Pouillot, Laurent Pierre Paul

An attachment assembly (10) for attachment of a tail boom (3) to a rear fuselage of a rotorcraft (1), comprising: a ring-shaped interconnecting carrier (10c) with a predetermined wall thickness; a predefined number of shear load transfer bodies (15a) connected at first discrete angular positions (17a, 17b, 17c, 17d) to the interconnecting carrier for transfer of loads essentially in circumferential direction (10e) of the interconnecting carrier; and a plurality of axial load transfer bodies (13b) connected to the interconnecting carrier at second discrete angular positions (17e, 17f, 17g) for transfer of loads in a direction (10f) essentially perpendicular to both the predetermined wall thickness (10d) and the circumferential direction, wherein the predefined number of shear load transfer bodies and the plurality of axial load transfer bodies extend from the interconnecting carrier at least approximately in the direction essentially perpendicular to both the predetermined wall thickness and the circumferential direction.

The present embodiments relate to a communication system (200) for an aircraft, comprising a plurality of radios (210) including at least a first radio (212) that is operable in an encrypted mode for transmitting/receiving encrypted audio signals, and a second radio (214) that is operable in a clear mode for transmitting/receiving unencrypted audio signals; an intercom system (220) that interconnects the plurality of radios (210), wherein the plurality of radios (210) is connected to the intercom system (220) via a plurality of communication lines (230); and a security module (240) that is configured to connect or disconnect selected ones of the plurality of communication lines (230) for inhibiting simultaneous transmission of an encrypted audio signal via the first radio (212) and an unencrypted audio signal via the second radio (214).

The invention is related to an adjustable spacer (1) for adjusting a spacing between a first component and a second component to a predefined distance, comprising: a support component (2) configured to be rigidly mounted to the first component; a spacing component (3) movably mounted to the support component (2) for adjusting positioning of the support component (2) relative to the second component; and a fixing component (4) configured for locking the spacing component (3) on the support component (2) after the positioning of the support component (2) relative to the second component at the predefined distance.

The present embodiments relate to a ground support equipment system (150) for use on an aircraft (100), comprising: a plurality of ground support equipment modules (192, 194) mountable to associated aircraft components (193, 195) of an aircraft (100) parked on ground (105) for protecting the associated aircraft components (193, 195) from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions; and a plurality of connecting means (200) adapted to connect the plurality of ground support equipment modules (192, 194) to at least one common interconnection device (212) for rendering mounting of the plurality of ground support equipment modules (192, 194) to the associated aircraft components (193, 195) discernible for a pilot of the aircraft (100).

The invention relates to a rotorcraft (1) comprising: rotor blades (1b, 1h) with rotor blade tips (6b, 6h) which form a virtual blade tip circle upon rotation around a rotor head (1d); at least one light returning unit (9b, 9h) provided on at least one of the rotor blade tips; and a blade tip illumination device (7) comprising at least one light source (7a, 7b) configured to emit a light beam (8a, 8b) toward at least a portion of the virtual blade tip circle for illuminating the at least one light returning unit; wherein the at least one light returning unit is adapted to return light in response to being illuminated with the emitted light beam, the returned light having a wavelength suitable for detection by a night-vision device (11) and forming on the virtual blade tip circle at least a luminous ring segment (12) visible via the night-vision device.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

The present embodiments relate to a load carrying assembly 190 for carrying a load with a rotary wing aircraft 100. The load carrying assembly 190 includes a cargo cable 175 and a load engaging system 200. The cargo cable 175 may have a first end 176 that is attachable to a hoist 170 or a cargo hook arrangement 180. The load engaging system 200 may include a first attachment 230 that is attached to the second end 177 of the cargo cable 175, a second attachment 235 that is adapted for receiving a load, a connecting apparatus 240 that connects the first attachment 230 with the second attachment 235, and at least two first and second thrust producing devices 210a, 210b, 220a, 220b that are attached to the connecting apparatus 240 and produce thrust in a direction that is orthogonal to the cargo cable extension.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …