Abstract: Systems and methods for alerting to traffic proximity in the airport environment. Knowledge of the geographic position, speed, rate of change of speed, heading (or track-angle) and/or altitude of own-aircraft (or vehicle) and another, potentially conflicting aircraft (or vehicle) are used to calculate a predicted distance between the two aircraft (or vehicles) at given point of time in the future. If separation distance is predicted to be less than a predetermined acceptable value, then an alert message (aural, visual or both) is issued to the pilot or operator of the vehicle.

Abstract: Systems and methods for alerting to traffic proximity in the airport environment. Knowledge of the geographic position, speed, rate of change of speed, heading (or track-angle) and/or altitude of own-aircraft (or vehicle) and another, potentially conflicting aircraft (or vehicle) are used to calculate a predicted distance between the two aircraft (or vehicles) at given point of time in the future. If separation distance is predicted to be less than a predetermined acceptable value, then an alert message (aural, visual or both) is issued to the pilot or operator of the vehicle.

Abstract: Radar return processing systems and methods are operable to process radar information when an installation vehicle is operating in proximity to a surface area of interest. An exemplary embodiment reduces energy of an output pulse emitted from a radar system; receives a plurality of radar returns from a plurality of objects that reflect the reduced energy output pulses emitted from the radar system; determines a surface area of interest based upon at least a current location of the installation vehicle; and filters the radar returns generated by objects that are located outside of the surface area of interest. Optionally, some systems and methods may reduce a sweep range of an antenna from which the reduced energy output pulses are emitted.

Abstract: A method for determining a currently obtainable climb gradient of an aircraft by determining an estimated aircraft weight as a function of phase of flight, determining the current aircraft weight as a function of the current dynamic pressure, the unaccelerated lift of the aircraft, and the wing surface area of the aircraft during steady-state flight, updating said estimated aircraft weight as a function of the current aircraft weight, determining the current lift and drag coefficients of the aircraft, determining currently available aircraft thrust, and estimating a currently obtainable maximum climb gradient as a function of said thrust, current weight, current lift and drag coefficients.

Abstract: An aircraft terrain warning generator is provided having a terrain and obstacle warning envelope having a lower boundary formed according to the lesser of the current aircraft flight path angle and the obtainable climb gradient.

Abstract: An aircraft terrain warning generator is provided having a terrain and obstacle warning envelope having a lower boundary formed according to the lesser of the current aircraft flight path angle and the obtainable climb gradient.