30results about How to "Little impact on structural strength" patented technology

The invention discloses a building pillar removing device and method. The building pillar removing device and method aim to overcome the defects that after existing house building pillars are removed, the influence on the structural strength of a house is large, the supporting strength at the pillar removing position of the house is lowered, and then the service life of the house is shortened. Before the pillars are removed, surrounding pillars and a cross beam or a floor need to be subjected to prestress concrete reinforcement, prestress steel strands are installed in prestress concrete, and each prestress steel strand penetrates through self-locking sleeves on self-locking plates and then the self-locking sleeves are backwards compressed; then jacking hydraulic cylinders are installed on the self-locking plates, and each prestress steel strand penetrates through locking sleeves on jacking plates and the locking sleeves are backwards compressed, so that the prestress steel strand is tightly clamped in the locking sleeves; and the jacking hydraulic cylinders at the two ends of the steel strands are started synchronously and push jacking pistons to outwards tension the prestress steel strands, and when it is detected that pressure borne by the pillars to be removed is within the safety removing range, the pillars to be removed are cut off and removed.

The invention provides a cantilever crane device, which is used for engineering machinery and comprises a first knuckle arm and a second knuckle arm. A transfer connection arm is arranged between the first knuckle arm and the second knuckle arm, one end of the transfer connection arm is hinged with the first knuckle arm via a first hinging shaft, the other end of the transfer connection arm is hinged with the second knuckle arm via a second hinging shaft, the axis of the first hinging shaft is perpendicular to that of the second hinging shaft, a first driving mechanism is disposed between the first knuckle arm and the transfer connection arm and can drive the transfer connection arm to rotate around the first hinging shaft, and a second driving mechanism is disposed between the transfer connection arm and the second knuckle arm, and can drive the second knuckle arm to rotate around the second hinging shaft. The invention further provides the engineering machinery. In the technical scheme, a cantilever crane can swing in a vertical direction and/or a horizontal direction by the aid of the transfer connection arm, flexibility is greatly improved, when the cantilever crane rotates within a small range, a rotary table does not need to be started, more energy is saved, and construction cost is reduced.

The invention provides a vertical-axis magnetic levitation tidal current energy power generation device and method in combination with an offshore horizontal-axis wind turbine tower barrel. The vertical-axis magnetic levitation tidal current energy power generation device comprises a central unit, a magnetic levitation rotor unit and a supporting unit, wherein the central unit comprises the horizontal-axis wind turbine single-pile tower barrel and a stator winding. The single-pile tower barrel is fixed to a seabed. The stator winding sleeves the outer wall of the single-pile tower barrel. Themagnetic levitation rotor unit is suspended around the annular stator winding under the action of the supporting unit. The supporting unit is a closed-loop rail with a T-shaped section and is correspondingly arranged below the magnetic levitation rotor unit and fixed to the seabed around the single-pile tower barrel. When a sea tide rises or falls, sea currents push blades to rotate, and magneticpoles of a permanent magnet in the rotor unit are rotated. At the moment, the stator winding installed on the outer wall of the wind turbine single-pile tower barrel converts tidal current kinetic energy into electric energy by cutting rotating magnetic induction lines, and the under-sea tidal current energy power generation method is added on the basis of an existing offshore wind energy power generation system, so that the comprehensive utilization rate of offshore energy is effectively increased.

The invention provides a self-cooling vertical stone machining tool and a manufacturing method thereof. The self-cooling vertical stone machining tool comprises a tool body and a tool handle, whereina main blade and an auxiliary blade are arranged on the tool body, a main cooling hole is formed in the tool handle, the main cooling holes are blind holes which extend into the tool body in depth, aplurality of auxiliary cooling holes extending outwards along the radial direction of the tool handle are formed in the inner wall of the main cooling hole; the manufacturing method comprises the following steps of preparing a tool blank through a sintering or chemical vapor deposition method, milling a spiral groove by using a milling machine, a main cutting edge and an auxiliary cutting edge aremachined through grinding and grinding, and a main cooling hole and an auxiliary cooling hole are machined through an electric spark punching machine. According to the adoption of the technical scheme, the polycrystalline diamond material has high hardness, the cutting performance of the tool is greatly improved, the cooling liquid flows through the main cooling hole and the auxiliary cooling hole to cool the tool, the situation that the local area of the tool is excessively heated is avoided, the tool is protected, the service life of the tool is prolonged, the structural strength of the tool is high, and the workpiece machining quality is improved.

