45results about How to "Improve bending and torsional performance" patented technology

A hollow chamber structural component includes a shell component which extends along a main extension direction. A cover component is attached to the shell component, wherein a hollow chamber is disposed between the shell component and the cover component and extends in the main extension direction. A reinforcing structure is arranged in the hollow chamber and comprises: a synthetic support structure, which follows at least in some sections the main extension direction and rests with at least some sections against an inside of the shell component; and at least one reinforcing element that follows at least in some sections the main extension direction and is joined to the synthetic support structure with the aid of a layer of adhesive.

The invention provides a rigidity-flexibility transition busbar and belongs to the technical field of an electrified railway and urban rail transit overhead contact line. The invention solves the problems of high transition hardness and cost of an existing rigidity-flexibility transition busbar. The rigidity-flexibility transition busbar comprises a busbar body; both ends of the busbar body respectively are a rigid connection end and a flexible connection end; the lower part of the busbar body is provided with a wire clamping jaw; a rigidity-flexibility transition part for enabling the rigidity of the busbar body to be gradually reduced is arranged between the rigid connection end and the flexible connection end; the upper surface of the rigidity-flexibility transition part is a continuous transition inclined plane; the busbar body is provided with a plurality of connection through holes running through the busbar body along the length direction; locking bolts are respectively arranged in the connection through holes; each locking bolt is sleeved with a positioning sleeve; and both end faces of each positioning sleeve are respectively pressed against the inner lateral surface of the busbar body. The rigidity-flexibility transition busbar adopts the continuous transition inclined plane to carry out transition and hard spots in the rigidity-flexibility transition busbar are eliminated.

The invention discloses a high-precision and high-strength cold-drawing forming die for a special-shaped D-shaped pipe. The high-precision and high-strength cold-drawing forming die comprises an outerdie body and an inner die body, and the outer die body comprises an outer die main body. The outer die main body is of an axisymmetric structure, the overall shape structure of the outer die main body is a cylinder, and a forming die cavity is machined in the center of the outer die main body. The first circular-arc inlet section is machined on the section inner contour in the forming die cavity,wherein the section inner contour penetrates through the symmetry axis of the forming die cavity and is parallel to the forming die cavity. The first circular-arc inlet section is in transition connection with the first circular-arc transition section, and the other end of the first circular-arc transition section is in transition connection with the first straight section. By adopting the high-precision and high-strength cold-drawing forming die as well as a cold-drawing auxiliary process, the special-shaped D-shaped pipe can be machined and produced, and then steel pipes of various specialshapes or special properties on oil downhole tools and construction machines can be machined. Complex machining can be simplified, the structural weight is greatly reduced, steel is saved, and throughmachining hardening, the strength of finished pipe metal is greatly improved.

The invention relates to a microwave curing method and a microwave curing device of a composite shaft part. The method is characterized by comprising the following steps: firstly, laying uncured composite materials on the surface of a smooth mandrel coated with a release agent, so as to form a to-be-cured shaft part, then arranging the to-be-cured shaft part in a vacuum bag in a sleeving manner, sealing both ends of the vacuum bag by high temperature resistant adhesive tapes, then vacuumizing the vacuum bag, so as to compact the to-be-cured shaft part, then putting the compacted to-be-cured shaft part and the mandrel into a microwave curing oven, setting heating parameters of the microwave curing oven according to a composite material heating process, and heating and curing the composite shaft part; after the final heat preservation time is finished, directly moving the shaft part out of the curing oven and cooling in the outdoor environment. The microwave curing method has the advantages of short heating and curing time, low energy consumption, good temperature uniformity and easiness in control.

The invention provides a front spring front support cross beam assembly. The front spring front support cross beam assembly comprises a cross beam formed by a section of box iron, two upper wing boards and two lower wing boards. The cross beam comprises an upper leg board and a lower leg board, the upper leg board is arranged over the lower leg board, the upper wing boards and the lower wing boards are all bent boards bent upwards by 90 degrees and respectively comprise a vertical portion and a transverse portion, the two upper wing boards are arranged opposite to each other, the vertical portions of the two upper wing boards are arranged on the outer sides of the transverse portions of the two upper wing boards, the transverse portions of the two upper wing boards are riveted to the two end portions of the upper leg board respectively through rivets, the two lower wing boards are arranged opposite to each other, the vertical portions of the two lower wing boards are arranged on the outer sides of the transverse portions of the two lower wing boards, the transverse portions of the two lower wing boards are riveted to the two end portions of the lower leg board respectively through rivets, the two upper wing boards are arranged over the two lower wing boards respectively and correspondingly, and the two upper wing boards and the two lower wing boards are respectively provided with a bolt hole used for being connected with frame bolts. The front spring front support cross beam assembly can play the role in reinforcing the cross beam of a frame, effectively support a left front spring front support and a right front spring front support, and greatly improve the bending-resisting capability of a whole vehicle chassis.

