Abstract: An aircraft and method of operating an aircraft include a flight formation control unit configured to automatically transition the aircraft into an automatic flight formation mode in response to the aircraft being within one or both of a predetermined speed or a predetermined range in relation to at least one other aircraft flying within the automatic flight formation mode. The flight formation control unit can be further configured to automatically transition the aircraft out of the automatic flight formation mode in response to detection of a control signal received from one or more flight controls of the aircraft. The flight formation control unit can be further configured to automatically cycle the aircraft and the at least one other aircraft to different positions during the automatic flight formation mode.

Abstract: An aircraft and method of operating an aircraft include a flight formation control unit configured to automatically transition the aircraft into an automatic flight formation mode in response to the aircraft being within one or both of a predetermined speed or a predetermined range in relation to at least one other aircraft flying within the automatic flight formation mode. The flight formation control unit can be further configured to automatically transition the aircraft out of the automatic flight formation mode in response to detection of a control signal received from one or more flight controls of the aircraft. The flight formation control unit can be further configured to automatically cycle the aircraft and the at least one other aircraft to different positions during the automatic flight formation mode.

Abstract: Systems and methods provide sloped landing exceedance warning and avoidance. One system includes a surface slope determination system configured to measure a plurality of distances between an aircraft and a surface. The system also includes an inertial navigation system configured to sense aircraft attitude information. A flight control system is communicatively coupled to the surface slope determination system and the inertial navigation system. The flight control system is configured to estimate a slope angle of the surface. The flight control system is also configured to determine one or more approach characteristics based on the slope angle and the aircraft attitude information. The flight control system is additionally configured to identify a warning condition and perform one or more avoidance measures when one or more of the approach characteristics exceeds a predetermined threshold. A pilot cuing device also generates a notification when the warning condition is identified.

Abstract: Systems and methods provide sloped landing exceedance warning and avoidance. One system includes a surface slope determination system configured to measure a plurality of distances between an aircraft and a surface. The system also includes an inertial navigation system configured to sense aircraft attitude information. A flight control system is communicatively coupled to the surface slope determination system and the inertial navigation system. The flight control system is configured to estimate a slope angle of the surface. The flight control system is also configured to determine one or more approach characteristics based on the slope angle and the aircraft attitude information. The flight control system is additionally configured to identify a warning condition and perform one or more avoidance measures when one or more of the approach characteristics exceeds a predetermined threshold. A pilot cuing device also generates a notification when the warning condition is identified.