Airbus Helicopters Deutschland Patente

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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 present embodiments relate to a guided missile 100 with a sleeve-shaped missile body 105, at least one engine 300 for producing forward thrust, at least one flight direction control device 107, and at least one aerodynamic extension 106. The least one flight direction control device 107 is rotatably mounted to a top area 103 and/or a bottom area 104 of the sleeve-shaped missile body 105 for adjusting a flight direction 113, 114 of the guided missile 100. The least one aerodynamic extension 106 comprises an aerodynamic cross-sectional shape 112a, 112b, 112c that is arranged on a left-hand side 101 and/or a right-hand side 102 of the sleeve-shaped missile body 105.

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.

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The invention is related to a rope ladder (8) comprising: a first ladder step connecting element (17) that is mounted to a first braided rope (10), a second ladder step connecting element (17) that is mounted to a second braided rope (11), and a ladder step (12a) that couples the first ladder step connecting element (17) with the second ladder step connecting element (17); wherein the first ladder step connecting element (17) is braided into the first braided rope (10) and the second ladder step connecting element (17) is braided into the second braided rope (11), and wherein the ladder step (12a) fixes the first ladder step connecting element (17) in the first braided rope (10) and the second ladder step connecting element (17) in the second braided rope (11).

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The invention is related to a method of repairing a sandwich component (1) having a honeycomb core (2) with an associated core height, which is arranged between a first cover plate (1 b) and a second cover plate (1d), said sandwich component (1) comprising a damaged area (3) including a cover plate crack of the first cover plate (1b) and a deterioration of said honeycomb core (2) adjacent to said cover plate crack, wherein a helically rolled-up repair element (6) in compressed form is introduced into said honeycomb core (2) through said cover plate crack. The invention is further related to such a helically rolled-up repair element (6).

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The present embodiments relate to a door 200 that is adapted to separating two environments 202, 204 with different pressures and to an aircraft 100 with such a door 200. The door 200 may include a door leaf 210, a door frame 220 having a door stop 225 with a first portion of a round shaped interface 227, and an actuating system 290 having a latch element 230 with a second portion of the round shaped interface 237. In the latched state, the difference between the pressures puts a pressure 215 on the door leaf 210 such that the first and second portions of the round shaped interface 227, 237 engage with each other. The door leaf 210 may move at a movable connection 235 with latch element 230, thereby performing an adjustment 295 of the position of the door leaf 210 relative to the door frame 220.

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The present invention relates to a compound helicopter 1 with braced wings 5a, 5b in joined-wing configuration and a fuselage 4 that extends along a longitudinal axis 1a, a wheel-type main landing gear 10 in tandem configuration with a first main landing gear 10a and a second main landing gear 10b which are pivotally mounted in a lower fuselage section 4e of the fuselage 4 and aligned on the longitudinal axis 1a, and a wheel-type lateral landing gear 11 with a first lateral landing gear 11a and a second lateral landing gear 11b which are pivotally mounted to the braced wings 5a, 5b.

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The invention refers to a vibration absorber device (22) for generating a force for absorbing vibration in a structure (12), comprising a base (18) for attaching the vibration absorber device (22) to the structure (12), a first mass element (14), a second mass element (26), a first spring element (16) connected between the base (18) and the first mass element (14), a second spring element (28) connected between the first mass element (14) and the second mass element (26), and an actuator (20) configured to move the first mass element (14) relative to the second mass element (26).

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The present embodiments relate to a rotorcraft 100, and, more particularly, to an apparatus for transmitting a mechanical control signal in a rotorcraft 100 from a point of introduction to a point of application. The apparatus may include a flexible kinematics element 200, 405, a control signal transmitter 406, 407, 408, and an interface element 430 that is coupled between a linear control signal conveyor 201 of the flexible kinematics element 200, 405 and the control signal transmitter 406, 407, 408. The interface element 430 may linearize a motion associated with the mechanical control signal at the input and/or output interface of the linear control signal conveyor 201 of the flexible kinematics element 200, 405.