The invention relates to a front end cross beam of a stainless steel staircase step, in particular to a front end cross beam of a split assembled step, and belongs to the field of escalator manufacture. The lower part of a lath shaped beam body is provided with a first support reinforcing surface vertical to the beam body and a second support reinforcing surface parallel to the beam body respectively; and the cross sectional shape of the cross beam is a semi-closed shape surrounded by the lath shaped beam body, the first support reinforcing surface and the second support reinforcing surface, and each surface is formed by continuously bending. The invention solves the technical problem and provides the technical task that the front end cross beam overcomes the defects that the front end cross beam structure of the prior stainless steel staircase step has poor bending resistance and torsional property and has no or indefinite assembly standard, and provides the front end cross beam with definite anti-deforming aim, rigidity and strength meeting standard code requirements, and definite assembly and positioning standards.

The invention relates to a hydraulic support base. The hydraulic support base comprises a main reinforcement and two groove bodies defined by base plates. The main reinforcement comprises internal main reinforcement bodies and external main reinforcement bodies, an attached plate is arranged on the position, corresponding to a connecting hole of a connecting rod, of the internal side of the main reinforcement, and a reinforcing plate is arranged on the position, corresponding to a pillar nest, of the external side of the main reinforcement. The internal main reinforcement bodies and the external main reinforcement bodies are connected through a first horizontally-arranged cover plate, the adjacent internal main reinforcement bodies are connected through second obliquely-arranged cover plates, and a third obliquely-arranged cover plate connected with a gap bridge is arranged on the pillar nest and connected with the internal main reinforcement bodies and the external main reinforcement bodies. A second reinforcement plate is arranged outside the internal main reinforcement bodies in the length direction of the internal main reinforcement bodies, and a lifting lug is arranged on the second reinforcement plate. According to the hydraulic support base, by arranging the attached plate and the reinforcing plate on the main reinforcement, the strength and the anti-bending and anti-torque capacities of the hydraulic support base are improved, the stressed area of the base is increased, the overall length of the base and the length of a sidewalk are increased, the overall height of the hydraulic support base is decreased, and the hydraulic support base is suitable for exploitation of a thin coal seam.

The invention discloses a light anti-bending and anti-torsion bionic composite material and a preparation method thereof. The composite material comprises a bottom layer, a lower partition plate layer, a hollow structure middle layer, an upper partition plate layer and an outer layer which are sequentially arranged in a stacked mode from bottom to top; the hollow structure middle layer comprises a first-stage dense hole structure, a loose hole upper-layer structure, a first-stage loose hole structure, a loose hole lower-layer structure and a second-stage dense hole structure which are sequentially stacked from bottom to top; and the first-level compact pore structure, the first-level loose pore structure and the second-level compact pore structure are each composed of a woven fiber resin layer, and each woven fiber resin layer is formed by alternately winding weft-wise fibers and warp-wise fibers on a core film. The middle layer of the hollow structure is arranged in the mode that the outside is dense and the inside is sparse, the weight of the material can be reduced, the specific rigidity of the material can be improved, when the material is bent, the upper surface of the middle layer of the hollow structure bears tensile stress, the lower surface of the middle layer of the hollow structure bears tensile pressure, and the bending resistance and toughness of the material are improved.

