Airbus Helicopters Deutschland Patente

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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.

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The present technology relates to an actuating system (200), including a latching and locking system, for an actuatable door (201). The actuating system (200) comprises a rotatable drive shaft (210), a rotatable latch shaft (225), a latching device (220), and a locking device (260). The latching device (220) includes at least two latches (230), a latch securing unit (300) for maintaining the at least two latches (230) in the latched position (335), and at least two lock lever counterparts (264, 266). The locking device (260) includes a lock lever (262) for engaging with the at least two lock lever counterparts (264, 266) to prevent the latch securing unit (300) from disengaging from the securing position (365), thereby locking the at least two latches (230) in the latched position (335) when the lock lever (262) is in a locked position (460).

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A rotary wing aircraft (100) that extends along an associated roll axis R between a nose region (101) and an aft region (102) is disclosed. The rotary wing aircraft (100) comprises a main rotor (120), a shrouded duct (140) that is arranged in the aft region (102) and that forms an inner air duct, wherein the shrouded duct (140) is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft (100); and a propeller (130) that is at least configured to propel the rotary wing aircraft (100) in the forward flight condition; wherein the propeller (130) forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller (130) is rotatably mounted to the shrouded duct (140) such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

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The invention relates to a battery and an electrical battery monitoring device comprising a first group of sensing switches (13) connected in series on a first monitoring circuit (11), said sensing switches, a second group of electrical sensing switches (14) connected in series on a second monitoring circuit (12), an input unit (16) to provide an input to the first and second monitoring circuits, a monitoring unit (17) to receive an output from the first and second monitoring circuits, wherein the monitoring unit receives at least two outputs from two measuring points of the first monitoring circuit, the two measuring points being separated by at least one sensing switch. The location of a defective battery cell may be early detected and precisely located by the monitoring of the battery cells in rows and columns.

A non-retractable wheel-type landing gear (8) for a rotorcraft, comprising: at least one wheel (8a); a shock absorber (8b) with a circumferential direction (8o), which is connected to the at least one wheel (8a) and comprises a shock absorber tube (8c) and a shock absorber rod (8d) telescopically mounted to the shock absorber tube (8c); a mounting arm (8e) extending laterally from the shock absorber tube (8c), the mounting arm (8e) being integrally formed with the shock absorber tube (8c) and adapted for attachment to a first fitting (14) of a rotorcraft; and a link fixation (8i) extending laterally from the shock absorber tube (8c), the link fixation (8i) being arranged in the circumferential direction (8o) of the shock absorber (8b) at an angle in a range from 45° to 120° with respect to the mounting arm (8e) and adapted for connection to a second fitting (15) of the rotorcraft.

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The present embodiments relate to an opening system 300 for a swiveling aircraft door 200, to a swiveling aircraft door 200 with such an opening system 300, and to an aircraft 100 comprising such a swiveling aircraft door 200. The opening system 300 includes a hinge bracket 410, a swivel mechanism 420, a hold-open latch 430, and an actuator 460. The hold-open latch 430 is in an unclamped state 432 when the swiveling aircraft door 200 is in the closed position 305 and latches in an over-centered state 434 when the swiveling aircraft door 200 is in the fully open position 308 to prevent the swiveling aircraft door 200 from returning to the closed position 305. The actuator 460 acts on the hold-open latch 430 that in turn acts on the swivel mechanism 420, thereby performing the opening and closing swivel movements of the swiveling aircraft door 200.

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A non-pressurized aircraft (100) comprising a hinged door with a door leaf (160) is disclosed. The non-pressurized aircraft (100) includes a canopy frame (370) with a canopy frame cross-section profile (375). The canopy frame cross section profile (375) has first and second canopy frame faces (371), (372) that are arranged at a predetermined angle (397) relative to each other, and a third canopy frame face (373) that is arranged between the first and second canopy frame faces (371), (372). The non-pressurized aircraft (100) further includes a hinge (220) that is entirely arranged within the outline (310) of the non-pressurized aircraft (100) and pivotally mounts the door leaf (160) to the third canopy frame face (373).

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A rotary wing aircraft (100) extending along an associated roll axis (R) between a nose region (101) and an aft region (102) and that comprises a fuselage (110) with a front section (112) and a rear section (114), the rotary wing aircraft (100) comprising: a main rotor (120) that is rotatably mounted at the front section (112), and a stabilizer arrangement (130) that is arranged at the rear section (114) in the aft region (102), wherein the rear section (114) extends between the front section (112) and the stabilizer arrangement (130) and comprises an asymmetrical cross-sectional profile (190) in direction of the associated roll axis (R).

The invention relates to a vehicle with at least one emergency exit system 5c, the at least one emergency exit system 5c comprising a jettisonable component 2i that is accommodated and locked in an associated frame structure 2l of the vehicle in normal operation mode and releasable from the associated frame structure 2l for being jettisoned from the vehicle in an emergency mode; and further comprising an emergency evacuation assistance device 9 that is adapted to assist in an emergency evacuation of the vehicle via the associated frame structure 2l in the emergency mode; wherein the emergency evacuation assistance device 9 is attached to the jettisonable component 2i such that the emergency evacuation assistance device 9 is deployed by means of the jettisonable component 2i when the jettisonable component 2i is jettisoned from the vehicle in the emergency mode.