Patent ID: 9483058
Filing Date: 2016-11-01
CPC Classification: B64D,G01C,G05D

Claim Text:
1. A computer implemented method of controlling an aircraft, the method comprising the steps of: determining whether a change in altitude at a predetermined engine thrust setting can be performed, the determination comprising: determining a climb requirement comprising initial and final altitudes and a required range of airspeeds at the final altitude; determining aircraft performance data comprising a thrust produced at the final altitude at the predetermined thrust setting, an airspeed at the initial altitude and an aircraft total mass at the initial altitude; using the aircraft performance data to determine an airspeed and a drag at the final altitude if a change in altitude at the predetermined engine thrust setting were performed; determining whether thrust and airspeed at the final altitude at the predetermined thrust setting is greater than drag; and providing a signal indicating whether the airspeed at the final altitude falls within the required range of airspeeds, and whether the thrust at the final altitude and airspeed at the predetermined thrust setting is greater than drag.