Airbus Helicopters Deutschland Patente

The invention relates to a compound helicopter (1) comprising a fuselage (4), a main rotor (2), a fixed wing arrangement (5) with an upper wing (6) and a lower wing (7) joining at an interconnection region (11), a propeller (8a) mounted to the interconnection region (11), and a lateral boom (14a) connected to the lower wing (7). The main rotor (2) comprises rotor blades (2a, 2b) that form a main rotor disc (3) which defines a compound helicopter perimeter (3a). The fixed wing arrangement (5) is completely arranged within the compound helicopter perimeter (3a) with the upper wing (6) connected to an upper fuselage section (4d) and the lower wing (7) connected to a lower fuselage section (4c). The lateral boom (14a) extends behind the lower wing (7) in a longitudinal direction (1a), spaced apart from the fuselage (4), and is connected to a vertical fin (17a).

The invention relates to a rotorcraft (100) having a main rotor (110) with at least one main rotor actuator (114); a series actuator arranged upstream of the main rotor actuator; engines (180) for powering the main rotor; and a flight control system (160) for controlling flight operation in an AEO mode or in an AFR mode, comprising: a control logic (165) for pre-conditioning the series actuator upon entering the AFR mode for enabling rotorcraft control upon occurrence of an IFSD, wherein pre-conditioning of the series actuator comprises shifting a reduced nominal stroke range authorized for the series actuator stroke of the series actuator in the AEO mode into a reduced shifted stroke range authorized for the series actuator stroke of the series actuator in the AFR mode to enable authorization of an increased stroke range upon occurrence of an IFSD to provide sufficient control authority for a recovery maneuver.

The invention relates to a rotary wing aircraft comprising an upper primary skin (2c) that separates an aircraft interior region from an aircraft upper deck (6). The aircraft upper deck (6) comprises engine compartments (20a, 20b), a tail rotor drive shaft (12c) arranged therebetween, a firewall arrangement (10b, 10c, 10d), and a central bracket (33) that is rigidly attached to the upper primary skin (2c) below the tail rotor drive shaft 12c. The central bracket (33) provides central bracket lugs (34a, 34b) in the engine compartments (20a, 20b) above the firewall (10d). The engine compartments (20a, 20b) comprise inboard fixations (19a, 19b) with inner main mounting brackets (16a, 16b) adapted for being rigidly attached to engines (11a, 11b) and to inboard lateral mounts (72a, 72b) that attach the inner main mounting bracket (16a, 16b) with the central bracket lugs (34a, 34b).

The invention relates to a rotary wing aircraft with a fuselage that includes an upper primary skin (2c) which comprises a polymeric composite, and with an aircraft upper deck (6) arranged above the fuselage; wherein the aircraft upper deck (6) comprises an engine accommodating region (7) that accommodates at least one aircraft engine (11b) within a firewall arrangement that comprises at least one lower firewall (30b) arranged above the upper primary skin (2c) of the fuselage and spaced apart from the upper primary skin (2c); wherein the at least one lower firewall (30b) includes at least a lower firewall panel (40) and a high emissivity panel covering layer (43a) that covers the lower firewall panel (40) and comprises a high emissivity of at least 0.7; and wherein the high emissivity panel covering layer (43a) is facing the at least one aircraft engine (11b).

The invention relates to a swivel device (10) that is configured for connecting human and/or non-human cargo to a rotorcraft, comprising: a first mechanical coupling device (20) that is configured for being connected to the rotorcraft; a second mechanical coupling device (40) that is configured for being connected to the human and/or non-human cargo; and a swivel arrangement (30) that couples the first mechanical coupling device (20) with the second mechanical coupling device (40), wherein the swivel arrangement (30) provides for a primary load path (58) that is configured for load transfer between the second mechanical coupling device (40) and the first mechanical coupling device (20) in a normal operation mode, and a secondary redundant load path (59) that is configured for load transfer between the second mechanical coupling device (40) and the first mechanical coupling device (20) in an emergency operation mode.

The present technology relates to a rotary-wing aircraft with a fuselage that comprises a load carrying shell structure (210) and a load carrying stiffening member structure (220), wherein the load carrying shell structure (210) delimits an aircraft inner volume (123), and wherein the load carrying stiffening member structure (220) is arranged outside of the aircraft inner volume (123) on an outer surface (218) of the load carrying shell structure (210).

The invention relates to a skid-type landing gear (10) for a rotorcraft (1), which comprises at least two skids (11) which are connected to each other via at least two cross tubes (13). Each cross tube (14) is connected to the skids (12) via connecting components (17), each comprising a pressure plate (17b). The pressure plates (17b) are respectively attached to the skids (12) by means of vertical attachments (29) via a predetermined number of fasteners (22). The vertical attachments (29) are configured to enable load transfer from the cross tubes (14) to the skids (12) by tension in the predetermined number of fasteners (22) and by pressure between the pressure plates (17b) and skids (11).

The invention is related to a structurally bonded arrangement (6) comprising: an interconnecting component (7); a first component (8a) with a first connecting area (9a) that is rigidly connected to the interconnecting component (7); and a second component (8b) with a second connecting area (9b) that is structurally bonded to the interconnecting component (7) in an associated bonding area (10); wherein a plurality of separated sub-bondings (10b, 10d) is formed in the associated bonding area (10) between the second component (8b) and the interconnecting component (7).

