1347 results about "Stringer" patented technology

A method of assembling a platform-based container comprising a base having at least one longitudinal beam, wherein the method comprises pre-loading the longitudinal beam, prior to the completion of the assembly of the container. The beam is then used in the assembly of the container, resulting in a container which no longer takes a permanent deformation under maximum load.

The structure comprises: a rim angle (22) with a front portion and a rear portion, the latter being slanted upward and backward and connected to the bulkhead (1); a simple frame (18), being connected to the front portion of the bulkhead (22); a buttstrap (23), being connected between the front portion of the rim angle (22) and the skin (6, 7) of the fuselage of the aircraft; and tension fittings (24, 25), being fitted between the buttstrap (23) and the longitudinal stringers (8, 9) of the fuselage.

The present invention describes a hollow structural body such as an automotive unibody or frame rail that is reinforced with a reinforcing material such as a polyurethane foam by inserting into a portion of the structural body a bulkhead-containing insert, which, in combination with the structural body at the place of insertion, creates a containment region for the reinforcing material. Uncured reinforcing material can then be added to the containment region and cured.

The present invention solves a problem in the art by providing structural reinforcement to be easily and precisely placed within the structural body to provide, for example, enhanced crash resistance or improvements in acoustical properties.

This invention relates to a king-sized automobile crossbeam using steal and its manufacturing method, tiny alloy elements of Nb, Ti, V are added in the steal. Their weight percentage is that C 0.07-0.12, ,Si 0.15-0.40, Mn 1.00-1.50,P less than 0.025,S less than 0.015,Nb 0.020-0.050,V 0.025-0.050, Ti 0.010-0.030,and tiny Ca, the rest are iron and other tiny impurities. Board butt is continuous cast, rolling and cooling control technique are used in hot rolling, the butt is heated to 1180-1250 degree centigrade, the temperature is 1020 to 1060 degree centigrade after rough rolling. Then it is finish rolled through blimp, the rolling temperature is maintained at 840 to 880 degree centigrade, the coiled sheet is cooled to 560 to 620 degree centigrade through laminar flow cooling. Because of the multiple unit tiny alloy elements design of the material chemical element, strong strength is got after above process and with good plastic laminar flow, cool formability, so it is specially propitious to king-sized automobile crossbeam making of cladding forming technique.

The invention discloses a 610MPa automobile girder steel, and the weight percentage (wt%) of the chemical composition of the steel is as follows: C: 0.08 to 0.12; Si: 0.10 to 0.30; Mn: 1.40 to 1.60; P: less than or equal to 0.010; S: less than or equal to 0.005; Nb: 0.040 to 0.060; V: 0.020 to 0.030; Ti: 0.010 to 0.030; Al: 0.030 to 0.060; Ca: tiny amount; and the rest is iron and residual trace impurities. The invention also discloses a production method for the 610MPa automobile girder steel, which adopts a 2250mm hot rolling line, and a continuously cast slab is heated to 1200 DEG C to 1250 DEG C; after rough rolling, the temperature is 1000 DEG C to 1050 DEG C, the continuously cast slab enters a finishing mill via a heat cover and is rolled, the finish rolling temperature is 820 DEG C to 880 DEG C, and the rolled steel coil is rapidly cooled to 530 DEG C to 580 DEG C by way of laminar cooling, and is then coiled. Since the chemical composition and the production technique are adopted, the tensile strength of an automobile girder is larger than 610MPa, the yield strength is larger than 500MPa, the specific elongation is larger than 20 percent, minus 60 DEG C longitudinal impact energy AKV is larger than 70J, and the automobile girder has excellent cold formability and high fatigue strength. The product is applicable to heavy-duty automobile members such as side members and cross members, which are produced by cold-roll forming and stamping forming techniques.

The invention relates to an integrated multispar torsion box structure of composite material for aircraft, comprising a lower skin (12), an upper skin (11), several spars (9), each of which comprises in turn a chord (13) and a web (14), several stringers (10) in the lower skin (12) and several stringers (10) in the upper skin (11), characterized in that the mentioned integrated torsion box structure is achieved by means of joining unitary U-shaped structural elements (15), unitary U-shaped structural elements (16) with a flap and unitary C-shaped structural elements (17) with a flap. The invention also relates to a method for manufacturing an integrated multispar torsion box structure of composite material for aircraft.

