Patent ID: 9639087
Date: 2017-05-02
CPC Classifications: B64C,B64D,G05D,G08G

Claim:
1. An aircraft, comprising: an actuator; a set of one or more inertial sensors; and a processor configured to: continuously generate an emergency landing procedure that includes a sequence of control settings; detect a local maximum in the other one of the desired signal and the measured signal; determine if a time difference between the local minimum and the local maximum does not exceed a time threshold; determine if an amplitude difference between the local minimum and the local maximum exceeds an amplitude threshold; in the event it is determined that the time difference does not exceed the time threshold and it is determined that the amplitude difference exceeds the amplitude threshold, decide to land the aircraft, including by using the sequence of control settings and the set of inertial sensors to control the actuator; and land the aircraft, including by using the sequence of control settings and the set of inertial sensors to control the actuator.