135 results about "Multi-function structure" patented technology

Multifunctional structures and methods of manufacturing multifunctional structures which function as both electronic devices and load-bearing elements are disclosed. The load-bearing elements are designed to have electronic functionality using electronics designed to be load-bearing. The method of manufacturing the multifunctional structure comprises forming an electronic element directly on at least one ply of arbitrarily shaped load-bearing material using conventional lithographic techniques and/or direct write fabrication techniques, and assembling at least two plies of arbitrarily shaped load-bearing material into a multifunctional structure. The multifunctional structure may be part of an aerospace structure, part of a land vehicle, pan of a watercraft or part of a spacecraft.

An on-chip redundant crack termination barrier structure, or crackstop, provides a barrier for preventing defects, cracks, delaminations, and moisture/oxidation contaminants from reaching active circuit regions. Conductive materials in the barrier structure design permits wiring the barriers out to contact pads and device pins for coupling a monitor device to the chip for monitoring barrier integrity.

The present invention relates to a headlight lamp (110) having a multifunction structure in which a lighting angle of a headlight of a vehicle is automatically and manually controlled based on a running speed of a vehicle, a brightness of a headlight of an opponent vehicle and a surrounding brightness of a vehicle. The headlight lamp (110) includes a plurality of high angle headlight filaments (115), capable of lighting for providing a high angle beam to a vehicle, a plurality of low angle headlight filaments (111) capable of lighting for providing a low angle beam to the vehicle, low angle headlight reflection covers (112) provided in the low angle headlight filaments (111) respectively, for thereby allowing the light from the low angle headlight filaments (111) to have a low beam pattern angle, and external connection terminals.

Disclosed herein are methods and devices for applying two or more mobilization fields in a microchannel using a multifunctional structure and manipulating particles and fluids based on more than one characteristic. Specifically, a fluidic channel comprising at least one metal structure having a coat comprising a conductive material, an insulative material, a semi-conductive material, or a combination thereof, is disclosed. Also disclosed are methods for manipulating or assaying a particle in a sample which comprises subjecting the sample to a fluidic channel comprising at least one metal structure having a coat comprising a conductive material, an insulative material, a semi-conductive material, or a combination thereof and inducing at least one mobilization field such as a magnetic field, an electroosmotic field, an insulative dielectrophoresis (iDEP) field, which iDEP field may be an iDEP trapping field or an iDEP streaming field, or a combination thereof.

A modular construction system that utilizes versatile construction components releasably attachable to one another, in virtually any desired direction, by use of one or more interconnect components positioned therebetween. Each construction component includes at least two inventive connective surfaces with a receiving region therein, while each interconnect component includes at least one coupling surface comprising multiple coupling elements capable of releasable frictional engagement with at least a portion of one or more receiving regions. The receiving regions, the interconnect components, and the coupling elements are sized and configured to (1) enable a first type of connection in which at least a portion of an interconnect component fits within and releasably connects overlapping connective surfaces of two construction components, and (2) optionally also enable a second type of connection, in which construction components are connected by an interconnect component that releasably engages with two or more proximal connective surfaces positioned and aligned in the same plane In one inventive embodiment, the receiving regions of the construction components are sized and configured to enable releasable coupling with male studs of conventional popular toy building blocks.

A method and apparatus relating to a multi-functional, structural circuit, referred to as a structural circuit, are disclosed. The method can include thermoforming a liquid crystal polymer (LCP) circuit with a structural element (215). At least one circuit component can be attached to the surface of the LCP circuit (220).

A process for fabricating a worked product or a monolithic multi-functional structural element comprising aluminium alloy includes a hot working step and at least one transformation step by cold plastic deformation after the hot transformation step. At least two zones of the structural element have imposed generalized average plastic deformations and the imposed deformations are different by at least 2%. Structural elements can be fabricated, particularly for aeronautical construction, with properties that are variable while their geometric characteristics are identical to those of existing components. The process is economic and controllable, and properties can be varied for parts not requiring any artificial ageing.

This invention relates to a multifunctional structure for mitigating the effects of explosions and impeding the penetration of projectiles that is also highly effective at supporting structural (i.e. static) loads. By wrapping a tile in multiple layers of high-performance fabric, upon impact by a projectile additional tensile forces are created, aiding in the deceleration of the projectile. With added layers the tensile forces aiding projectile deceleration increase, resulting in a ballistic panel for use in multifunctional structural/armor systems having a lighter weight and greater stopping power than conventional armor systems in addition to functioning as part of a structure for supporting static loads.

