Recently,stratospheric airships prefer to employ a vectored tail rotor or differential main propellers for the yaw control,rather than the control surfaces like common low-altitude airship.The load capacity of vectored mechanism and propellers are always limited by the weight and strength,which bring challenges for the attitude controller.In this paper,the yaw channel of airship dynamics is firstly rewritten as a simplified two-order dynamics equation and the dynamic characteristics is analyzed with a phase plane method.Analysis shows that when ignoring damping,the yaw control channel is available to the minimum principle of Pontryagin for optimal control,which can obtain a Bang–Bang controller.But under this controller,the control output could be bouncing around the theoretical switch curve due to the presence of disturbance and damping,which makes adverse effects for the servo structure.Considering the structure requirements of actuators,a phase plane method controller is employed,with a dead zone surrounded by several phase switch curve.Thus,the controller outputs are limited to finite values.Finally,through the numerical simulation and actual flight experiment,the method is proved to be effective. Recently, stratospheric airships prefer to employ a vectored tail rotor or differential main propellers for the yaw control, rather than the control surfaces like common low-altitude airship. Which load capacity of vectored mechanism and propellers are always limited by the weight and strength, which bring challenges for the attitude controller. In this paper, the yaw channel of airship dynamics is rewritten as a simplified two-order dynamics equation and the dynamic characteristics is analyzed with a phase plane method. Analysis shows that when ignoring damping, the yaw control channel is available to the minimum principle of Pontryagin for optimal control, which can obtain a Bang-Bang controller. But under this controller, the control output could be bouncing around the theoretical switch curve due to the presence of disturbance and damping, which makes effects for the servo structure. Consumption of the structure requirements of actuators, a phase plane method controller is employed, with a dead zone surrounded by several phase switch curves .hus, the controller outputs are limited to finite values. Finally, through the numerical simulation and actual flight experiment, the method is proved to be effective.