Abstract: A system includes a communications system and at least one processor coupled with the communications system and with a non-transitory processor-readable medium storing processor-executable code. The communications system is configured to receive measured air data from an air sensor system and receive flight data from a flight monitoring system. The air data is indicative of at least one air characteristic of an environment surrounding an aircraft. The flight data is indicative of at least one flight characteristic of the aircraft. The processor-executable code causes the at least one processor to detect a failed state of the air sensor system based on the measure air data and the flight data, estimate air data in response to detecting the failed state of the air sensor system, and provide the estimated air data to at least one of a display device and an automated flight control system.

Abstract: A system, device, and method for presenting aircraft requirements are disclosed. The aircraft requirements presentation system could include a source of maintenance data; an aircraft system(s); an input device; a processing unit (PU); and a display unit. The PU may be configured to acquire maintenance data; identify one or more schedule maintenance actions due at the present time; generate command data to a disable specific functionality of the aircraft system(s); provide the command data to the aircraft system(s); generate an image data set representative of one or more page images, whereon each page there may be image of at least one maintenance strip indicating a maintenance action and at least one a count for the maintenance action; and present the image(s) on the display unit. In some embodiments, a maintenance strip could include a graphical user interface through which a pilot may enable the disabled functionality.

Abstract: Embodiments of the inventive concepts disclosed herein may provide visual and audible flight direction cues to the pilot of a helicopter to maintain an optimum energy sustaining profile to successfully perform an autorotation maneuver. From the moment the engine fails or fails to provide adequate power to the main rotor system, systems described herein provide airspeed, attitude, and altitude guidance to the pilot to intercept and fly the correct path for a successful autorotation entry and autorotation descent. The system displays specific cues as the helicopter approaches the determined flare altitude and guides the pilot through the autorotation flare and minimum rate of descent touchdown.

Abstract: A present novel and non-trivial system, device, and method for generating surface information presentable on a display unit is disclosed, where the surface information may be presented to draw a viewer's attention to threatening terrain location within a targeted area. An image generator (“IG”) may be configured to receive navigation data; receive search data representative of at least a reference location, a targeted area, and a pattern comprised of a plurality of ground tracks; retrieve object data representative of object cell elevations of the targeted area; determine threat data representative of a threat level for each object cell; and generate an image data set representative of an image comprised of one or more threat-based search area location highlighters and/or one or more threat-based ground track location highlighters. The reference location could be comprised of a search pattern datum or a commencement search point.