The invention discloses a micro-truss structure carrying and thermal protection structure multi-objective optimization method, and belongs to the field of spacecraft instrumentation overall design andmultifunctional structure material design. A flow channel is introduced into a micro-truss sandwich structure, multi-objective optimization of temperature and stress is realized by thermal transfer and force transfer coupling calculation, and final design meets a design process and the lightest front edge structure of a design boundary. The problem of thermal mechanical coupling under practical working conditions is taken into full consideration, the influence of the temperature on strength is introduced, processing technology boundary conditions are considered, and optimum structural designis realized by an optimization algorithm. The method is simple and effective, optimum design can be realized by small calculated amount, and time and cost consumed by trial and errors are greatly reduced.

The invention provides a satellite-rocket integrated multifunctional structure aircraft for ground simulation and relates to the technical field of aerospace structure design. The satellite-rocket integrated multifunctional structure aircraft mainly comprises a propulsion subsystem, a common multifunctional solar panel, a common multifunctional service module and an effective load, wherein the effective load is arranged at the front end; the common multifunctional service module is located in the middle; the propulsion subsystem is located at the bottom of the common multifunctional service module; and the rear end of the system is also connected with an adapter of a vehicle. Through designing a series of novel concept multifunctional structures, such as the common multifunctional solar panel, a multifunctional structure cable, a multifunctional satellite-rocket adapter, a multifunctional structure battery and a multifunctional structure computer, deep integration of the structures is achieved, and the structure quality and redundancy volume of a system are effectively reduced, so that the payload ratio of a satellite is greatly improved, and the performance of the satellite-rocket integrated aircraft is greatly strengthened.

A cellular composite laminate structure (101) adapted for efficient energy absorption is provided along with the related use and method of manufacture. The structure uses rigid cellular core layers (102, 103) designed to remain rigid during impact loading to channel an imposed compressive force into plastic deformation of deforming sacrificial layers (116). The rigid cellular core layers (102, 103) are arranged such that they will interpenetrate during impact loading while the deforming sacrificial layers (116) are arranged such that they will impede interpenetration of the rigid cellular core layers (102, 103) and be subjected to tensile deformation only. The rigid cellular core layers (102, 103) and deforming sacrificial layers (116) can be formed to create two-dimensional cellular sheet or three-dimensional cellular topology structures. The deforming sacrificial layers (116) can be connected at various points to the rigid cellular core layers (102, 103) or can be connected only at the periphery of the overall structure. Higher strength, rigid materials are contemplated for the rigid cellular core layers (102, 103) while ductile materials are contemplated for the deforming sacrificial layers (116).

A multi-function structure of a plug-in universal IC card is to be promoted and the manufacturing cost is to be reduced. The body of the plug-in UICC is constructed of a molding resin. A tape substrate and a chip mounted on one side of the tape substrate are sealed in the interior of the molding resin. A side opposite to the chip mounting side of the tape substrate is exposed to the exterior of the molding resin and constitutes a surface portion of the plug-in UICC. Contact patterns serving as external terminals of the plug-in UICC are formed on the surface of the tape substrate exposed to the exterior of the molding resin. In the plug-in UICC whose body is constructed of molding resin, cracking of the chip can be prevented effectively even in the case where the chip is large-sized.

The invention discloses a preparation process of composite material corrugated sandwich plates, relating to a preparation process of corrugated sandwich plates. The invention aims at the problems thatthe current preparation process of the corrugated sandwich plates has long process period and high manufacturing cost and the problems that the current corrugated sandwich plate is made of metal materials and has high density, low specific strength and specific stiffness, and poor designability. The technology is that the surface of a core die is coated with a release agent; the upper die of thecore die is removed; a composite material core is paved on the outer surface of the upper die of the core die and matched with the outer surface of the upper die in shape; the die is closed to lead the composite material core to be formed, and the upper surface and the lower surface of the core die are respectively paved with a layer of panel, and then heated and pressurized and solidified with the heating temperature of being 160 DEG C-180 DEG C, the solidifying pressure being 0.5MPa-1.5MPa, and the solidifying time being 2.5h-3.5h; and demoulding is conducted to prepare the composite material corrugated sandwich plate. The invention has the advantages of short process period, low manufacturing cost, low density, and high specific strength and specific stiffness, and is mainly applied tothe super-light multifunctional structures in the fields of space flight and aviation and the like.

