A Self-Adaptive Aircraft Pitch Rate Control System Employing Difference Equations for Parameter Identification

摘要

In a high performance aircraft in Mach number, angle of attack and altitude can cause a large variation in the short-period transfer function. To provide the pilot with a consistant pitch rate control characteristic an airborne computer, with inputs of elevator deflection angle and pitch rate is used to identify and track changes in the elevator effectiveness. Simulation with an aircraft whose elevator effectiveness varied over a range of 240:1 showed that the desired loop gain was maintained within a factor of two for both pilot command inputs and for random wind gust disturbances of root-mean-square magnitude 20 ft/sec. (Author)