CONTROL LOGIC FOR LANDING-ABORT AUTOPILOT MODE.

This report describes the results of an investigation of an automatic control for an aborted landing. Emphasis was 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 objectives were to 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 automatic control system developed herein met the objectives, and the performance demonstrated showed the logic to be effective and safe for initiating a go-around maneuver.