97 results about "Angle alpha" patented technology

The invention relates to a manufacturing method of a microprism reflective film die integrating two triangular pyramids and a reflective film, and the manufacturing method of the die comprises the following steps: 1, respectively rotating a die base material on a B-axis rotary table to 0 degree, 120 degrees and 60 degrees, and machining a first tool to a third tool by using a first tool with a tool angle alpha mounted on a fly-cutter disc; the mold base material is rotated to be located at the 0-degree position, the 120-degree position and the 60-degree position, machining of the fourth tool, the fifth tool, the sixth tool and the sixth tool is conducted, in the machining of the fourth tool, the fifth tool, the sixth tool and the sixth tool, the first tool is used for machining, the second tool is used for machining, the first tool and the second tool are symmetrical tools, and the inclination angles of the two sides are the same. While better performance indexes under different application conditions are obtained, the influence of large conical surface angle deflection angle processing or asymmetric design on optimization and balance of the retroreflection performance of 0 / 90 / 180-degree orientation of the reflective film can be reduced.

The invention discloses a method for realizing elliptic cone scanning by a communication-in-moving antenna. The method comprises the following steps: determining the value of a scanning position point number parameter N; determining the value of the maximum scanning offset angle delta A in the azimuth angle direction and the value of the maximum scanning offset angle delta E in the pitch angle direction; determining values of an expected azimuth angle alpha 0 and an expected pitch angle beta 0 of the current antenna; setting a scanning counter i; when i is less than 4N, calculating a parameter theta i, calculating a scanning offset angle delta i, calculating a scanning track beta i of a pitch angle, and calculating a scanning track alpha i of an azimuth angle; the pitch angle of the antenna is controlled to rotate to a new position beta i, and the azimuth angle of the antenna is controlled to rotate to a new position alpha i; and updating the scanning counter i, i = mod (i + 1, 4N), and returning to execute. The method not only can realize elliptic cone scanning, but also can realize cone scanning, and can effectively solve the problem that the average receiving level is reduced when the communication-in-moving antenna of which the cross section of the beam main lobe is elliptic performs cone scanning.

The application provides a fall-preventing triangular profile structure and a mounting method. The triangular profile structure comprises a triangular cross-section structure formed by sequentially connecting a first side 1, a second side 2 and a third side 3; an angle alpha between the second side 2 and the third side 3 is 90-120 degrees; an angle beta between the first side 1 and the second side 2 is 30-60 degrees; the length of the third side 3 is less than the length of the first side 1; and an anti-skid structure is arranged on the bottom surface of the third side 3. The technical scheme can simplify the construction process, improve the operation flexibility, and save the construction cost.

The invention relates to a method and device for designing a spatial streamline inlet of a rotational flow separator, and the method comprises the steps: determining an inlet angle alpha, a wrap angle beta, an incident angle gamma and an overturning angle theta of the inlet of the rotational flow separator according to the performance requirements of the rotational flow separator; the method comprises the following steps: selecting a control point at a rotational flow separator, generating a basic shape of a characteristic bus of the spatial streamline inlet through a spline curve equation, then selecting a type value point to carry out iterative optimization on the bus shape, and determining a final curve shape of the spatial streamline inlet through an entrance angle, a wrap angle, an incident angle and a flip angle; based on the inlet shape of the rotating flow separator, the section shape of a space streamline inlet is designed through a Bezier curve equation; and according to the final curve shape and the section shape of the spatial streamline inlet, the spatial streamline inlet structure of the rotating flow separator is determined. Compared with the prior art, pre-separation of particles / liquid drops is achieved through fluid inertia accelerated rotation, and the separation efficiency of the hydrocyclone is improved.

The invention provides a dynamic art device, relates to the technical field of artware, and solves the technical problem of dynamic simplicity of ornaments in the prior art. The device comprises a first rotation driving assembly, a rotation shell, a second rotation driving assembly and a decoration part, the first rotation driving assembly is arranged in the rotation shell, the driving end of the first rotation driving assembly is connected with the rotation shell, and the rotation shell is of a spherical shell structure; the rotating part of the second rotating driving assembly is rotatably arranged on the rotating shell, the decorating part is arranged on the rotating part, the rotating axis of the rotating part deviates from the center of the decorating part, the included angle alpha between the rotating axis of the rotating part and the rotating axis of the rotating shell is larger than or equal to 30 degrees and smaller than or equal to 90 degrees. By means of the eccentric arrangement mode of the decoration part and the two rotary driving assemblies, the decoration part can eccentrically rotate on the rotating hemispherical shell, and therefore the dynamic state of the decoration part is more complex and elegant.

The invention provides a niobium plate leveling method which comprises the following steps: primary leveling: feeding a niobium plate to a leveling machine for the first time for leveling, and discharging at a first bending angle to obtain a primary leveled plate; secondary leveling is conducted, specifically, after the primary leveling plate is rotated by an angle alpha, the primary leveling plate is fed into the leveling machine for leveling in a secondary feeding mode, discharging is conducted at a second bending angle, and a secondary leveling plate is obtained; wherein the first bending angle is the included angle between the tangent line of the primary discharging end of the niobium plate and the horizontal direction, the second bending angle is the included angle between the tangent line of the secondary discharging end of the niobium plate and the horizontal direction, alpha is larger than or equal to 45 degrees and smaller than or equal to 90 degrees, and the first bending angle is larger than or equal to 50 degrees and larger than or equal to the second bending angle and larger than 0 degree. According to the leveling method, the technological process can be simplified while the flatness and the thickness uniformity of the niobium plate are improved, and the machining requirement of the high-precision pure niobium plate is met with low production cost.

The application provides an internal embedded bomb cabin honeycomb configuration aerodynamic layout for improving flow field stability, and the internal embedded bomb cabin cross section body is a hexagonal honeycomb configuration layout, wherein the top surface of the honeycomb configuration is opened, the other five surfaces are closed wall surfaces, the top surface is parallel to the bottom surface, the included angle alpha between the bottom surface and the adjacent surface is 135 degrees, the longitudinal depth ratio beta of the honeycomb configuration is L / H=1.5, L is the maximum transverse distance of the bomb cabin cross section, and H is the maximum longitudinal height of the bomb cabin cross section. Under the condition of meeting the requirements of structural strength, sound and heat insulation, weight reduction, internal structure design of the fuselage, capacity and other constraints, the internal flow flow field stability of the internal embedded bomb cabin can be greatly improved, the flow field characteristics are improved from the physical root, the evolution of fine vortex and secondary vortex is effectively inhibited, and the process of the flow field from the steady state to the unsteady state is greatly delayed. Because the optimization design effectively inhibits the unsteady flow, especially the premature appearance of the turbulent flow, the aerodynamic efficiency of the internal flow of the bomb cabin is improved.

The application discloses a grinding processing method for inner concave outer circle and end face, which comprises the following steps: grinding the inner concave outer circle and end face of a part to be processed by using a grinding wheel; the grinding wheel comprises a grinding wheel body and a connecting rod; one end of the connecting rod is connected to a grinding wheel frame, and the other end is connected to one end of the grinding wheel body; a grinding surface is arranged on the side surface of the grinding wheel body to grind the part to be processed; the central axis of the connecting rod and the central axis of the part to be processed have an inclination angle alpha; on the plane passing through the central axis of the part to be processed, the end face projection line is used as a reference line, the highest height of the inner concave outer circle projection line relative to the reference line is H, the diameter of the grinding wheel body is D, the diameter of the connecting rod is d, the length of the connecting rod is l, l<=3d is satisfied, and beta=90-alpha. The application has the advantages of high machining precision and high efficiency.

The invention discloses a snakelike arm structure based on a negative Poisson's ratio metamaterial. A snakelike mechanical arm is obtained by assembling a plurality of mechanical metamaterial structural bodies. The mechanical metamaterial structural body is composed of an external frame unit capable of elastically deforming and bionic scales; the elastically-deformable outer frame unit is formed by arranging four connecting rods between a vertical rod A and a vertical rod B which are arranged in parallel. The elastically deformable outer frame unit has an elastic deformation characteristic of the flexible mechanism. The mechanical metamaterial structural body is divided into a first plane and a second plane from the space structure, the second plane tilts upwards by a certain angle alpha relative to the first plane, the alpha forms a micro-convex bionic scale structure with a certain backward angle, the highly asymmetric pawl characteristic with one sharp side and the other gentle side is shown, and the mechanical metamaterial structural body is formed. Therefore, the mechanical metamaterial structural body forms friction anisotropy in the scale blade direction, namely, different friction forces are shown in different movement directions.

The invention provides a radar covering part design method and system, a vehicle and an evaluation method. The radar covering part design method comprises the steps that three-dimensional models of a radar and a covering part are established; measuring a first included angle alpha between the radar and the covering part on the horizontal section and a second included angle beta between the radar and the covering part on the vertical section; the larger value in the first included angle alpha and the second included angle beta is called as an included angle theta between the radar and the covering part; and calculating the optimal thickness d of the covering part according to the included angle theta between the radar and the covering part, the electromagnetic wave frequency f of the radar and the dielectric constant of the covering part. The influence of the installation angle of the covering part and the radar on the optimal thickness of the covering part can be fully considered, so that the detection performance of the radar is ensured.

The invention relates to a motor NVH (Noise Vibration and Harshness) performance optimization method, which comprises the following steps of: S1, defining a cogging angle of a rotor which comprises N sections of skewed poles, and calculating an initial angle alpha (0) of each section of skewed pole; s2, calculating an electromagnetic force amplitude initial value Fr0 (Amp) when the initial angle of each skewed pole is alpha (0); s3, adjusting the angle of each section of skewed pole according to a preset angle step number a (step), calculating the electromagnetic force amplitude Fr (Amp) of each section of skewed pole corresponding to the angle, and defining a target function Min (Fr (Amp)); s4, according to the target function Min (Fr (Amp)), obtaining the target electromagnetic force amplitude of each section of skewed pole, and synchronously calculating the electromagnetic force resultant force amplitude of the target electromagnetic force amplitude of each section of skewed pole; and S5, evaluating whether the influence of the electromagnetic force phase meets requirements or not, if not, returning to S3, adjusting the angle of each section of skewed pole and / or adjusting the target function, and if yes, obtaining the target electromagnetic force amplitude and the target angle of each section of skewed pole.

The invention provides an aqueduct construction method. The aqueduct construction method comprises the following steps that S1, an aqueduct is divided into a straight line section and a curve section; s2, calculating a central angle alpha of the second groove body; s3, dividing the straight line segment into a first straight line segment and a second straight line segment; a prefabricated groove field is built on the first straight line section; s4, supports are installed at the tops of the cushion blocks of the two adjacent pier columns, then a groove body left end mold, a groove body right end mold and a groove body mold plate of a first groove body are installed, prefabrication of the first groove body is conducted, and all prefabrication of the first groove body and assembly construction of a second straight line section are completed; s5, clockwise rotating the left end mold of the groove body by 0.5 alpha, anticlockwise rotating the right end mold by 0.5 alpha, adaptively moving and adjusting top supports of two adjacent pier columns in the longitudinal groove direction, mounting a groove body mold plate of a second groove body, and then completely prefabricating the second groove body and assembling and constructing a curved section; and S6, assembling construction of the first straight line section is completed. The construction efficiency of aqueduct construction is improved.

The application discloses a processing method of an adjustable-angle golf club pipe handle, which completes mechanical processing procedures of the pipe handle on a machine tool, and utilizes a first spindle and a second spindle to move along an X axis transversely, and utilizes a first tool seat and a second tool seat to flexibly move along the X axis and a Z axis to adjust the position of a workpiece and a tool, so that all mechanical processing is completed, the occupation of the machine tool is reduced, compared with traditional multiple intermediate sequences and manual clamping, the production cycle is reduced, and the processing efficiency is improved. An inner thread hole of the pipe handle and a center axis of an installation inner hole have an angle alpha, the rotation axis of the rotary tool is offset from the center axis of the pipe handle by adjusting the installation posture of a driving unit on the first tool disc, quick and flexible adjustment can be conducted according to production requirements, the production requirements of different products can be quickly adapted, and good convenience and applicability are achieved.

The invention discloses a method for correcting propeller deflection and a device for adjusting propeller deflection. The method comprises the steps that a propeller is installed to a set position; selecting a three-coordinate direction of a rectangular coordinate system of the measurement reference of the measurement device; measuring a first angle gamma at which the paddle deflects around an axis parallel to the first direction; measuring a second angle alpha at which the paddle deflects about an axis parallel to the second direction; measuring a third angle beta at which the paddle deflects about an axis parallel to the third direction; and adjusting the position of the paddle so that the first angle gamma reaches a first set value, the second angle alpha reaches a second set value, and the third angle beta reaches a third set value. According to the method for correcting the deflection of the paddle, the measuring device is in communication connection with the upper computer, the actual coordinates of the paddle in the selected three-coordinate direction are measured through the measuring device, the upper computer calculates and obtains the deflection angle of the paddle around the axis parallel to the three-coordinate direction, the deflection operation of the paddle can be completed by adjusting the angle to the set value, and the efficiency is high.

The utility model relates to the technical field of multi-rotor aircrafts, and particularly discloses a multi-rotor aircraft propeller suitable for plateau areas, the spanwise direction is the direction from the blade root to the blade tip, the chordwise direction is the direction perpendicular to the spanwise direction, the distance between the front edge and the rear edge of the position where an airfoil is located is the chord length C of the airfoil, and the chord length C of the airfoil is larger than the chord length C of the airfoil. The included angle between the chord line of the airfoil and the blade rotor plane is a torsion angle alpha, the vertical connecting line between the rotation center of the propeller and the blade tip is L, the distance between the front edge point of the airfoil and the L is Yq, the distance between the rotation center of the propeller and the blade tip is R, and C, Yq and alpha are all maximum values at the position 35% R away from the blade root. C, alpha and Yq are gradually increased from the blade root to the maximum chord length position, and C, alpha and Yq are gradually reduced from the maximum chord length position to the blade tip. By adopting the structural design, the flight requirements of plateau areas can be met.

The invention relates to the technical field of tires, in particular to a method for judging the theoretical calculation flat-width matching degree of a tire. According to the method, the included angle alpha between the relative straight line of the tire cord and the horizontal datum line and the vertical distance beta between the farthest tire cord and the horizontal datum line are clearly measured, and the specific judgment threshold value is set, so that a traditional subjective judgment mode depending on the number of bent cords and the rubber seepage amount in a finished product X-ray image is replaced; the judgment result of the flatness and width suitability is more accurate and traceable, and misjudgment caused by human experience difference is avoided.

The invention discloses a vacuum coating device and a coating uniformity correction method. The vacuum coating device comprises a vacuum chamber, a first target material group, a second target material group and a base, the first target material group and the second target material group are arranged in the vacuum chamber; the base is rotatably arranged in the vacuum chamber around a first axis, and the first target group and the second target group are respectively arranged on two sides of the first axis; the workpiece is rotatably arranged on the base around a second axis, and the first axis and the second axis are arranged at an included angle; the workpiece comprises a first surface group and a second surface group which are adjacent to each other and form an included angle, and establishing a rectangular coordinate system in a first plane perpendicular to the first axis by taking an intersection point of the first axis and the first plane as an original point and taking a midline of the first target group and the second target group as an X axis, the included angle between the projection line of the first surface group on the first plane and the X axis is alpha, and the angle alpha is 40-50 degrees. By adopting the scheme, the problem that the coating uniformity on the surface of a workpiece is difficult to correct is solved.

The invention provides a parameter optimization method for a rotary cultivator with a low-speed small-bending-angle rotary blade, belongs to the field of agricultural mechanical equipment, and analyzes, researches and optimizes the bending angle of the existing rotary blade, the edge angle of the rotary blade and the rotating speed of a rotating body. The bending angle alpha of the rotary blade, the cutting edge angle beta of the rotary blade and the rotating speed n of the rotating body are used as test factors, the soil crushing rate M and the torque T are used as evaluation indexes, three-factor and three-horizontal orthogonal tests are carried out on the machine tool, and after range and variance analysis is carried out on the test results, the obtained better structure parameter combination is as follows: the bending angle alpha of the rotary blade is equal to 132 degrees, and the bending angle beta of the rotary blade is equal to 132 degrees; the edge angle beta of the rotary blade is 20 degrees, and the rotating speed n of the rotary body is 150 r / min; according to actual production requirements, the better structure parameter combination is adjusted as follows: the bending angle alpha of the rotary blade is equal to 132 + / -5 degrees, the cutting edge angle beta of the rotary blade is equal to 20 + / -2 degrees, and the rotating speed n of the rotary body is equal to 150 + / -10 r / min; the rotary cultivator used by the optimization method comprises a rack, a rotary body and a transmission assembly. The parameter optimization method is novel, the structural parameter combination is reasonable, the soil crushing rate is high, and the machine load is small.

The invention discloses a method for realizing straight pyramid scanning by a communication-in-moving antenna. The method comprises the following steps: determining the value of a scanning position point number parameter N; determining values of an expected azimuth angle alpha 0 and an expected pitch angle beta 0 of the current antenna; setting a scanning counter i; determining the value of the maximum scanning offset angle delta A in the azimuth angle direction and the value of the maximum scanning offset angle delta E in the pitch angle direction, and calculating the values of parameters phi 1 and phi 2; when i is less than 4N, calculating a parameter theta i, calculating a scanning offset angle delta i, calculating a scanning track beta i of a pitch angle, and calculating a scanning track alpha i of an azimuth angle; the pitch angle of the antenna is controlled to rotate to a new position beta i, and the azimuth angle of the antenna is controlled to rotate to a new position alpha i; and updating the scanning counter i, i = mod (i + 1, 4N), and returning to execute. The method is suitable for a communication-in-moving antenna with a convex cross section of a beam main lobe directional diagram, the application range is wider than that of elliptic cone scanning, and a higher average receiving level can be obtained.

The invention belongs to the technical field of aircraft design, and particularly relates to a variable-pitch pull rod adjusting and fixing device and method. The device comprises a base and four column bodies integrally formed with the base. U-shaped grooves are formed in the upper part and the lower part of the base; the side wall of the U-shaped groove is parallel to the side wall of the rectangular hole, and an angle alpha is formed between the side wall of the U-shaped groove and the vertical direction and ranges from 3 degrees to 8 degrees; the four columns are respectively positioned at four corners of the base; and the A surface of each column body is coplanar with the side wall of the U-shaped groove.

The utility model relates to the technical field of tunnel construction, in particular to an angle control tool for a tunnel feet-lock anchor pipe. The tool comprises a steel plate, a mounting base, a first support, a second support, a guide pipe and a steel frame, the steel plate is included, positioning assemblies are arranged on the two sides of the steel plate in a mirror symmetry mode, and each positioning assembly comprises a mounting base, a first support, a second support and a guide pipe; the second support and the first support are arranged on the mounting base from top to bottom, the second support is shorter than the first support, and the guide pipe is obliquely mounted above the first support and the second support. The inclination angle alpha between the guide pipe and the horizontal plane can be adjusted to be 10-20 degrees, it is guaranteed that the angle meets the standard requirement when the feet-lock anchor pipe is driven in, and therefore the grouting fullness and the steel frame stability are improved. The tool has the advantages of being easy to manufacture, convenient to construct, capable of being repeatedly used, safe, economical and the like, the problem that the angle of the anchor pipe is difficult to control in manual operation is effectively solved, and the steel frame sinking risk caused by the fact that the angle does not meet the standard requirement is reduced.

The utility model relates to the technical field of machining, and particularly discloses an integral alloy boring cutter with a cutting groove, which comprises a cutter head and a cutter body, the cutter head is fixedly connected with the cutter body and is positioned at one end of the cutter body, the integral length of the cutter head and the cutter body is 45mm, the cutter head is provided with a cutter tip included angle alpha, the cutter tip included angle alpha is 60 degrees, and the cutter tip included angle alpha is 45 degrees. The end portion of the included angle alpha of the tool nose is provided with an arc chamfer R1 with the radius of 0.25 mm, the upper end of the tool bit is further provided with an inverted triangular caulking groove, the length L of the tool bit is 3.2 mm, and the tool bit is further provided with an inclined angle beta which is 8 degrees. The inverted triangular caulking groove structure is additionally arranged at the end part of the tool bit, so that chips can be effectively prevented from being accumulated on the tool bit and a workpiece during machining, meanwhile, an operator can be prevented from being scratched, the service life of the boring tool is prolonged, the surface smoothness of the machined workpiece is improved, complicated and difficult materials are favorably machined, and the production cost is reduced. The safety of the boring cutter in use is improved, and machining errors are reduced.

