Airbus Helicopters Deutschland

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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