The invention provides an enhanced heat transfer resistance reduction energy-saving heat exchange plate for a broken line type printed circuit plate heat exchanger. The enhanced heat transfer resistance reduction energy-saving heat exchange plate for the broken line type printed circuit plate heat exchanger comprises a heat exchange plate body with a plurality of broken line flow channels arrangedin parallel on the surface; and balance enhancing seams are processed at the bent corners of the broken line flow channels. The balance enhancing seams and the broken line flow channels provided by the invention are integrally machined and formed through a chemical etching process, therefore, the machining is easy, the structure is firm, and the economical efficiency is good; the balance enhancing seams can achieve low-speed jet flow among the flow channels, so that a backflow area is damaged, the heat transfer is enhanced, and meanwhile, pressure distribution in all the flow channels is moreuniform, flow distribution among all the parallel flow channels is more uniform, and therefore, the working medium pressure drop in the flow channels is reduced, and the efficiency of the heat exchanger is further improved; and meanwhile, the influence of the balance enhancing seams on the structural strength of the heat exchanger is small, so that the high pressure bearing capacity can be continuously kept.

The invention discloses a lens connecting structure of rimless eyeglasses and rimless eyeglasses using the lens connecting structure, which belong to the field of the eyeglasses structure. The lens connecting structure disclosed by the invention comprises connecting holes formed in lenses and insertion tabs which are arranged on pile tips or a nose bridge and can be tightly inserted in the connecting holes in a matched manner to stop rotation, wherein an opening is formed in the middle part of each insertion tab along an insertion tab inserting direction, teeth are at least arranged on external sidewalls of the two sides of each insertion tab, and glue or fastening plugs are further arranged in the openings of the insertion tabs. The invention further discloses the rimless eyeglasses. According to the lens connecting structure of the rimless eyeglasses and the rimless eyeglasses using the lens connecting structure, the insertion tabs on the pile tips or the nose bridge of the eyeglasses are in close fit with the connecting holes in the lenses, the friction action between the insertion tabs and the connecting holes is improved by using the teeth on the external sidewalls of the two sides of each insertion tab, and a locking fixing force between the insertion tabs and the connecting holes is increased by arranging the glue or fastening plugs are in the openings of the middle parts of the insertion tabs, so that the lenses of the rimless eyeglasses are firm and reliable in connection and are not prone to loosening; the lens connecting structure has the advantages of simple structure, convenience and quickness in manufacturing and assembling, and the like, so that the manufacturing cost of the rimless eyeglasses is effectively reduced.

The invention discloses an aircraft hardpoint sealing mechanism driven by motors. The aircraft hardpoint sealing mechanism comprises a casing (1), wherein a hanging frame hole (12) is formed in the casing (1), and two sealing plates (9) matched with the casing (1) in a rotating manner are mounted on the bottom surface of the outer sides of the casing (1) respectively and positioned on two sides of the hanging frame hole (12) respectively; a step motor (2) driving the sealing plates (9) to rotate and two opposite-transmitting type infrared sensors (4) positioned on two sides of the hanging frame hole (12) respectively are mounted on the inner side surface of the casing (1). The aircraft hardpoint sealing mechanism disclosed by the invention is simple in structure and convenient to use, when a hanging frame is mounted, the sealing plates are opened through a switch by ground staff, then the sealing plates are held in an open state, and when the hanging frame is released, the sealing mechanism is automatically closed, so that the aircraft hardpoint sealing mechanism is relatively convenient to use; because space for the sealing plates does not need to be reserved in the inner part of the casing, and plan view sizes of the sealing mechanism and a corresponding skin opening are small and slightly greater than sizes of the hanging frame, so that influence on the structural strength of the aircraft is small.

The invention belongs to the technical field of motor rotors, in particular to a rotor sheath of an external rotor permanent magnet motor. The motor comprises a rotating shaft and a stator which sleeves the outer wall of the rotating shaft. The rotating shaft and the stator are fixedly connected. A matching rotor is arranged on the outer side of the stator. Permanent magnets are embedded into theinner wall of the rotor. A rotor sheath is arranged in the interlayer between the permanent magnets and the stator. A spiral slot is arranged in the rotor sheath from top to bottom. Heat dissipation slots are arranged in the outer wall of the rotor sheath. The spiral slot is arranged in the rotor sheath to block the axial and circumferential eddy current paths of the sheath, so that the eddy current loss of the sheath is reduced. The spiral slot can increase the heat dissipation area of the rotor, speed up the wind in the air gap and improve the heat dissipation effect at the joint of the rotor and the rotor sheath. The processing technology of the spiral slot is less difficult, and the spiral slot can be made by simple turning. The heat dissipation slots are arranged in the outer wall ofthe rotor sheath to assist the spiral slot in heat dissipation, and thus, the heat dissipation effect is better.

