9results about How to "Requires minimization" patented technology

The invention provides a high-strength complex-section cavity product cutting device which comprises a height adjusting mechanism, a radian adjusting mechanism, a follow-up mechanism and a cutting unit which are sequentially arranged from bottom to top. The cutting-off unit comprises a vertical cutting-off mechanism used for cutting off material belts on the two sides of the cavity product and a horizontal cutting-off mechanism used for cutting off a reinforcing rib structure in the middle of the cavity product. The invention further provides a cutting-off method which comprises the following steps: pre-punching and cutting off a process hole in advance in a material belt before rolling forming, and integrally cutting off a cavity product by adopting a regional secondary cutting-off mode after rolling forming. Follow-up continuous cutting of high-strength complex section type cavity products can be achieved on a rolling line, the cutting efficiency is high, the quality is good, the product rework rate is greatly reduced, and the service life of a cutter is remarkably prolonged; the device is flexible to use and high in universality, and can be adapted to cold-bending profiles with various different section types through replacement of the standard cutting head.

The application relates to the technical field of composite copper foil preparation, in particular to a PET composite copper foil with high peeling resistance and oxidation resistance and a preparation method thereof. The preparation method of the PET composite copper foil with high peeling resistance and oxidation resistance comprises the following steps: PET composite copper foil preparation and PET composite copper foil composite treatment. In the application, the inert structure of a PET surface is broken through corona treatment, and a polar group is introduced; then, a reinforcing liquid containing a silane coupling agent and nano silicon dioxide sol is coated to form a polar transition layer, so that the interface bonding force and the peeling resistance of the PET and the metal layer are improved through chemical bonding and physical anchoring; then, a layer of oxidation-resistant barrier metal layer is formed by using a physical vapor deposition method; then, the PET composite copper foil is placed in a copper-containing electrolyte, and electrolysis treatment is carried out by electrifying, so that a layer of copper foil is deposited, and the PET composite copper foil is obtained; and finally, the obtained PET composite copper foil is subjected to a surface treatment process.

The utility model relates to the technical field of robots, and discloses a distance measuring device and a robot. The transmitting assembly is arranged on the fixed base, and the transmitting assembly is configured to transmit detection light. The receiving assembly is arranged on the fixed base, and the receiving assembly is configured to receive the reflected light. The rotor assembly is arranged on the rotating support and rotates synchronously with the rotating support. The first circuit board is arranged on the fixed base, a stator winding is printed on the first circuit board, the stator winding and the rotor assembly are oppositely arranged, and when the stator winding is powered on, a magnetic field is generated to drive the rotor assembly to move so as to drive the rotating support to rotate relative to the fixed base. Compared with a stator winding which is relatively large in size and is wound on the stator teeth in the prior art, the distance measuring device provided by the embodiment of the utility model has the advantages that the stator winding is printed on the first circuit board, so that the size of the stator winding is greatly reduced, the thickness of the distance measuring device in the axial direction is particularly reduced, and the requirement of miniaturization of the distance measuring device is met.

This invention relates to an installation structure for a dual-screen automotive display and a vehicle thereof. The dual-screen installation structure includes an instrument panel body, a steering support body, and a dual-screen body. The instrument panel body has a first mounting point for assembly and fixation with the steering support body. The dual-screen body has a second mounting point corresponding to the first mounting point, enabling co-location of the instrument panel body, steering support body, and dual-screen body. The dual-screen body has a third mounting point for connection with the instrument panel body. This invention also provides a vehicle including the aforementioned dual-screen installation structure. This invention solves the problems of inconvenient assembly and maintenance, high cost, and inability to meet automotive lightweighting requirements in existing dual-screen installation structures, as well as the problem that the dual-screen structure cannot fit snugly against the instrument panel, affecting the overall interior quality.

