A lighting system for an aircraft having at least one rotationally mounted propeller assembly that includes hub and a plurality of rotor blades extending radially away from the hub includes a light source and an optical element. The light source is mounted within the hub and is configured, upon being energized, to emit light in a first direction. The optical element is mounted within the hub and is disposed to receive the light emitted by the light source and is configured, upon receipt of the light, to redirect the light radially outward from the hub so that the light reflects off the rotor blades.

An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

An energy absorbing arrangement may comprise an inner barrel comprising a centerline axis, an outer barrel, a webbing extending between the outer barrel and the inner barrel and configured to be offset from a nose lip by a distance, the webbing being folded together to form a plurality of folds, the plurality of folds being stitched together via a plurality of stitches, wherein the webbing is configured to absorb energy from an object in response to the object passing through the nose lip and applying a force to the webbing.

An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.

A panel structure for an aircraft with at least one composite layer, and at least one net-shaped layer attached to the composite layer, wherein the net-shaped layer has a material suitable to improve the impact resistance of the panel structure. The net-shaped layer can be used to attach two composite layers. Alternatively, the net-shaped layer can be attached to a surface of one composite layer. In this last case, the net-shaped layer may be joined to a laminate sheet material and filled with a foam material. An impact reinforced panel structure is disclosed capable of withstanding any impact, such as a blade release, or a bird strike, without substantially modifying the manufacturing process.

A helicopter anti-bird-collision system including a search light (2) and a control unit (35) which is configured for operating the search light (2) in a flash light mode by switching the search light periodically on and off.

The present invention is a helicopter lighting system. In particular, the present invention is directed to a helicopter lighting system with light that is directed toward a helicopter's rotors to deter bird strikes. The helicopter lighting system preferably has at least one light mounted on the helicopter's tail aimed at the tail rotor, where illumination from the at least one light comprises ultraviolet light between 300 and 400 nm in wavelength and the at least one light flashes at a pre-determined frequency, preferably between 1 Hz and 3 Hz. The light system further preferably comprises at least one roof light mounted on the roof, where illumination from the roof light shines on the main rotor and vertical shaft of the helicopter. The lighting system also preferably has a belly light mounted on the belly of the helicopter.

The present invention is an aircraft lighting system. In particular, the present invention is directed to an aircraft lighting system with light that is directed toward an aircraft's engines to deter bird strikes. The lighting system for a jet-powered aircraft has at least one light mounted on an aircraft fuselage aimed at an engine inlet of an engine nacelle of the aircraft. The illumination from the light comprises ultraviolet light between 300 and 400 nm in wavelength and the light flashes at a pre-determined frequency preferably between 1 and 3 Hz. Additional lights can be mounted on the engine nacelles to illuminate outer engine nacelles. Preferably, the engine of the aircraft also has blades coated in fluorescent or iridescent paint to increase the reflectivity of the blades to further illuminate the blades of the engine. The lighting system preferably automatically illuminates the engine inlets during take-off and descent.

In an aircraft, the airframe includes a windshield frame, with an energy attenuating windshield corner support extending across a corner of the windshield frame. The energy attenuating windshield corner support is configured to deform upon an impact to a windshield disposed in the windshield frame. This energy attenuating windshield corner support may be shaped and/or sized to enable, and/or comprised of a material that enables, the aircraft windshield corner support to deform upon the impact to the windshield disposed in the windshield frame, attenuating energy of the impact to the windshield disposed in the windshield frame.

An impact-energy tolerant method and structures for impact-energy absorption and penetration resistance are disclosed. A body comprising a body end, and a fiber band comprising supplemental attachment sites located between an inner wall and an outer wall of the body end.