将出现无法控制的偏转。