Control Logic for Landing-Abort Autopilot Mode

摘要

An automatic control for an aborted landing is discussed with emphasis on the use of a body-mounted accelerometer, which is assumed to be both available and reliable, to provide a surrogate for an angle-of-attack signal. The control logic was developed for a typical large commercial jet transport and tested by simulation on a digital computer. The system developed met the objective: achieve a safe aborted landing and climb-out, such as might be required as a result of missing the landing window at Cat. II decision height, in the presence of severe wind shear. The performance demonstrated shows the logic to be effective and safe for initiating a go-around maneuver.