Apparatus and method for warning of a high yaw condition in an aircraft

Claim 3

The method as set forth in claim 1 wherein the second rolling moments are maximum rolling moments generated by operation of the aircraft primary flight control surfaces.

Claim 4

The method as set forth in claim 2 wherein: a. maximum sideslip angles, β MAX , are determined to be sideslip angles in wich the second rolling moments are equal to the first rolling moments; and b. the warning sideslip angles, β W , are sideslip angles which are less than the maximum sideslip angles by amounts equal to Δβ.

Claim 5

The method as set forth in claim 3 wherein: a. the first rolling moments are determined from aircraft test data measured at selected aircraft airspeeds and selected sideslip angles; and b. the second rolling moments are determined by aircraft test data measured at the selected aircrafts airspeeds.

Claim 6

The method as set forth in claim 4 wherein Δβ is determined as a function of aircraft airspeed.

Claim 7

The method as set forth in claim 1 wherein the airflow differential is measured by measuring a difference in air pressure at the first and second locations of the aircraft.

Claim 8

The method as set forth in claim 1 wherein the warning is provided to the pilot by vibrating cockpit controls which operate the rudder.

Claim 9

Apparatus for warning a pilot of an aircraft having a rudder and other primary flight control surfaces, of an excessive yaw condition, comprising: a. means for measuring the aircraft yaw condition by measuring an airflow differential at first and second locations of the aircraft; b. means for converting the measured airflow differential to a measured sideslip angle; c. means for generating values of warning sideslip angle as a function of aircraft airspeed, the generating means including: (1) means for determining first rolling moments generated about a roll axis of the aircraft when the aircraft is at selected sideslip angles and at selected aircraft airspeeds, (2) means for determining second rolling moments generated about the roll axis in a direction opposite to the first rolling moments by operation of the aircraft primary flight control surfaces at the selected aircraft airspeeds, and (3) means for selecting the warning sideslip angles from the selected sideslip angles at which the first rolling moments exceed the second rolling moments at the selected aircraft airspeeds; d. means for measuring aircraft airspeed and for comparing the measured sideslip angle with the warning sideslip angle corresponding to the measured aircraft airspeed; e. means for generating a first signal when the measured sideslip angle exceeds the warning sideslip angle; and f. means for providing a warning to the pilot in response to the first signal.

Claim 10

Apparatus for warning a pilot of an aircraft having a rudder and other primary flight control surfaces, of an excessive yaw condition, comprising: a. means for measuring the aircraft yaw condition by measuring an airflow differential at first and second locations of the aircraft; b. means for converting the measured airflow differential to a measured sideslip angle; c. means for generating values of warning sideslip angle as a function of aircraft airspeed, the generating means including: (1) means for determining first rolling moments generated about a roll axis of the aircraft when the aircraft is at selected sideslip angles and at selected aircraft airspeeds, (2) means for determining second rolling moments generated about the roll axis in a direction opposite to the first rolling moments by operation of the aircraft primary flight control surfaces at the selected aircraft airspeeds, and (3) means for selecting the warning sideslip angles from the selected sideslip angles at which the first rolling moments exceed the second rolling moments at the selected aircraft airspeeds; d. means for measuring aircraft airspeed and for comparing the measured sideslip angle with the warning sideslip angle corresponding to the measured aircraft airspeed; e. means for generating a first signal when the measured sideslip angle exceeds the warning sideslip angle; and f. means for providing a warning to the pilot in response to the first signal.

Claim 11

The apparatus as set forth in claim 8 wherein said airflow differential measuring means includes means for measuring a difference in air pressure at the first and second locations of the aircraft.

Claim 12

The apparatus as set forth in claim 9 wherein the warning means includes means for vibrating cockpit controls which operate the rudder.

Claim 15

The method as set forth in claim 11 wherein the rolling moments are generated due to a dihedral effect which results from yawing of the aircraft while it is airborne.