The invention provides a deformable biplane configuration. The configuration comprises an upper wing, a lower wing and a plurality of parallel distributed deformation mechanisms, wherein the upper wing and the lower wing are connected through the deformation mechanisms; each deformation mechanism comprises a connecting strut and 1 to 2 motion mechanisms; a drive mechanism and a locking device are arranged on each motion mechanism which is fixed on the upper wing or the lower wing; one end of the connecting strut is mechanically connected with the motion mechanism, while the other end of the connecting strut is mechanically connected with the motion mechanism or fixedly connected with the upper wing or the lower wing; the drive mechanism drives the motion mechanism to drive the connecting strut to ensure that the upper wing and the lower wing rotate in 0 to 180 degrees in the course direction and the height direction; and when the upper wing and the lower wing move to a set position, the locking device locks the motion mechanism, and positions of the upper wing and the lower wing are fixed. Regarding the wing configuration mode of a solar plane, the deformable biplane configuration is adopted, compared with single plane configuration, under a condition that the same wing type, the same wingspan and the same aspect ratio of a single wing are adopted, through the deformable biplane configuration, the takeoff weight can be increased, the effective load can be increased, the induced drag of the wings can be reduced, and the area of a solar cell panel can be increased, so that the solar energy absorption capacity can be improved, and the energy consumption of night flight can be reduced.

The invention discloses a wing spar of a compound-wing aircraft, which comprises two transverse integral beams arranged horizontally opposite to each other, and a cross-type load-bearing beam for carrying bending and torsional moments is arranged between the two transverse integral beams. The interior of the cross-type load-bearing beam is a hollow structure, and the ends of the cross-type load-bearing beam are fixedly connected with two transverse integral beams; both ends of the two transverse integral beams are provided with an end rib for carrying bending and torsional moments. The two transverse integral beams are connected and fixed by two end ribs. The cross-type load-bearing beam has a hollow structure as a whole, which greatly reduces the structural weight of the wing. At the same time, the cross-type load-bearing beam greatly improves the resistance of the load-bearing beam Bending and torsional performance, the cross-type load-bearing beam is equipped with a water channel, which simply and effectively solves the problem of water storage and drainage inside the wing spar, and the addition of end ribs can obtain a lighter weight under the premise of determining a certain bending and torsional strength. the weight of.

The invention provides a rigid-flexible transition busbar, which belongs to the technical field of electrified railway and urban rail transit overhead catenary. It solves the problems of transitional hardness and high cost in the existing rigid-flexible transition busbar. The rigid-flexible transitional bus bar includes a bus bar body. The two ends of the bus bar body are respectively a rigid connection end and a flexible connection end. The lower part of the bus bar body has a clamping jaw. The rigid-flexible transition part whose body rigidity gradually decreases, the upper surface of the rigid-flexible transition part is a continuous transition slope; the bus bar body is distributed along the length direction with several connecting through holes passing through the bus bar body, and locks are respectively installed in the connecting through holes. Each locking bolt is covered with a positioning sleeve, and the two end surfaces of the positioning sleeve respectively abut against the inner surface of the main body of the bus bar. The rigid-flexible transitional busbar adopts a continuous transition slope for transition, eliminating hard points in the rigid-flexible transitional busbar.

The invention relates to a front end assembly structure of a stainless steel staircase step, in particular to a front end assembly structure of a split assembled step, and belongs to the field of escalator manufacture. By using a horizontal positioning surface as a standard, a front end cross beam for realizing height horizontal positioning is placed above triangular brackets and the horizontal positioning surface which are arranged in parallel; the triangular brackets and the horizontal positioning surface are contacted and connected with and position a first vertical positioning surface and a second vertical positioning surface to realize the vertical positioning and specific size span positioning of two triangular brackets. The invention solves the technical problem and provides the technical task that the structure overcomes the technical defects in the front end assembly structure of the prior stainless steel staircase step, and provides an implementation proposal for the front end assembly structure of the step with good integrity, deformation resistance, definite assembly standard aim, large overload capacity, convenient assembly and easy quality control.

The invention relates to the technical field of automobiles, in particular to an automobile body aluminum profile water tank column and an automobile. The automobile body aluminum profile water tank column comprises a main board, a first connecting frame and a second connecting frame. The first connecting frame and the second connecting frame are fixedly arranged on the same side of the main board; The first connecting frame comprises a first support plate and a second support plate; The first support plate and the second support plate together form a triangular cavity structure with the mainplate; The second connecting frame comprises a third support plate and a fourth support plate; The third support plate and the fourth support plate together with the main plate form a triangular cavity structure. The automobile body aluminum profile water tank column and the automobile provided by the invention are provided with two connecting frames arranged on the main board, so that one part isreliably connected with the other part at the same time by two identical side faces, and the cross-section structure enables the product to have higher strength, rigidity, bending and torsion resistance; Using aluminum alloy profile longitudinal / transverse beam, it has high strength and strength, and the investment of mould is low, and the production efficiency is high.

