Abstract: The invention relates to a device for opening a passenger door (1) of an aircraft in case of emergency, which is fastened so it is manually pivotable on the fuselage (3) of the aircraft via a hinge and/or support arm configuration (2), an auxiliary-energy-operated emergency opening drive (4) being provided between the fuselage (3) and the passenger door (1), which automatically opens the passenger door (1) in accordance with an emergency control unit (5), the auxiliary energy for the emergency opening drive (4) being pyrotechnic energy, whose gas expanding inside an expansion chamber (6) after triggering by the emergency control unit (5) impinges the emergency opening drive (4) with pressure medium to open the passenger door (1), wherein said emergency opening drive (4) generates a rotational movement.

Abstract: A fuselage structure, particularly an aircraft door (1) of composite material comprising at least one panel (2) and at least one beam (3) mounted to each other and the panel (2) with the panel (2) being formed of at least one group of composite layers (5, 6, 20). The at least one beam (3) is provided at least at one of its respective ends (10, 11) with a flange (13) suitable for adhesive engagement with the at least one panel (2). The at least one group of composite layers (5, 6, 20) of the panel (2) is in form locking engagement with this flange (13) of the beam (3).

Abstract: A fuselage structure, particularly an aircraft door (1) of composite material comprising at least one panel (2) and at least one beam (3) mounted to each other and the panel (2) with the panel (2) being formed of at least one group of composite layers (5, 6, 20). The at least one beam (3) is provided at least at one of its respective ends (10, 11) with a flange (13) suitable for adhesive engagement with the at least one panel (2). The at least one group of composite layers (5, 6, 20) of the panel (2) is in form locking engagement with this flange (13) of the beam (3).

Abstract: The invention relates to a device for opening a passenger door (1) of an aircraft in case of emergency, which is fastened so it is manually pivotable on the fuselage (3) of the aircraft via a hinge and/or support arm configuration (2), an auxiliary-energy-operated emergency opening drive (4) being provided between the fuselage (3) and the passenger door (1), which automatically opens the passenger door (1) in accordance with an emergency control unit (5), the auxiliary energy for the emergency opening drive (4) being pyrotechnic energy, whose gas expanding inside an expansion chamber (6) after triggering by the emergency control unit (5) impinges the emergency opening drive (4) with pressure medium to open the passenger door (1), wherein said emergency opening drive (4) generates a rotational movement.

Abstract: A device for locking a door kinematics system of the door of an airplane includes a control unit, an actuator for actuating a locking system and an automatic reset device. The control unit actuates the actuator as a function of the existence of a predetermined signal so that the actuator brings the locking system in a locking position. The reset device, if required, brings the locking system autonomously into a release position.

Abstract: A supporting arm of a passenger door of an aircraft, has a curved structure which forms hollow chambers and movably connects the passenger door to a frame on the fuselage. Receiving means one for the supporting arm for receiving connecting means which enable a movable connection on the one hand to the passenger door and a pivoting drive and on the other hand to the frame on the fuselage, so that the door is movable by means of the supporting arm on a linear-displacement path and a pivoting path. The structure of the supporting arm is formed from fiber composite, the structure-forming fiber composite being formed from individual structural elements. This fiber composite structure further improves the thermal insulation of the supporting arm and nevertheless achieves a further weight reduction of the supporting arm, while maintaining exacting structural safety requirements for the latter.

Abstract: A device for locking a door kinematics system of the door of an airplane includes a control unit, an actuator for actuating a locking system and an automatic reset device. The control unit actuates the actuator as a function of the existence of a predetermined signal so that the actuator brings the locking system in a locking position. The reset device, if required, brings the locking system autonomously into a release position.

Abstract: A supporting arm of a passenger door of an aircraft, has a curved structure which forms hollow chambers and movably connects the passenger door to a frame on the fuselage. Receiving means one for the supporting arm for receiving connecting means which enable a movable connection on the one hand to the passenger door and a pivoting drive and on the other hand to the frame on the fuselage, so that the door is movable by means of the supporting arm on a linear-displacement path and a pivoting path. The structure of the supporting arm is formed from fiber composite, the structure-forming fiber composite being formed from individual structural elements. This fiber composite structure further improves the thermal insulation of the supporting arm and nevertheless achieves a further weight reduction of the supporting arm, while maintaining exacting structural safety requirements for the latter.

