Computer Program to Simulate the Lateral-Directional Response of a High Performance Aircraft Digital Electronic Flight Control System

摘要

The IBM Company's Continuous System Modeling Program was used to simulate the lateral and directional flight control systems of the F/A-18 aircraft. The model is designed for use in studies of high angle-of-attack maneuvering flight and is restricted to the Auto Flaps Up mode of operation. The model accepts simulated pilot stick and rudder inputs, air data information, and rate gyro, angle-of-attack, and acceleration feedback signals. Outputs are differential stabilator, differential leading-edge and trailing edge flap, aileron, and rudder deflections. Typical input values are used to validate the model, generating output controls surface deflections which correspond to those expected for the F/A-18 aircraft. (Author)