The invention discloses a drone noselanding gear well section based on catapult-assisted take-off. A landing gear well comprises partition frames at the two ends, a girder connected with the partitionframes and a skin; a landing gear fixing compartment is arranged in the middle of the landing gear well, a framework of the landing gear fixing compartment comprises four main girders, the main girders are fixedly connected with the partition frames, and partition plates are arranged at both the two sides of each main girder and the partition frames; the main girders and the partition plates forman integrated wall plate girder, the wall plate girder is hinged to a landing gear main support and a landing gear slant supporting rod, and openings are formed in the skin at the lower portion of the landing gear fixing compartment. The landing gear well is of a box body type structure low in structural weight, the openings are formed among the main girders, the rigidity of other parts of the landing gear well and the rigidity of an overall aircraft cannot be lowered, and additional strength reinforcement setting is also not needed; the wall plate girder penetrating through the whole box body has the advantages of being continuous in stress and short and direct in force transmitting path, and transmitting of instantaneous impact large loading concentrated force and torque inside the structure is benefited.

The invention provides a deformable biplane configuration. The configuration comprises an upper wing, a lower wing and a plurality of parallel distributed deformation mechanisms, wherein the upper wing and the lower wing are connected through the deformation mechanisms; each deformation mechanism comprises a connecting strut and 1 to 2 motion mechanisms; a drive mechanism and a locking device are arranged on each motion mechanism which is fixed on the upper wing or the lower wing; one end of the connecting strut is mechanically connected with the motion mechanism, while the other end of the connecting strut is mechanically connected with the motion mechanism or fixedly connected with the upper wing or the lower wing; the drive mechanism drives the motion mechanism to drive the connecting strut to ensure that the upper wing and the lower wing rotate in 0 to 180 degrees in the course direction and the height direction; and when the upper wing and the lower wing move to a set position, the locking device locks the motion mechanism, and positions of the upper wing and the lower wing are fixed. Regarding the wing configuration mode of a solar plane, the deformable biplane configuration is adopted, compared with single plane configuration, under a condition that the same wing type, the same wingspan and the same aspect ratio of a single wing are adopted, through the deformable biplane configuration, the takeoff weight can be increased, the effective load can be increased, the induced drag of the wings can be reduced, and the area of a solar cell panel can be increased, so that the solar energy absorption capacity can be improved, and the energy consumption of night flight can be reduced.

The invention discloses an improved auxiliary frame of a large-earthwork concrete mixing carrier. The auxiliary frame mainly solves the problems that loads of the mixing carrier increase substantially and a prior auxiliary frame cracks easily. The improved auxiliary frame comprises an auxiliary beam, a front table, a rear table, an inclined tensioned support, a U-shaped bent plate and an inclined support, wherein the front table is arranged at one end above the auxiliary beam, the rear table is arranged at the other end above the auxiliary beam, the U-shaped bent plate is arranged on the auxiliary beam, the inclined tensioned support is arranged between the U-shaped bent plate and the rear table, and the inclined support is arranged between an auxiliary beam cross support at the front end of the bottom of the rear table and the U-shaped bent plate. The strength of the auxiliary frame of the concrete mixing carrier can be well improved, the improved auxiliary frame can be used under all kinds of large-earthwork concrete mixing carrier using conditions, local tension resistance of the auxiliary frame of the concrete mixing carrier is improved, and stress conditions of the auxiliary frame are fully optimized.

In order to overcome the problems of paint cracking and welding seam fatigue caused by insufficient rigidity and strength of existing car door and window structures, the present invention provides a car door and window frame structure, including door inner panels, door outer panels, window frame front components, window A frame rear assembly, a waistline reinforcement assembly and an upper sash, the sash front assembly includes a sash front outer panel and a sash front inner panel overlapping each other, the sash front outer panel and the sash front A first cavity is formed between the inner panels at the front of the window frame, the rear assembly of the window frame includes an outer panel at the rear of the window frame and an inner panel at the rear of the window frame which overlap each other, the outer panel at the rear of the window frame and the outer panel of the window frame A second cavity is formed between the inner panels at the rear of the window frame. At the same time, the invention also discloses an automobile comprising the above-mentioned vehicle door and window frame structure. The car door and window frame structure provided by the invention can ensure sufficient connection rigidity and strength of the window frame, and avoid paint cracking and sheet metal rusting caused by solder joints and seam welding cracks.