The invention provides a lift coupling structure for a semi-annular empennage aircraft, a connecting rod is arranged below a wing of the semi-annular empennage aircraft, and the front end and the rear end of the connecting rod are respectively provided with a lift propeller; the maximum included angle alpha between the rotation contour of the lift propeller located at the front end of the connecting rod and the outer contour of the front fuselage on the vertical projection plane and the rotation center of the lift propeller is 45 + / -5 degrees; the maximum included angle beta between the rotation center of the lift propeller and the overlapping area of the rotation contour of the lift propeller located at the rear end of the connecting rod and the outer contours of the rear fuselage and the rear edges of the wings on the vertical projection plane is 90 + / -5 degrees. According to the lift coupling structure, the coupling area is designed between the lift propeller and the wing body fusion body, the rotating contour, affected by the wing body to the greatest extent, of the lift propeller is shielded below the fuselage and the wings, so that the propeller tip is shielded to weaken the propeller tip vortex, and the lift loss is further reduced.

A seal includes an annular jacket including a body including a heel, a first lip, and a second lip, the heel, the first lip, and the second lip defining an annular recess oriented downwardly along a central axis, where the first lip is substantially parallel to the central axis, and the second lip is substantially parallel to the central axis. Wherein the second lip comprises an angled portion adjacent the heel and a planar portion adjacent the angled portion, where the angled portion forms an angle alpha with a line perpendicular to the central axis, where alpha is between 30 DEG and 90 DEG, where the heel has an axial length LH, where the first lip has an axial length LFL, and where LH < = 3 LFL.

According to the lift coupling propelling structure for the semi-annular empennage aircraft, propelling propellers are arranged at the tail end of a fuselage of the aircraft, connecting rods are arranged below wings, and lift propellers are arranged at the front ends and the rear ends of the connecting rods; the tail end of the rear part of the connecting rod is connected with a semi-annular empennage; the minimum vertical height L from the highest point of the front edge of the semi-annular empennage to the tip of the propelling propeller is equal to 0.1-0.2 time of the radius R of the tip of the propelling propeller; the maximum included angle alpha of the overlapped area of the rotating contour of the lift propeller and the outer contour of the front fuselage is 45 + / -5 degrees; the maximum included angle beta of the overlapped area of the rotating contour of the lift propeller and the outer contour of the rear fuselage and the outer contour of the rear edge of the wing is 90 + / -5 degrees. According to the lifting force coupling propelling structure special for the semi-annular empennage, by optimizing the coupling relation between the propelling propeller and the semi-annular empennage and the coupling relation between the lifting force propeller and the fuselage wings, the propelling efficiency of the propelling propeller can be remarkably improved, and the lifting force loss of the lifting force propeller is reduced.

The molten iron pretreatment stirring device comprises a stirrer, the stirrer is obliquely inserted into molten iron, the included angle alpha between the stirrer and the horizontal direction is adjustable within the range of 20-60 degrees, the stirrer comprises a stirring rod and stirring rods, the multiple stirring rods are arranged in an axial symmetry mode with the stirring rod as the axis, the stirring rods are parallel to one another, and the stirring rods are parallel to one another. And the stirrer is driven to rotate by taking the stirring rod as an axis. Compared with the prior art, the method has the beneficial effects that 1, the stirring rod directly stirs the desulfurizing agent into the iron liquid, and good dynamic conditions for mixing the iron liquid and the desulfurizing agent are obtained; and 2, as the rotating flow field with the included angle of 20-60 degrees with the vertical direction is obtained, the material exchange rate between the slag and the molten iron is far higher than that of a traditional stirring method.