Abstract: An arrangement for controlling the closing and opening operation of an aircraft passenger door includes electromechanical actuators and manual actuators for moving the door and for actuating the various latching and locking mechanisms of the door, a door control unit, as well as an actuator control unit, an operating console, and sensors that sense position and status conditions of the door, all connected to the door control unit, a power supply, and power switches connected serially between the power supply and the actuator control unit. In an operating method, the door control unit controls the actuator control unit, and can switch all of the individual function steps for opening or closing the door selectively between being manually controlled and being electromechanically controlled. While the door can be actuated electrically, in the case of a malfunction or if desired by the operator, it can be operated fully or partly mechanically under a manual control.

Abstract: An arrangement for controlling the closing and opening operation of an aircraft passenger door includes electromechanical actuators and manual actuators for moving the door and for actuating the various latching and locking mechanisms of the door, a door control unit, as well as an actuator control unit, an operating console, and sensors that sense position and status conditions of the door, all connected to the door control unit, a power supply, and power switches connected serially between the power supply and the actuator control unit. In an operating method, the door control unit controls the actuator control unit, and can switch all of the individual function steps for opening or closing the door selectively between being manually controlled and being electromechanically controlled. While the door can be actuated electrically, in the case of a malfunction or if desired by the operator, it can be operated fully or partly mechanically under a manual control.

Abstract: A door system, particularly for a passenger plane, includes bearing and guiding device which operates between the door leaf and the door frame, as well as a lifting device which is arranged between the bearing and guiding device and the door leaf. The lifting device moves the door leaf at the end of the closing movement transversely to the moving path (B) of the guiding device with a form-locking engagement with door-frame-fixed receiving elements into the completely closed position and, at the start of the opening operation, in the opposite lifting direction (A) out of the form-locking engagement. The lifting device contains lifting kinematics for the control of the door blade lifting movement and an assigned lifting drive.

Abstract: A carrier membrane supports area covering solar cells and, preferably, is used for energy supply on a spacecraft. The membrane is stretched in a frame between two opposite sides and consists of plastic sheeting covered by a fiber-reinforced plastic fabric. To save weight, prevent insulation problems and thereby increase service reliability, the fabric is made of plastic reinforced with aromatic polyamide fibers in the form of woven crossing bands. The bands extend in the direction in which the membrane is stretched and transversely of the stretched direction.

Abstract: A force or load transmitting connecting element is provided at its ends w bolt eyes for receiving bolts which secure the connecting element to another structural component also provided with complementary bolt eyes or for securing a wing to an aircraft body. The bolt eyes must be capable of taking up compression and/or tension loads. For this purpose at least one reinforcing bridging web is located between at least two bolt eyes. The bridging web extends with its main plane perpendicularly to the central axes of the bolt eyes and loops at least partially around at least one of the bolt eyes. The bolt eyes are constructed as metal bushings. Thus, the bridging web braces the bolt eyes relative to each other.

Abstract: A connecting element for securing a rotor blade to the rotor hub of a helicopter rotor comprises at least two components arranged at an angle relative to each other. At least one component extends outside the boundary of the other component on both sides of the other component. Slots are arranged in at least one of the components and these slots extend substantially toward the shearing center or rather toward the central shearing axis. Additionally, each connecting element has a flattened zone adjacent to the rotor hub to function as a flapping hinge. The connecting element also functions as a lead-lag hinge and as a torsion hinge.

Abstract: The neck of a hingeless helicopter rotor wing blade is provided with a damping device effective to dampen lead-lag movements of the rotor wing blade. For this purpose the damping device comprises at least two stiff plates secured to opposite sides of the blade neck by a plurality of elastomeric members glued or bonded to the respective stiff plate and to the blade neck at spaced intervals. The difference of deformation between the stiff plates and the blade neck causes a deformation of the individual members in directions substantially across the longitudinal blade direction (in lead-lag plane). The spacings between adjacent members are located where the damping action is inherently low.

Abstract: A low temperature tank is suspended in an outer shell or container by a pality of straps of fiber compound materials. Each strap comprises a plurality of individual strap elements arranged in series. The strap elements are made of different fibers whereby the strap element closest to the tank is made of a fiber material having the lowest heat expansion coefficient as compared to the heat expansion coefficient of the other elements of a strap further away from the tank. Preferably the strap elements are thermally insulated from each other. In that case the strap elements need not necessarily be made of fiber materials having different heat expansion coefficients.

Abstract: A laminar panel assembly which is particularly useful in space vehicles for contact with solar cells includes a first and a second cover layer, a supporting core structure interposed between the cover layers and at least one force infeed element disposed within the core structure between the cover layers. The force infeed element includes at least one solid central piece for punctiform load infeed, and shear webs extending from the central piece radially outwardly in a branched formation such that the number of shear webs increases with increasing radial distance from the central piece.