The invention relates to a material performance detection method, and discloses a method for testing the dynamic fracture expansion toughness of a brittle material.The method comprises: A) preparing a sample (1) with a straight cutting groove (11), and spraying a dot matrix reference system on the observation surface of the sample; B) performing a three-point bending loading experiment on the sample, and measuring the displacement of each scatter point in the reference system along the horizontal and vertical directions by using a digital image measuring device to obtain a cloud chart of the displacement of the scatter points along the horizontal and vertical directions; C) determining geometric centers of the two fractured bodies before the sample is fractured by using a digital image measuring device and a computer through a geometric method, and determining displacements of the geometric centers along the horizontal direction and the vertical direction by combining the displacement cloud atlas; and D) calculating the unit area dissipated energy in the fracture process of the sample, and combining the performance parameters of the sample and the loading parameters of the experiment to obtain the dynamic fracture extension toughness. The method for measuring the dynamic fracture expansion toughness of the brittle material is high in measurement precision.

The invention discloses a bleed air window of an RAT generator. Comprising a supporting arm hole (2) formed in a generator supporting arm (11), and the supporting arm hole (2) is covered with a trumpet-shaped drainage cover (1). The drainage cover (1) comprises a U-shaped lip I (3), a U-shaped lip II (4), a U-shaped lip III (5), a U-shaped lip IV (6) and a hole net (9), wherein the U-shaped lip I (3) and the U-shaped lip II (4) are oppositely arranged, and the U-shaped lip III (5) and the U-shaped lip IV (6) are oppositely arranged. The U-shaped lips I-IV form a quadrilateral large-end air inlet of the drainage cover (1), a hole net (9) is arranged at a small-end air outlet of the drainage cover (1), and the hole net (9) is attached to the conical surface of the supporting arm (11) at the supporting arm hole (2). The technical problems that an existing air entraining window is complex in manufacturing process, high in machining cost and large in influence on the weight of an overall mechanism are solved.

The invention relates to a sealing and riveting tool and a sealing and riveting method applicable to a composite vertical tail wing box of an airplane. According to a technical scheme in the invention, the sealing and riveting tool is such structured that a handle is connected with an extension tube; the extension tube is connected with a magnetic chuck; one end of a wind pipe is connected with awind-controlled switch, and the other end of the wind pipe passes through the handle and the extension tube and then communicates with the magnetic chuck; and an endoscope lens is mounted on the magnetic chuck and is connected with a display screen through a wire. As the sealing and riveting tool is employed for sealing and riveting of the composite vertical tail wing box of the airplane, a fastener can be inserted into a pre-drilled fastener hole in the enclosed wing box under the guidance of the endoscope lens, and then the wind-controlled switch on the wind pipe is turned on so as to fix stringers and/or angular pieces in an enclosed box section via the fastener. According to the invention, the assembling sequence of the wing box is rationally formulated, an endoscope is cooperatively used for observation and is manually hand-held, and the installation of fasteners between stringers and angular pieces is realized through an inherent lightening hole in the wing box, so engineering requirements are met.

The invention relates to a front cover structure for a railway vehicle head. The front cover structure comprises a front cover mounted at the head part of a vehicle body, and the front cover is divided into a plurality of pieces which are fixedly connected together through connecting structures. The front cover structure is simple and practical in integral structure, the front cover is divided into a plurality of pieces and then is sewn, and the strength of the connecting structures among the pieces is controlled, so that the local tearing strength of the front cover made of glass fiber reinforced plastics and the structural failure deformation process under the crashing condition are effectively controlled, the tearing failure is achieved according to the design requirements in the crashing process, the tearing part is bent by the crushing force according to the design requirements, the structure doesn't damage distribution and stretching of fiber in a glass fiber reinforced plastic body, the performance of the glass fiber reinforced plastics is reserved, small influence is produced on the integral structure of the glass fiber reinforced plastic body, the design only affects the strength of local glass fiber reinforced plastics according to the working condition requirements, tearing is performed step by step according to the design requirements after crashing, and the safety design and car coupler hanging requirements are met.

