An aircraft wing inspection system includes a housing, a light source, a camera, and a display device. The housing is adapted to be mounted on an aircraft fuselage. The light source is disposed within the housing and is operable, upon being electrically energized, to emit a light beam. The camera is disposed within the housing and is configured to capture images of the aircraft wing, convert the captured images to digital image data, and transmit the digital image data. The display device is disposed remote from, and is in operable communication with, the camera. The display device is configured to receive the digital image data transmitted from the camera and to render the captured images.

A system and method for sensing height above landing surface for an aircraft, processing that sensed height information to provide information useful to the aircraft pilot for assisting with the landing and flare-to-land maneuver, and providing the processed information in a peripheral vision display indicating landing conditions sequentially without interfering with pilot vision and focus on the landing area.

A system and method for sensing height above landing surface for an aircraft, processing that sensed height information to provide information useful to the aircraft pilot for assisting with the landing and flare-to-land maneuver, and providing the processed information in a peripheral vision display indicating landing conditions sequentially without interfering with pilot vision and focus on the landing area.

The display system has a three-dimensional and curved display surface made up of a single electronic display screen or several joined electronic display screens, the display surface having at least one main zone dedicated to a pilot and suitable for being located in front of said pilot, the main zone being substantially planar or concave, and at least one lateral zone associated with each main zone, each lateral zone being concave and laterally extending the associated main zone.

The display system has a three-dimensional and curved display surface made up of a single electronic display screen or several joined electronic display screens, the display surface having at least one main zone dedicated to a pilot and suitable for being located in front of said pilot, the main zone being substantially planar or concave, and at least one lateral zone associated with each main zone, each lateral zone being concave and laterally extending the associated main zone.

A bicycle system with omnidirectional viewing having front-facing, stereoscopic video camera devices relying on computer vision. The front-facing, stereoscopic video camera devices positioned on the bicycle help identify, classify, and recommend a safe trajectory around obstacles in real-time using augmented reality. The bicycle system details safety-related and guidance-related information.

A bicycle system with omnidirectional viewing having front-facing, stereoscopic video camera devices relying on computer vision. The front-facing, stereoscopic video camera devices positioned on the bicycle help identify, classify, and recommend a safe trajectory around obstacles in real-time using augmented reality. The bicycle system details safety-related and guidance-related information.

A flight control system includes a pilot control module configured to receive commands from a pilot, a flight control module operable to transmit an instruction to change at least one operating condition of an aircraft, and a flight control computer in communication between the flight control module and the pilot control module. The flight control computer is configured to receive a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer may instruct the flight control module to transmit an instruction to change a first operating condition of the aircraft and instruct the flight control module to transmit an instruction to change a second operating condition of the aircraft to at least partially offset the expected change to the second flight characteristic.

A flight control system includes a pilot control module configured to receive commands from a pilot, a flight control module operable to transmit an instruction to change at least one operating condition of an aircraft, and a flight control computer in communication between the flight control module and the pilot control module. The flight control computer is configured to receive a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer may instruct the flight control module to transmit an instruction to change a first operating condition of the aircraft and instruct the flight control module to transmit an instruction to change a second operating condition of the aircraft to at least partially offset the expected change to the second flight characteristic.

The present invention relates to A power margin indicator device constituting a first limitation indicator for a rotorcraft, for providing a pilot of said rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of said rotorcraft as a function of flying conditions, said device comprising: input means for collecting input data corresponding various operating parameters of said at least one engine and of said MGB; calculation means connected to said input means, said calculation means serving to determine a collective pitch margin for the blades of a rotor of said rotorcraft; and display means presenting said collective pitch margin.