Abstract: A gas turbine engine control system according to an exemplary aspect of the present disclosure includes, among other things, an automatic control operable to control a gas turbine engine. The gas turbine engine control system further comprises a module operable to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure of the automatic control. The exemplary gas turbine engine control system may further comprise a fuel flow meter to sense a fuel flow to the engine, a fuel control to control the fuel flow to the engine, and the module in electrical communication with the fuel flow meter to fix the fuel control in response to one of the multiple of pre-determined modes.

Abstract: A gas turbine engine control system includes a module operable to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure of an automatic control.

Abstract: A thin flat disc with an orifice or orifices to size and control electron and other charged particulate beams. The disc is made of electrically conductive chemical vapor deposition (CVD) diamond. In addition the disc contains one or more high precision fine to ultra-fine orifices.

Abstract: A method for automating a landing maneuver for an aircraft, comprising the steps of generating an approach profile comprising an initial approach fix (IAF), a flight path, a landing decision point, a balked landing route, a pre-landing point, and a landing point, engaging an automated approach system to access the approach profile, receiving periodic position data of the aircraft, comparing the position data to the approach profile to compute a plurality of deviations each time the position data is received, outputting the plurality of deviations to a display, converting the plurality of deviations into a plurality of control commands, and maneuvering the aircraft in response to the control commands along the flight path.

Abstract: A method for automating a takeoff maneuver for an aircraft, comprising the steps of generating a takeoff profile comprising a takeoff point, a flight path, and a takeoff decision point (TDP), engaging an automated takeoff system to access the takeoff profile, receiving periodic position data of the aircraft, comparing the position data to the takeoff profile to compute a plurality of deviations each time the position data is received, outputting the plurality of deviations to a display, converting the plurality of deviations into a plurality of control commands, and maneuvering the aircraft in response to the control commands along the flight path.

Abstract: A method of automated scan compensation in a target acquisition system for reducing areas of potential threat surrounding an aircraft. The target acquisition system is located on an aircraft and adapted to receive data from a plurality of sensors. The target acquisition system includes a scanning device with adjustable scan limits for scanning a desired area in the vicinity of the aircraft. The method involves determining the aircraft's current position, altitude, and heading. The terrain in the vicinity of the aircraft is then scanned and a line of sight between the aircraft and the scanned terrain is determined. Changes in the terrain which prevent other areas of the terrain in the vicinity of the aircraft from being scanned are also determined. The method then involves determining adjustments to the scan limits on the target acquisition system to reduce the size of the unscanned areas, and adjusting the scan limits as the aircraft flies over the terrain.

Abstract: Taxi and slope landing symbology for a helicopter having a main rotor drive shaft and a main rotor hub defining a hub moment, wherein the main rotor drive shaft and the main rotor hub have hub moment limits. The taxi and slope landing symbology comprises a first symbol for providing a symbolic representation of the hub moment limits, and a second symbol for providing a dynamic symbolic representation of the hub moment, wherein the second symbol is disposed in combination with the first symbol to provide a visual cue of the hub moment relative to the hub moment limits.

Abstract: When an engine malfunctions in a multi-engine aircraft, movement of the throttle(s) associated with the other operative engine(s) is inhibited.