The invention relates to the technical field of buildings, in particular to a connecting device, a composite wall and a production method of the composite wall. The connecting device comprises a bodyand a connecting assembly which is detachably mounted on the body and used for being connected with a thermal insulation part, and support legs for guaranteeing the body to stand on a mold table is formed at one end of the body. According to the connecting device, the composite wall and the production method of the composite wall, a reinforcing mesh and a thermal insulation plate which are mountedon a first wall board through the connecting device can be overturned along with the first wall board.

The invention relates to a compressor. The compressor comprises a dynamic vortex disk and a static vortex disk; a dynamic disk scroll plate is formed on the dynamic vortex disk; a static disk scroll plate is formed on the static vortex disk; a plurality of labyrinth grooves are formed in the side surface of the dynamic disk scroll plate or the side surface of the static disk scroll plate; and thestarting end of each labyrinth groove is the top end part of the static disk scroll plate or the dynamic disk scroll plate. A sealing structure is formed through the plurality of labyrinth grooves andthe sealing structure has throttling and depressurizing effects on compressed air among various crescent compression cavities, so that the fact that the compressed air in a high-pressure cavity is leaked into a low-pressure cavity is avoided and the radial sealing property between the dynamic vortex disk and the static vortex disk is improved.

The invention discloses an air injection structure of an air layer resistance reduction device, a ship air layer resistance reduction system and an air layer resistance reduction ship. The air injection structure of the air layer resistance reduction device comprises a pressure stabilizing cavity and a plurality of spray holes formed in a ship bottom plate, a pressure stabilizing pipe is arranged above a longitudinal bone, an inner cavity of the pressure stabilizing pipe is the pressure stabilizing cavity, the pressure stabilizing pipe is provided with a plurality of air conveying pipes in one-to-one correspondence with the spray holes, and the two ends of each air conveying pipe communicate with the pressure stabilizing pipe and the corresponding spray hole correspondingly. In the prior art, the pressure stabilizing cavity is directly connected with the ship bottom plate, so that the pressure stabilizing cavity can penetrate through the longitudinal bone, and a longitudinal bone reinforcing plate needs to be additionally arranged on the longitudinal bone in order to compensate for the influence of opening holes in the longitudinal bone on the overall strength of the ship. According to the embodiment, the pressure stabilizing cavity is formed above the longitudinal bone, the longitudinal bone does not need to be cut or penetrate through, and the structural strength of the ship cannot be affected.

The invention discloses an air film hole inlet and outlet groove structure for a lap joint laminate contact surface. The air film hole inlet and outlet groove structure for the lap joint laminate contact surface is characterized in that an air film hole inlet and an air film hole outlet on the laminate contact surface with punched air film holes are subjected to hole diameter expansion treatment, that is, grooves are independently processed at the inlet and outlet positions, and then two laminates are overlapped and assembled. The grooves can be processed into a plurality of shapes, such as a conical shape, a cylindrical shape and a semispherical shape, and a proper groove shape can be selected according to specific conditions of a punching tool and the like. According to the air film hole inlet and outlet groove structure for the lap joint laminate contact surface, the corresponding air film holes in the lap joint laminates can effectively communicate, the problem that the corresponding air film holes of the two laminates are staggered due to processing errors is solved, and therefore the air film cooling effect on the lap joint laminates is guaranteed.

The invention discloses a pipeline laying structure applied to a high-speed geotechnological centrifugal machine. According to the structure, pipelines and cables are integrally cured and molded in the pipeline laying structure to reduce protruding matters on the outer surface of a rotary arm of the geotechnological centrifugal machine, so that the whole centrifugal machine has a better aerodynamic shape to help to reduce wind resistance, heat generated by friction and energy consumption; the rotary arm of the centrifugal machine is tightly sleeved with the pipeline laying structure, the direct pressing force of the pipelines, the cables and the rotary arm is replaced with a sleeve pressing force of the pipeline laying structure and the rotary arm, the pressing force is larger, the connection is more stable, and damage on the pipelines and the cables is not caused; the installation and dismantling of the pipeline laying structure is simple, a large number of screw holes do not need tobe reserved in the rotary arm of the geotechnological centrifugal machine, so that stress concentration on a local region on the rotary arm is not caused, and therefore the using safety of the rotaryarm can be effectively protected.