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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 invention relates to an aircraft door (7) with an inner door space (7d); a door opening system (8) arranged at least partly in the inner door space, comprising: at least one locking device (8c) for locking the aircraft door in a locked state, actuation kinematics (8b) for actuating the at least one locking device, and at least one transmission rod (8d) coupling the actuation kinematics with the at least one locking device; wherein the at least one transmission rod is displaceable in the inner door space by means of the actuation kinematics for actuating the at least one locking device; and an anti-vibration device (9) mounted in the inner door space to the at least one transmission rod for absorbing vibrations of the at least one transmission rod, wherein the anti-vibration device is displaceable in the inner door space together with the at least one transmission rod.

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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).

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The invention relates to a ball lock pin (1000) comprising a pin body (210) with an inner accommodation (212) and at least one locking ball accommodation (262); a blocking pin (242) at least partly arranged in the inner accommodation and movable between a blocking position and a releasing position; at least one locking ball (222) movably arranged in the at least one locking ball accommodation and biased into a locking position by the blocking pin, if the blocking pin is in the blocking position, wherein the at least one locking ball is released for moving into an unlocking position if the blocking pin is in the releasing position; a primary spring element (272) arranged in the inner accommodation and biasing the blocking pin into the blocking position; and a redundant spring element (274) arranged in the inner accommodation and biasing the blocking pin into the blocking position.

A rotorcraft comprising a fuselage (2) forming at least one lower lateral fuselage compartment (2c) with at least a first fitting (10a), a second fitting (11c), and a third fitting (11d); and at least one non-retractable wheel-type landing gear (8) that comprises: at least one wheel (8a); a shock absorber (8b) with a shock absorber tube (8c) having an open end (8g) and an axially opposed closed end (8f), and a shock absorber rod (8d) telescopically mounted to the shock absorber tube via the open end; a first fixation (8p) provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation (8e) provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation (8i) provided close to the closed end on the shock absorber tube and connected to the third fitting.

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The invention relates to a method of operating a rotorcraft (1) with at least one main rotor and at least two engines, comprising: determining whether the rotorcraft (1) is operated in an AEO mode wherein the at least two engines are powering the at least one main rotor, or in a SEO mode wherein only a first engine of the at least two engines is powering the at least one main rotor while a second engine of the at least two engines is inactive; if the rotorcraft is operated in the SEO mode, monitoring the first engine to enable detection of engine failures; and if during monitoring of the first engine an engine failure of the first engine is detected (20), entering (30) into autorotation of the at least one main rotor upon detection of the engine failure by adjusting main rotor actuators of the at least one main rotor.

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The invention relates to a method of processing engine monitoring parameters in a rotorcraft that comprises at least one rotor and at least two engines for powering the at least one rotor in one of an All Engines Operative mode and a Single Engine Operation mode, wherein the engine monitoring parameters are at least indicative of power margins of one engine of the at least two engines of the rotorcraft, wherein the method comprises displaying an engine monitoring indicator (11) for the one engine of the at least two engines of the rotorcraft for visualizing a current performance state of the one engine; and, if the rotorcraft is operated in the Single Engine Operation mode, displaying a first graphical representation (13b) of a Single Engine Operation mode indicator (13) with the engine monitoring indicator (11) for visualizing that the rotorcraft is operated in the Single Engine Operation mode.

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The present technology is related to a structurally bonded arrangement (160) for structurally bonding a first component (210) to a second component (220). The structurally bonded arrangement includes a first connecting area (215) of the first component (210), a second connecting area (225) of the second component (220) that is spaced apart from the first connecting area (215) to form an interspace (230), and multiple interconnecting components (270) arranged across the interspace (230). First and second interconnecting components (270a, 270b) of the multiple interconnecting components (270) are structurally bonded separate from each other to the first connecting area (215) at separate first bonding areas (280a, 280b) and to the second connecting area (225) at separate second bonding areas (290a, 290b) thereby structurally bonding the first component (210) to the second component (220). The present technology is also related to a rotorcraft (100) with such a structurally bonded arrangement (160).

The invention is related to a rotorcraft (1) with at least one main rotor (1a) and a fuselage (2), comprising: a tail boom (2a) connected to the fuselage, the tail boom extending in a longitudinal direction (2c) from the fuselage toward a duct-type portion (7); a shroud (3) provided at the duct-type portion and forming a transverse duct (6) comprising a circumferential direction (14) and a longitudinal extension (6a) oriented at least essentially perpendicular to the circumferential direction and the longitudinal direction of the tail boom; and at least one ducted tail rotor (8a) rotatably arranged in the transverse duct; wherein the shroud comprises a first section (9) connected to the tail boom and a second section (10) spaced apart from the tail boom and diametrically opposed to the first section, the first section comprising an airfoil-like aerodynamic profile (9a).

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.

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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.

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).

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The invention relates to a rotary wing aircraft with a fuselage (2) that forms an aircraft interior region (2b), the fuselage comprising an upper primary skin (2c) that separates the aircraft interior region from an aircraft upper deck (6) arranged above the fuselage (2), the upper primary skin being mounted on top of a predetermined number of supporting beams; wherein the aircraft upper deck (6) comprises an engine accommodating region (7) with a firewall arrangement (10), the engine accommodating region accommodating at least one aircraft engine (11b) within the firewall arrangement (10) such that the firewall arrangement defines a fire proof separation at least between the at least one aircraft engine (11b) and the aircraft interior region (2b); and wherein the firewall arrangement (10) comprises at least a funnel-shaped lower firewall (10d) arranged between the at least one aircraft engine (11b) and the upper primary skin (2c) of the fuselage.

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