This invention relates to the field of spacecraft thermal control technology, specifically to a fiber-reinforced flexible composite substrate for deployable space radiators and its preparation method. The method first involves cryogenically treating polyimide fibers with liquid nitrogen, weaving them into a fabric, and then subjecting them to gradient heating and surface carbonization to obtain a carbonized fiber-woven reinforcement. Simultaneously, boron nitride nanosheets and carbon nanotubes are covalently linked via amide bonds and coated with polydopamine to obtain a composite thermally conductive filler, which is then dispersed in polyimide resin. Finally, the resin is impregnated onto the surface of the reinforcement and the interior of the fiber bundles, and then cured to obtain the final product. In this invention, the carbonized layer of the fiber-woven fabric forms thermally conductive channels in both the warp and weft directions, and the composite thermally conductive filler forms a thermally conductive network within the matrix. Together, they construct a dual-network thermally conductive structure, giving the substrate excellent thermal conductivity, flexibility, and lightweight properties, making it suitable for high-power deployable spacecraft radiators.

The application discloses a single-component dealcoholized sealant and a preparation method and application thereof. The single-component dealcoholized sealant comprises the following raw materials in parts by mass: 80-120 parts of alkoxyl-terminated polydimethylsiloxane; 40-70 parts of surface-modified silica powder; 10-40 parts of flame retardant; 3-12 parts of flame retardant synergist; 3-12 parts of fumed silica; 5-40 parts of plasticizer; 0.5-10 parts of crosslinking agent; 0.5-10 parts of catalyst; and 0.5-10 parts of adhesion promoter. The structural formula of the alkoxyl-terminated polydimethylsiloxane is shown as formula (I): (R1O)3SiCH2CH2[(CH3)2SiO]nSi(CH3)2CH2Si(OR2)3 n Formula (I), wherein R1 and R2 are independently selected from C1-C10 alkyl, and n is 800-2200. The sealant has good storage stability, low hardness and high elongation, low viscosity, good extrudability, no corrosion to PC, fast curing speed, low density and good flame retardancy.

This invention relates to a thermoforming process for a rear longitudinal beam. This process designs the sidewall surface corresponding to the feature surface at the overlap of the automotive sheet metal rear longitudinal beam and sill beam as an arc shape. This effectively controls the material flow direction, reduces forming friction, and improves wrinkling and cracking phenomena caused by uneven material feeding at the overlap surface. Furthermore, it does not affect the feature surface shape of the rear longitudinal beam, thus achieving a significant improvement in the quality of the corresponding part. Without altering the feature surface shape of the rear longitudinal beam, the sheet metal thickness is reduced, meeting the requirements for automotive lightweighting.

The utility model provides a kind of system-level package chip of global satellite navigation, receiver and electronic equipment, can be reused in single antenna full-frequency positioning scene and double antenna three-frequency positioning directional scene, at least package has power module, clock module, GNSS receiver module, storage module and radio frequency front end module in chip, and peripheral interface is provided on chip;Power module is connected with clock module, GNSS receiver module and storage module respectively;Clock module is connected with GNSS receiver module;The input end of radio frequency front end module is connected with external single antenna or double antenna, and the output end of radio frequency front end module is connected with GNSS receiver module;GNSS receiver module is connected with storage module and peripheral interface.The utility model provides system-level package chip high integration, can satisfy the requirement of equipment to miniaturization.

The application provides a manufacturing method of a low-altitude aircraft landing gear cover plate, the landing gear cover plate comprising a cover plate body and an edge connecting part, the cover plate body is designed in a curved surface structure, the edge connecting part is distributed in a U shape along the left side, the right side and the bottom of the cover plate body, is smoothly and transitionally connected with the cover plate body and is in a plate structure, the edge is rounded, mounting holes are formed in the edge connecting part, mounting holes are also formed in the top of the cover plate body near the outer edge, carbon fiber SMC prepreg is used as a raw material for preparation during manufacturing of the landing gear cover plate, a mold is designed (the actual size of the mold cavity is 0.5%-1.0% larger than the actual size of the landing gear cover plate) and a process is controlled (precise control is performed on a forming process, temperature fluctuation is less than or equal to ±1℃, pressure fluctuation is less than or equal to ±0.1MPa, curing time error is less than or equal to ±5s, and a shaping tool cooling mode is adopted), so that the prepared landing gear cover plate is stable in size, easy to assemble and capable of guaranteeing the assembly quality of the low-altitude aircraft and flight safety.