A vehicle body and frame assembly includes a pair of longitudinally extending side rails having a plurality of transverse cross members extending therebetween. The cross member is a multiple piece structure, including a central portion having a pair of end portions secured thereto. The central portion of the cross member is preferably formed from a first metallic material, while the end portions are preferably both formed from a second metallic material. The end portions of the cross member are preferably formed from the same metallic material as the respective side rails to which they are secured. The end portions of the cross member can be secured to the ends of the central portion by any desired process, such as by magnetic pulse welding. Similarly, the cross member can be secured to the side rails by any desired process, such as by magnetic pulse welding or by conventional welding. The end portions of the cross member can extend either partially or completely through the respective side rails. If desired, a reinforcing and positioning collar can be secured to the end portions of the cross member adjacent to each of the side rails.

The invention provides a precast lattice beam used for slope reinforcement and a construction method for slope reinforcement adopting the precast lattice beam, as well as a slope structure reinforced by the precast lattice beam and a construction method thereof. The precast lattice beam comprises a plurality of precast cross-shaped beam units which are arranged and connected in a matrix manner; each of the cross-shaped beam units comprises a transverse beam and a longitudinal beam in intersection; an anchor head part is formed in the central interacting part of each of the cross-shaped beam units; each of the anchor head parts comprises a concrete groove and a backing plate placed on the concrete groove; an anchor hole is formed in each of the concrete grooves and the backing plates; the two end parts of the transverse beam and the two end parts of the longitudinal beam of each of the cross-shaped beam units extend respectively to form L-shaped hook parts reversed in directions; the transverse beam of each of the cross-shaped beam units is connected with that of the adjacent cross-shaped beam unit in a hooking manner through the corresponding L-shaped hook parts; the longitudinal beam of each of the cross-shaped beam units is connected with that of the adjacent cross-shaped beam unit in a hooking manner through the corresponding L-shaped hook parts; therefore the precast lattice beam is formed by splicing a plurality of structures taking the shapes of the Chinese character jing. According to the precast lattice beam used for slope reinforcement, the manufacturing method thereof and the construction method for slope reinforcement adopting the precast lattice beam, the following characteristics are achieved: on-the-spot construction steps are reduced, the construction period is shortened, the standardized management production is realized, the quality is ensured, and high efficiency and environment protection are realized.

In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

Substantially rectangular-shaped tanks are provided for storing liquefied gas, which tanks are especially adapted for use on land or in combination with bottom-supported offshore structure such as gravity-based structures (GBS). A tank according to this invention is capable of storing fluids at substantially atmospheric pressure and has a plate cover adapted to contain fluids and to transfer local loads caused by contact of said plate cover with said contained fluids to an internal frame structure comprised of a plate girder ring frame structure and/or an internal truss frame structure. Optionally, a grillage of stiffeners and stringers may be disposed on the plate cover and additional sifters disposed on the plate girder ring frame structure and/or an internal truss frame structure. Methods of constructing these tanks are also provided.

A forming jig includes a grid pattern of support walls arranged on a support base and having upper free ends located along an imaginary curved surface, and modular sectional profile members arranged on the walls to enclose a vacuum chamber within the jig. Grooves, channels and air passages between neighboring profile members communicate into the vacuum chamber. The outer surface of the profile members matches the intended inner surface of a structural component to be fabricated using the jig. In the fabrication process, a film is applied to the outer surface to pre-establish a vacuum, the film is removed while simultaneously a vacuum skin is applied, stringer members are set into the grooves, fiber skin layers are laid up, a sealant is applied around the perimeter, a structural shell is vacuumed onto the skin layers, and then this preformed component is removed from the jig, injected with resin unless the skin layers were pre-impregnated with resin, and cured.

The invention relates to bridge engineering, in particular to an abrupt slope bare rock drilling platform and a technology in a huge reservoir and used for bridge construction. The invention is characterized in that an abrupt slope bare rock drilling device in a huge reservoir comprises steel pipe piles, a cross beam, a longitudinal beam, cross struts and a steel casing, wherein the steel pipe piles are arranged on the riverbed in a longitudinal and transverse spacing manner; the longitudinal and transverse spaces of the steel pipe piles are connected through a braced plane frame, the longitudinal cross strut and the transverse cross strut; the space surrounded by the four steel pipe piles is internally provided with the steel casing the height direction of which is parallel to the steel pipe piles; and the diameter of the pile foundation steel casing is 280cm, and the steel casing is made by rolling an A3 steel plate with the thickness of 14mm. The construction technology of the platform has 14 steps, and the invention provides the abrupt slope bare rock drilling platform and the technology in the huge reservoir, which can ensure the platform safety, easily heighten or lower the steel pipe piles, ensure the accurate in-position of a drilling machine and the pile foundation verticality, and is convenient to controlling the axial plane position of the pile foundation.

