Messerschmitt-boelkow-blohm Gesellschaft MIT Beschraenkter Haftung

Messerschmitt-bolkow-blohm Gmbh

Messerschmitt-boelkow-blohm Gmbh

Messerschmitt-bolkow-blohm Gesellschaft MIT Beschrankter Haftung

Wolfgang Buchs

Horst Bansemir

Albert Seidel

Werner Malburg

Franz Nowak

Rudolf Woerndle

Dieter Braun

Andreas Kirchner

Martin Mueller

Rolf Staedtler

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. The bands extending in the stretched direction provide greater surface coverage than the bands extending transversely to

Solar cell carrier membrane comprising a fabric composed of plastic

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.

Load transmitting connecting element with bolt eyes

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.

Hingeless rotor, especially for a helicopter

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.

Elastomeric damping device especially for the neck of helicopter wing

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.

Suspension system for a low temperature tank

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.

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Valley, Germany

Wolfgang Buchs