An inkjet print head including a chamber layer provided with an ink via, at least one ink chamber having a heater, and at least one ink channel connecting the ink via and the ink chamber; and a nozzle layer provided with at least one nozzle at a position corresponding to the ink chamber. The ink channel is provided with a multi-functional structure. The multi-functional structure performs functions of a filter and a restrictor.

The invention discloses a bearing and thermal protection integrated wing leading edge structure based on a micro-truss and belongs to the field of overall design of aircrafts and design of multifunctional structural materials. The bearing and thermal protection integrated wing leading edge structure is composed by arranging periodic structure units in a matrix mode; the periodic structure units are composed of upper face plates, lower face plates, flow channels and cores; the upper face plates and the lower face plates are each of a curved surface structure and correspond to the outer side face and the inner side face of a wing leading edge correspondingly; two flow channel wall plates extend from the left and right ends of each lower face plate in the core direction and then are connected, and the flow channel wall plates and the lower face plates together form the flow channels in an approximate triangular prism shape; and the two ends of the cores are fixedly connected with the upper face plates and the tops of the flow channels correspondingly. A micro-truss structure with the curvature is provided, the flow channels are introduced in the internal space of the micro-truss, under the situation that bearing is not affected, the effect of insulating the outside high temperature is achieved through cooling of internal fluids, a temperature control part is omitted, and thus theweight is reduced effectively.

Structural furring systems having enhanced drainage functionality are described. Furring strips can include a substantially planar face, substantially planar webs extending from edges of the face, and substantially planar legs extending from opposite edges of the legs. The face and/or legs include a row or array of protrusions configured to accommodate drainage and ventilation between the furring strip and an attached exterior cladding and/or building substrate. Furring strips can be manufactured by rolling a sheet metal such as steel. Additional embodiments include a furring tape configured to be affixed to a substantially flat face of a commercially available furring strip to provide similar drainage features.

The invention provides a multifunctional structure engineering loading test system. The system comprises a counterforce frame, a horizontal actuator unit, a loading beam, a vertical actuator unit, a first connection part, and a second connection part; one end of the horizontal actuator unit is hinged with the counter-force frame, and the other end is hinged with the loading beam; the first connection part is arranged on the loading beam, one end of the vertical actuator unit is connected with a second connection part, the second connection part is connected with the first connection part, thereby enabling the vertical actuator unit to make fitting curve movement on horizontal and vertical directions by following a loading point; the other end of the vertical actuator unit is connected withthe counter-force frame; the space between the loading beam and the counter-force frame is used for placing a test piece. The vertical actuator can follow the loading point to make fitting curve trajectory follow-up at the horizontal and vertical directions without a specific follow-up device, the structural part can conveniently perform pressing, bending and shearing and multiple composite typeloading test.

The invention discloses a film spacecraft, and belongs to the technical field of spacecraft design. The thin-film spacecraft comprises a multifunctional body platform, a thin-film propelling device, athin-film camera, a thin-film antenna, a thin-film battery piece, a thin-film sensor, a thin-film actuator and the like. The thin film propelling device stretches the six thin film sails into a hugeregular hexagon sail surface in a supporting rod stretching mode, flight power is obtained under the action of sunlight pressure, and the thin film camera can conduct high-resolution imaging on an observed target. According to the film spacecraft, multiple functions of thin film propulsion, thin film imaging, thin film communication, thin film power generation, thin film sensing and actuation andthe like are integrated; the film spacecraft can complete long-term voyage and large-range space flight tasks, the advantages of a thin film structure technology and a multifunctional structure technology are fused, through depth integrated design of the structure and loads, weight reduction, energy increase and function ratio improvement of the spacecraft structure are further achieved, and the requirements of spacecrafts for high performance and long service life can be better met.

A system for thermal management and structural containment includes a first battery cell having first and second terminal ends, and a first capillary void matrix disposed about an outer casing of the first battery cell.

A binder hold down page of multifunction construction. The hold down page is equipped with at least one article holder. The hold down page has a hold down surface opposite an outer surface, at least one of which is configured with an article holder of integral construction. A plurality of article holders can be provided, each for holding a different type of article. In one preferred embodiment, both surfaces are configured with at least one article holder. In another preferred embodiment, both surfaces are configured with a plurality of article holders. A hold down page constructed in accordance with the invention is retained along one side in a binder. The hold down page preferably also is releasably latched to the binder along a side of the page that is spaced from the side captured by the binder. Rings can be used to retain the hold down page in the binder.