The invention discloses a chassis of a body of a hundred-percent modern city tramcar. The chassis comprises a sleeper beam, a longitudinal beam, a first end beam, a second end beam, a first side edge beam and a second side edge beam, wherein the sleeper beam is welded to form a closed box type shaped like a Chinese character 'gong'; the longitudinal beam is welded to form a closed box type structure which penetrates through the whole body; the sleeper beam, the longitudinal beam, the end beams and the side edge beams are welded together to form a #-shaped frame structure. The chassis is formed by welding high-strength carbon steel materials, all parts are independently welded to be spliced into the chassis, and the chassis is riveted with other parts of the body. Requirements for small space of a low-floor vehicle chassis are met, and the sleeper beam and the longitudinal beam respectively form the closed box-type structure, so that the stress is uniform and is not prone to concentration, the structure is stable, the local fatigue failure is not prone to occurrence, requirements for weight control over the chassis of the whole vehicle are met, and damaged parts of the body can be independently replaced.

The invention discloses an IBC solar cell string welding strip welding production line and a production method thereof. Compared with a conventional tabber and stringer in which the position of a metal wire is fixed by using a latter cell piece, an IBC cell cannot achieve the effect, and a net pressing clamp is needed for covering and fixing. The IBC solar cell string welding strip welding production line comprises a cell arrangement module, welding strip adding modules, a final welding module and a cell string transferring module, wherein the cell arrangement module, the welding strip addingmodules and the final welding module are sequentially arranged; and the cell string cell module is arranged at the output ends of the welding strip adding modules and transfers cell strings output bythe welding strip adding modules to the final welding module, and the welding strip adding modules comprises middle racks, welding strip feeding devices, welding strip transferring devices, light welding devices, clamp backflow devices, third cell conveyors, clamp conveyors and pressing positioning clamps. The IBC solar cell string welding strip welding production line and the production method thereof can realize full-automatic arrangement, preliminary welding and final welding of cell pieces.

The present invention relates to the technical field of engineering construction, and more particularly, to a formwork jumbo for full face construction of a pipe gallery and a construction method thereof. The formwork jumbo comprises a longitudinal beam, a formwork part, a formwork supporting device and hydraulic mechanisms. The formwork part comprises a top form, side forms and a bottom form. Each of two sides of the longitudinal beam is connected to one side of a distributive girder through one hydraulic mechanism. The other side of each distributive girder is connected to one side form. The top and the bottom of each of the side forms are connected to the top form and the bottom form, respectively. The middle section of the top form and the middle section of the upper portion of each side form are connected by a hydraulic mechanism, and so are the middle section of the bottom form and the middle section of the lower portion of each side form. The formwork jumbo is applicable to a full face pipe gallery construction technique. One-step formation through pouring of concrete is achieved, and the steps of construction joint treatment, stay bolt set-up and formwork removal in traditional formwork construction are omitted. The problem of water penetration through a construction joint is fundamentally solved. The formwork jumbo is more practical, more convenient, and prone to standardized management, and has enormous technical and economical benefits.

The invention relates to a production device and a machining method for U-shaped longitudinal beam and lining beam automatic positioning beam combining spot welding. The production device and the machining method are characterized in that a beam combining feedstock feeding device is placed on the right side of an automatic spot welding device, a lining beam end face positioning component is placed on the front side of the beam combining feedstock feeding device, six sets of longitudinal beam feeding devices are sequentially arranged on the right side of the beam combining feedstock feeding device and the right side of the lining beam end face positioning component, and a feeding platform is placed in front of the longitudinal beam feeding devices. A feedstock extraction device is placed at back of the longitudinal beam feeding devices, and a track installed in the feedstock extraction device forwards extends to reach the position above the feeding platform. A beam combining discharged material feeding device and two sets of discharged material supporting rollers are sequentially placed on the left side of the automatic spot welding device. A discharging platform is placed in front of the beam combining discharged material feeding device and the discharged material supporting rollers, a discharged material extraction device is placed at back of the beam combining discharged material feeding device and the discharged material supporting rollers, and a track installed in the discharged material extraction device forwards extends to reach the position above the discharging platform.

A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.