Pilot Manipulation Research Articles

Method of predicting nonlinear pilot-induced oscillations due to flight control degradation based on digital virtual flight

Because few methods of predicting nonlinear pilot-induced oscillations are available, it is difficult to analyze the sensitive characteristics of such oscillations in the stage of aircraft scheme design. The pilot has the ability to self-adapt, and the control behavior may change before and after flight control degradation. To identify flight control degradation faults and adaptively adjust a pilot's manipulation behavior, three new modules, including pilot perception, flight control degradation judgment and adaptive adjustment, are established to construct a time-varying pilot model. Combined with a digital flight task model, a digital virtual flight simulation model of flight control degradation is built. An identification algorithm based on fuzzy logic is adopted to quantitatively evaluate the pilot-induced oscillation characteristics according to the numerical simulation results. Then, a nonlinear pilot-induced oscillation prediction method based on digital virtual flight is established. A pitch attitude tracking task is selected to predict the longitudinal, nonlinear pilot-induced oscillations. The results show that the prediction results of the simulations are basically consistent with those of a human-in-the-loop flight test with a ground simulator, which verifies the correctness of the proposed method. Through a sensitivity study of the stick force gradient after degradation, the influence of this parameter and the recommended value are determined. This method can be used to predict the nonlinear pilot-induced oscillation characteristics of fly-by-wire aircraft in the conceptual design stage and provide a theoretical reference for the optimal design of flight control systems.

Study on Pilot Transfer Function Model Gain of Closed-Loop Pilot-Vehicle System

Based on the analysis of pilot handling behavior characteristics, this paper establishes the pilot transfer function model. According to the characteristics of closed-loop pilot-vehicle system and the relationship between pilot and flight quality, the specific calculation method of pilot model steady state gain was given. Take the aircraft roll angle manipulation for example, and simulate the pilot's manipulation of aircraft of dynamic process. The results show that: the pilot model steady state gain calculation method is simple and feasible, and have a certain reference value for the analysis of closed-loop pilot-vehicle system.