A hybrid landing distance prediction algorithm based on fuzzy inference is suggested to overcome the shortcomings of current approaches in real-time performance and handling nonlinear dynamics in order to successfully prevent runway excursion incidents during aircraft landings. The method integrates multiple prediction strategies based on the three distinct dynamic phases of the landing process: during the glide phase, a ground speed vector mapping method is used for prediction; during the rollout phase, a trajectory analysis method is employed; and during the flare phase, which involves significant state changes and is difficult to model accurately, a Mamdani-type fuzzy inference method is applied. A high-fidelity simulation platform for multi-condition validation is also proposed. With a prediction inaccuracy of fewer than 35 meters during the flare phase and a computation time of less than 3 milliseconds per calculation, this platform can deliver real-time landing distance forecasts in turbulent wind environments. The proposed method meets real-time decision-making requirements and offers a feasible engineering strategy to enhance landing safety margins.

At present, aircraft taxiing at ground airports needs to be provided with a thrust by the main engine. The taxiing process is inefficient, has high fuel consumption and serious pollution, and is prone to safety risks. In this paper, a new configuration of aircraft autonomous traction taxiing system is proposed based on the principle of hydraulic secondary control, in which a hydraulic motor drive device is installed at the front wheels of the aircraft to drive the wheels to rotate forward or backward. Based on this, autonomous taxiing can be realized without relying on the main engines, thus greatly improving airport operation efficiency. Meanwhile, this paper analyzes the influencing factors of the autonomous traction taxiing process, and investigates the parameter matching design of the new configuration system. Besides, this paper develops the ground principle prototype, designs the aircraft longitudinal bonding force observer and the aircraft wheel disturbance moment observer, and proposes the speed control method of the aircraft front wheel autonomous traction taxiing by considering the ground bonding force saturation characteristics. Finally, the ground taxiing test is conducted, and the results show that the new configuration proposed in this paper presents a new solution for aircraft autonomous traction taxiing.