The invention discloses a dot-shaped three-dimensional stitching method for embroidery, and aims to solve the problems of strong texture mechanical feeling, insufficient three-dimensional layering and lack of natural dislocation effect in the conventional embroidery. According to the stitching method, a parallel basic stitch sequence is formed by presetting a deviation angle alpha (15-75 degrees) and a distance d (0.3-0.7 L), filling stitches (the included angle beta between the filling stitches and basic stitches ranges from 45 degrees to 90 degrees, and the length ranges from 0.4 L to 0.8 L) are embroidered in gaps of the adjacent sequences to jointly form eight-shaped topological closed units, the units are approximately octagonal, and adjacent vertexes are regularly staggered. The optimization parameters comprise that alpha is preferably 45 degrees, d is 0.4-0.6 L, beta is preferably 90 degrees, and the density of filling pins is higher. According to the stitching method, tension is dispersed through mechanical coupling, the stability is enhanced through geometric constraint, the texture natural sense, three-dimensional hierarchy and durability are improved, the cloth deformation rate is reduced by 18%-22%, the embroidery thread durability is improved by 200 times or more of friction cycles, and the stitching method is suitable for precise operation of an industrial embroidery machine.

The application relates to the technical field of bearing processing, in particular to an inner ring feeding device and method. The inner ring feeding device comprises a first fixed pipe, a second fixed pipe and a flexible assembly comprising a first flexible section and a second flexible section; the first fixed pipe, the first flexible section, the second flexible section and the second fixed pipe are sequentially connected and form a feeding channel; the first flexible section is arranged in a semicircular shape; the feeding direction of the feeding channel is from top to bottom; the central axis of the first fixed pipe is arranged at intervals with the central axis of the second fixed pipe; the preparation state of the feeding device comprises that the minimum included angle alpha between the arc surface normal of the first flexible section and the feeding direction of the first fixed pipe is less than or equal to a set value; the feeding state of the feeding device comprises that the arc surface of the first flexible section is extruded by the inner ring so that the minimum included angle alpha is reduced. Thus, the problem that the surface of the inner ring is damaged due to collision in the conveying process of the inner ring feeding device is solved.

The invention relates to a pneumatic tire (1) having a radial carcass reinforcement, two working crown plies (41, 42) and a circumferential reinforcing element ply (43), the two working crown plies (41, 42) and the circumferential reinforcing element ply (43) being the only layers for forming the crown reinforcement (4) over at least 75% of a width L5 of the tread (5), the absolute value of the difference between the angle alpha 2 and the absolute value of the angle alpha 1 is larger than 7 degrees, the absolute value of the angle alpha 2 is larger than the absolute value of the angle alpha 1, and the average angle alpha meets the relational expression 13 + 131 * exp (-L / 100) lt; [alpha] [lt]; and 28 + 110 * exp (-L / 100). According to the invention, the rubber mixture constituting said ply C comprises a composition comprising from 40 phr to 70 phr of a reinforcing filler, said reinforcing filler comprising at least 10 phr of pyrolytic carbon black.

The high-strength and high-sharpness shaving blade comprises a blade body part and a blade tooth part, the cutter tooth part comprises a plurality of cutter tooth bodies evenly distributed at the front end of the cutter body part, and a cutter tooth groove is formed between every two adjacent cutter tooth bodies. The bottom of the cutter tooth part further comprises a shovel-shaped body, and the shovel-shaped body enables the cutter tooth groove to have a closed lower end and an open upper end; a reinforcing body with a triangular section is arranged between the shovel-shaped part and each cutter tooth body, and the inclination angle alpha of the side edge of the reinforcing body is larger than or equal to 30 degrees and smaller than or equal to 60 degrees. According to the utility model, the structural characteristic of the shovel-shaped body is added, and the cutter tooth bodies are connected in series, so that the effect of reinforcing the structure is achieved, the pressure can be effectively shared, and the probability that the cutter teeth are broken due to stress is greatly reduced. The blade is provided with the reinforcing body, the reinforcing body is located at the junction of the shovel-shaped part and the blade teeth, the structural strength is further improved, the reinforcing part can guide the hair to move towards the blade tooth grooves in the two sides, then the probability that the hair is accumulated and blocked in the local part is reduced, and the chip removal and shaving efficiency is improved.