12results about How to "Good load transfer" patented technology

The present invention relates to a high-strength aluminum alloy material for textile machinery and a preparation method thereof, belonging to the technical field of aluminum alloy preparation, and a preparation method of a high-strength aluminum alloy material for textile machinery, comprising the following steps: providing an ingot; preparing a reinforcing material using multi-walled carbon nanotubes, titanium powder and aluminum powder; applying nano copper to the reinforcing material using an ultrasonic vibration assisted electroplating method, and then combining it into the ingot, casting, and obtaining a modified aluminum plate; surface modification of the modified aluminum plate using a nickel-based material and a ceramic material, and obtaining a high-strength aluminum alloy material for textile machinery. Aluminum powder helps the carbon nanotubes to disperse evenly, and titanium powder acts as a buffer medium to improve the strength of the aluminum alloy by forming TiC in situ and forming Ti-Al intermetallic compounds at the interface; TiB2 material generates B2O3 at high temperature, and will not adhere to the mold during demolding in subsequent hot forging, thereby increasing the service life of the mold, and after cooling, B2O3 forms a layer of boric acid film to increase the wear resistance of the material.

The utility model relates to the technical field of kitchen pretreatment, in particular to a waterproof sealing type speed reducer which comprises a speed reducer body, a rack and a main shaft and further comprises a sealing kit arranged between the speed reducer body and a cover plate at the tail end of a spiral conveyor. The sealing kit comprises a packing sealing seat, a packing gland, a packing, a sealing gasket, a rear sealing seat and a lip-shaped framework sealing gasket, the packing sealing seat and the rear sealing seat are installed at the two ends between the speed reducer and a tail end cover plate of the spiral conveyor respectively, and the main shaft is arranged in the packing sealing seat and the rear sealing seat in a penetrating mode. The packing is arranged between the packing sealing seat and the main shaft, the packing gland is installed on the packing sealing seat and used for pressing the packing, and the lip-shaped framework sealing gasket is arranged between the rear sealing seat and the main shaft. And kitchen sewage can be effectively prevented from entering the speed reducer.

The invention relates to a low-cost and high-precision unmanned aerial vehicle control surface integral forming method, and belongs to the technical field of advanced composite material manufacturing. According to the method, the core force bearing part of the control surface of the unmanned aerial vehicle breaks through the traditional step-by-step manufacturing mode of composite material forming and metal piece post-assembly, and integrated compression molding of the metal connecting piece and the composite material control surface is achieved. Through the technical means of precise positioning of the metal connecting piece, compression molding and forming integration of the composite material and the like, integrated forming of the metal connecting piece and the composite material is achieved, and the problem that traditional control surface manufacturing needs separate part manufacturing, machining and manual assembling is solved. The prepared unmanned aerial vehicle control surface has the advantages of being high in qualified rate, high in forming precision, high in production efficiency, low in cost, good in structural integrity and the like.

The invention discloses a 3D bundled Ti-TiC reinforced aluminum-based composite material, comprising an aluminum matrix, in which a 3D bundled Ti-TiC multi-level configuration reinforcement is distributed, wherein the 3D bundled Ti-TiC multi-level configuration reinforcement is sequentially arranged from the radial center outwardly, including titanium wire, a dense TiC ceramic layer, and a TiC gradient composite layer, wherein the TiC particle size in the TiC gradient composite layer gradually increases outwardly along the radial direction; the invention also discloses a preparation method of the 3D bundled Ti-TiC reinforced aluminum-based composite material, comprising preparing the 3D bundled Ti-TiC multi-level configuration reinforcement, mixing surface copper-plated aluminum powder, anhydrous ethanol, and the 3D bundled Ti-TiC multi-level configuration reinforcement, then performing vacuum drying, placing the mixture into a graphite mold, sealing it, placing it in a hot pressing sintering furnace, sintering it, cooling it to room temperature with the furnace, and finally performing aging heat treatment to obtain the 3D bundled Ti-TiC multi-level configuration reinforced aluminum-based composite material.

The utility model discloses a wind turbine generator gearbox assembly which is characterized in that first annular grooves are formed in the two end faces of a first inner ring, first roller rings are coaxially embedded in the first annular grooves, one first roller ring rotationally abuts against the end face of a first check ring, and the other first roller ring rotationally abuts against the end face of a second check ring; a second annular groove is formed in the second inner ring, a second roller ring is coaxially embedded in the second annular groove, and the second roller ring rotationally abuts against the end face, away from the first inner ring, of the second check ring; the inner peripheral edge of the first inner ring extends to the inner peripheral side of the first center hole and is fixedly connected to the planet wheel assembly. A connecting part of an annular structure is connected between the first inner ring and the second inner ring, the connecting part is located in the second center hole, a third annular groove is formed in the outer circumferential wall of the connecting part, a third roller ring is coaxially embedded in the third annular groove, and the third roller ring rotationally abuts against the inner circumferential wall of the second center hole; and the stability and firmness of the whole structure in long-term use can be ensured.

The invention discloses a forming method of a composite material multi-way connector, and belongs to the technical field of composite material forming. A multi-way joint is decomposed into a first multi-way joint decomposition structure and a second multi-way joint decomposition structure, then the first multi-way joint decomposition structure and the second multi-way joint decomposition structure are formed through forming molds respectively, then the joint and a pipe beam are fixed in a cementing mode in the mode that a main pipe beam is connected in a sleeved mode and a secondary pipe beam is horizontally placed, and finally room-temperature curing fiber prepreg is wound on the top area of a joint connecting pipe. And curing and forming to obtain the composite material multi-way joint. The fiber continuity and the structural integrity of the multi-way connector can be effectively ensured, meanwhile, assembly of the pipe beam is facilitated, the load transfer capacity of the root of the connecting pipe is enhanced through bonding of the connecting web structure, and the winding fiber on the head of the connecting pipe can effectively restrain stripping of an adhesive layer of the multi-way connector.

