Patent ID: 8290641
Filing Date: 2012-10-16
Classification: G01C,G05D

Abstract:
1. An aircraft attitude system for use by a pilot for warning of an aircraft departure from a desired aircraft attitude and directives for the pilot to manually return an aircraft to a desired aircraft attitude, the aircraft attitude system comprising: a detection system having a first accelerometer such that the first accelerometer determines a first attitude parameter of an aircraft in which the detection system is mounted; a user interface for receiving manual inputs corresponding to a set of pilot-selectable attitude parameters of the aircraft, the pilot-selectable attitude parameters including maximum pitch angle and maximum bank angle; and an instrument display having a recovery system, the recovery system receiving information corresponding to the first attitude parameter such that, responsive to the first attitude parameter of the aircraft corresponding to the first pilot-selectable attitude parameter, the recovery system provides progressive flight control positioning directives to the pilot via the instrument display for manually returning the aircraft to a flight attitude within the pilot-selectable attitude parameters; the instrument display displaying the progressive flight control positioning directives as arrows illuminated on the display, with a length of a first of the arrows corresponding to a magnitude of the first attitude parameter detected by the accelerometer such that a shorter length indicates a smaller angle of the first attitude parameter and a longer arrow indicates a larger angle of the first attitude parameter; wherein: the first of the arrows is displayed with an overall length corresponding to the magnitude of the first attitude parameter; and responsive to the attitude excursion exceeding the first pilot-selectable attitude parameter, the first of the arrows has a first segment and a second segment, the first segment extending from a base of the first of the arrows and being of a first length corresponding to the magnitude of the first pilot-selectable attitude parameter, the second segment extending from the first segment such that the pilot is presented with a visual depiction corresponding to an extent of the attitude excursion.