Abstract: The invention relates to SiC-bound diamond hard material particles, a porous component formed with SiC-bound diamond particles, methods for producing same and the use thereof. Diamond hard material particles and components have a composition of 30 vol. % to 65 vol. % diamond, 70 vol % to 35 vol. % SiC and 0 to 30 vol.

Abstract: The invention relates to SiC-bound diamond hard material particles, a porous component formed with SiC-bound diamond particles, methods for producing same and the use thereof. Diamond hard material particles and components have a composition of 30 vol. % to 65 vol. % diamond, 70 vol % to 35 vol. % SiC and 0 to 30 vol.

Abstract: In a multicore type error correction processing system which can simultaneously cope with a plurality of error correction methods and a plurality of code lengths, an interconnect part 11 has a barrel shifter which extends across a plurality of error correction processing parts 12a-12c. An error correction process can be selectively performed by collectively using a group of the plurality of the error correction processing parts 12a-12c or by individually using each of individual error correction processing parts 12a-12c in response to interconnection configuration information. With this structure, the plurality of the error correction processing parts 12a-12c are collectively used if computation resources are insufficient and an idling error correction processing part is assigned to another error correction process if computation resources are excessive.

Abstract: The present invention relates to a method of fabricating a mold core (5) for making hollow parts (11) based on a composite material including fibers, fabrics, or textiles together with a resin, the method consisting in mixing a filler material (1) and a binder material (2) in order to obtain a uniform mixture of materials, and in solidifying, compacting, and shaping the resulting mixture in order to constitute said core, the method being characterized in that it further consists in introducing into the mixture at least one complementary material (3) that is expandable under the effect of heat or by applying another physical or chemical principle, and in mixing said materials (1, 2, 3) in order to obtain a uniform distribution of the complementary material (3) in the mixture.

Abstract: In a multicore type error correction processing system which can simultaneously cope with a plurality of error correction methods and a plurality of code lengths, an interconnect part 11 has a barrel shifter which extends across a plurality of error correction processing parts 12a-12c. An error correction process can be selectively performed by collectively using a group of the plurality of the error correction processing parts 12a-12c or by individually using each of individual error correction processing parts 12a-12c in response to interconnection configuration information. With this structure, the plurality of the error correction processing parts 12a-12c are collectively used if computation resources are insufficient and an idling error correction processing part is assigned to another error correction process if computation resources are excessive.

Abstract: A method of fabricating components (23) based on fiber-reinforced plastics material, in particular with the help of a wrapped mold core (10), includes the following steps: a) fabricating the mold core (10); b) wrapping the mold core (10) with a wrapper (14) that withstands resin; c) applying fiber semi-finished products (16) and introducing resin to create the plastics component (23); and d) hardening the plastics component (23) under the effect of temperature; which method is improved by the fact that, under all circumstances, and during hardening in step d), substantial pressure equilibrium is established across the fiber semi-finished product (16, 20) between ambient pressure (pu) and the pressure (pk) inside the core. A device is also described.

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 composite element made from a preform of fiber-reinforced plastic material arranged around a core with a multi-layer thermoplastic foil between the preform and the core and a method for fabrication of such a composite element. At least one of the layers of said multi-layer thermoplastic foil has a different melting temperature from the melting temperature of at least one of the other layers.

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 present invention concerns an intermediate reinforced composite part composed of an assembly of at least two composite members (1,2,4,5) each comprising reinforcing fibres or fabrics and an impregnation matrix, said assembly comprising a bonding agent (3) ensuring a mechanical bond between said members, characterised in that the bonding agent (3) comprises at least one carbon nanotube (“Bucky Paper”) sheet.

Abstract: The present invention relates to a method of fabricating a mold core (5) for making hollow parts (11) based on a composite material including fibers, fabrics, or textiles together with a resin, the method consisting in mixing a filler material (1) and a binder material (2) in order to obtain a uniform mixture of materials, and in solidifying, compacting, and shaping the resulting mixture in order to constitute said core, the method being characterized in that it further consists in introducing into the mixture at least one complementary material (3) that is expandable under the effect of heat or by applying another physical or chemical principle, and in mixing said materials (1, 2, 3) in order to obtain a uniform distribution of the complementary material (3) in the mixture.

Abstract: A method of fabricating components (23) based on fiber-reinforced plastics material, in particular with the help of a wrapped mold core (10), includes the following steps: a) fabricating the mold core (10); b) wrapping the mold core (10) with a wrapper (14) that withstands resin; c) applying fiber semi-finished products (16) and introducing resin to create the plastics component (23); and d) hardening the plastics component (23) under the effect of temperature; which method is improved by the fact that, under all circumstances, and during hardening in step d), substantial pressure equilibrium is established across the fiber semi-finished product (16, 20) between ambient pressure (pu) and the pressure (pk) inside the core. A device is also described.

Abstract: An aircraft door arrangement, especially for an airplane, comprising a door; a door frame; a support arm with a pivoting axis on the door side, on which the door is mounted so as to swivel, and a pivoting axis on the frame side, on which the support arm is mounted so as to swivel on the door frame, whereby at least the pivoting axis on the door side is defined by two articulated joints positioned at a distance from each other in the vertical direction of the support arm, of which articulated joints at least one articulated joint has two bearings positioned at a distance from each other in the vertical direction; a pivoting drive that is arranged in the area of the support arm on the door side and that serves to swivel the door; and a driven element that is coupled to the pivoting drive and to the door and that transmits an actuating movement of the pivoting drive to the door.

Abstract: The invention relates to an aircraft door arrangement, especially for an aeroplane, said arrangement comprising a door, a doorframe, a supporting section with a pivotal axis (AD) on the door side, along which the door is pivotably positioned, and a pivotal axis (AF) on the frame side, along which the supporting section (8) is pivotably positioned on the door frame. At least the pivotal axis (AD) on the door side is defined by two articulations (G1, G2) which are interspaced in the vertical direction (Y) of the supporting section (8), at least one (G1; G2) of said articulations comprising two vertically (Y) interspaced bearings (L1a, L1b). The inventive door arrangement also comprises a pivotal drive (10) which is arranged on the door side of the supporting section (8) and is used to pivot the door, and an output element (12; 14, 16) which is coupled to the pivotal drive (10) and the door and transfers an actuating movement of the pivotal drive (10) to the door.

Abstract: The invention relates to a process and an apparatus for the microsuspension polymerization of vinyl chloride in vessels whose contents are agitated predominantly by natural convection where, in a reactor having a ratio of height H to diameter D of H/D 2, which is equipped externally or internally with a heat exchanger provided with water and connected to a pumped circulation system provided with water, the introduction of the cooling water takes place in the upper third of the heat exchanger and the cooling water is conducted downward and is conducted away in the lower third of the heat exchanger.