The invention relates to the technical field of composite materials, and in particular to a composite plastic based on a PPO material and a preparation method thereof. The invention uses a polyphenylene ether having a chain-branched triazine group and polyvinyl chloride modified by a long-chain fatty acid ester as raw materials for blending, and can prepare a composite plastic with good thermal stability and plasticity; the triazine group is chain-branched on the polyphenylene ether side chain, and can significantly improve the thermal stability of the polyphenylene ether; the triazine group has excellent heat resistance and can maintain structural stability at high temperatures, so that the modified polyphenylene ether has a higher use temperature range; the introduction of the long-chain fatty acid ester can further improve the performance of the polyvinyl chloride at high temperatures; the prepared composite plastic can have good thermal stability through the combination of the two; the flexible characteristics of the long-chain fatty acid ester can adjust the toughness of the composite plastic, and combined with the rigidity of the modified polyphenylene ether, the rigidity and toughness of the composite plastic can be better balanced.

The back door assembly comprises an inner plate and an outer plate which are installed in a buckled mode, a hinge reinforcing plate and an expansion reinforcing plate which can expand when heated are arranged in a cavity defined by the inner plate and the outer plate, and the hinge reinforcing plate at least surrounds the area, where a hinge is arranged, of the back door assembly and is fixedly connected with the inner plate and the outer plate. The expansion reinforcing plate is fixedly arranged on one side of the hinge reinforcing plate, and the area on one side of the hinge reinforcing plate can be filled with the expanded expansion reinforcing plate. According to the back door assembly disclosed by the utility model, the hinge reinforcing plate and the expansion reinforcing plate are arranged between the inner plate and the outer plate, and the area on one side of the hinge reinforcing plate is filled through the expansion state of the expansion reinforcing plate; therefore, each area of the hinge reinforcing plate can root on the inner wall structure of the back door assembly, good acting force transmission performance is achieved, the size and the structural design difficulty of the hinge reinforcing plate are reduced, and the total production cost of the back door is reduced.

The invention discloses a titanium alloy. The titanium alloy is obtained by injection molding of titanium alloy powder. The titanium alloy powder comprises a titanium alloy ball, a TiB2 layer, a polyamine layer and a graphene oxide layer, the surface of the titanium alloy ball is sequentially coated with the TiB2 layer, the polyamine layer and the graphene oxide layer, and the graphene oxide layer contains cerium. The invention also discloses a preparation method of the titanium alloy, which comprises the following steps: mixing titanium alloy powder with a binder, carrying out injection molding, degreasing, carrying out vacuum sintering at 1000-1100 DEG C for 2-3 hours, cooling to room temperature, carrying out solid solution at 700-720 DEG C for 40-60 minutes, carrying out air cooling to room temperature, carrying out heat preservation at 450-470 DEG C for 3-3.5 hours, and then carrying out air cooling to room temperature to obtain the titanium alloy. The titanium alloy disclosed by the invention keeps good toughness while having good strength.

The invention relates to a propulsion system (100) comprising: a turbojet engine (102) having a fan housing (102a) and a center housing (102b); a pylon (104) having an upper spar (106b), a front wall (106d) and fittings (172) rigidly fixed to the rigid structure (106) on both sides of a vertical mid-plane (P); a cylindrical pin (174) integrated with the fan housing (102a) and inserted into a hole of the upper spar (106b); a lock beam (200a) having an upper hinge (202) at the vertical mid-plane (P) between the lock beam (200a) and the front wall (106d) and having a lower hinge (204a-b) on both sides of the vertical mid-plane (P) between the lock beam (200a) and the central housing (102b); and two reaction rods (170a) arranged on both sides of the median plane (P), each rod (170a) being hinged at the front end on the central housing (102b) and at the rear end on the fitting (172). In this arrangement, there is no need to have a rear attachment.

The application discloses a kind of titanium alloys, the titanium alloy is obtained by titanium alloy powder injection molding;Wherein, the titanium alloy powder includes: titanium alloy ball and TiB2 layer, polyamine layer, graphene oxide layer successively coated on the surface of titanium alloy ball, and the graphene oxide layer contains cerium element.The application also discloses a preparation method of the above-mentioned titanium alloy, comprising the following steps: taking titanium alloy powder and binder mixing, injection molding, degreasing, vacuum sintering at 1000-1100 DEG C for 2-3h, cooling to room temperature, solid solution at 700-720 DEG C for 40-60min, air cooling to room temperature, then heat preservation at 450-470 DEG C for 3-3.5h, and then air cooling to room temperature, to obtain titanium alloy.The titanium alloy has good strength while maintaining good toughness.

The invention relates to an aircraft propulsion system (100) comprising: a turbojet engine (102) having a fan housing (103) with an aft face portion (103a); a pylon (104) with a front portion (106a) and a lower spar (106b) with a rear fitting (108) secured thereto; a front engine attachment (150) fixed between the upper portion and the front portion (106a) of the fan housing (103); a front arch (152) having two arms (152b-152c), each arm having a first end secured to the lower spar (106b) and a second end hingedly secured to the rear face (103a); and two lateral levers (154), each having a first end hingedly secured to the rear fitting (108) and a second end hingedly secured to the rear face portion (103a). In this arrangement, a force is transmitted to the rear of the pylon.