139results about How to "High profile precision" patented technology

The invention provides an umbrella-shaped antenna reflector which comprises a base, a fixing face part, a foldable part, a mesh face part and a driving assembly. The fixing face part is a fixing face reflector body. The foldable part comprises a plurality of unfolding ribs. The mesh face part comprises a front tension mesh and a rear tension mesh. The driving assembly comprises a motor and a power rope. The fixing face part is fixedly connected with the base. The foldable part is connected with the base in a hinged mode. The mesh face is arranged on the foldable part. The umbrella-shaped antenna reflector can be unfolded smoothly through the driving assembly. The umbrella-shaped antenna reflector is provided with a large diameter and high in accuracy, has the advantages of being high in molded surface accuracy, high in molded surface keeping capacity, high in stability and high in reflection efficiency and can be applied to the outer space, and the unfolding ribs are large in rigidity.

The invention relates to the technology field of communication and observation control, which provides a composite material satellite antenna reflection plane and the method for preparation. The composite material satellite antenna reflection plane adopts 3D glass fiber felt as core material, and adopts carbon fiber composite as covering sandwich type composite material satellite antenna reflection plane. Compared with the prior art, the invention has the following advantages: 1. shaped surface accuracy of the satellite antenna reflection plane is high and satellite signal gain is great, 2. quality of the reflection plane is light, and is fit for transportation, in particular to fitting for vehicle satellite antenna and portable satellite antenna, 3. integrality of the reflection plane is good, hardness is great, thereby being capable of preferably retaining the shaped surface accuracy and bearing more wind load and impact load, 4. adopting the 3D glass fiber felt as the core material, the invention inaugurates a new technology of the sandwich composite material satellite antenna reflection plane, the technology is capable of producing heavy caliber satellite antenna reflection plane, and which is simple in manufacturing technology comparatively and low in the cost.

The invention provides forming equipment of a large size composite stringer, belonging to the forming technology of composites. The invention relates to improvement of the forming equipment of the large size composite stringer. The section of the stringer is I-shaped, inverse J-shaped or inverse T-shaped. The forming equipment comprises a first mandrel [1] and a second mandrel [2]. The invention is characterized in that the whole forming equipment comprises a plane base plate [5], 1-15 mandrel modules which are arranged on the base plate [5] and are placed in parallel along the width direction of the base plate [5], first mandrel [1] locating mechanisms and 2-20 second mandrel [2] locating mechanisms which are fixed on the base plate [5], arranged parallel to each other along the length direction of the base plate [5] and vertical to the mandrel modules. The base plate has no profile and the first mandrel 1 and the second mandrel 2 have high rigidity, thus greatly reducing deformation of the stringer profile and improving the profile precision and the qualified rate of the stringer workpieces.

The invention provides a sunflower type solid antenna capable of being spread. The sunflower type solid antenna capable of being spread aims at resolving the problems that mesh type and inflatable antenna molded surfaces are not high in precision and limited in working frequency at preset. According to the sunflower type solid antenna capable of being spread, a regular dodecagon plate body serves as a base, six driving shafts and six universal shafts are arranged in a staggered mode along the edge of the base, each driving shaft is connected with a corresponding edge on the base through the corresponding driving shaft support, the two ends of each driving shaft are respectively connected with one end of an adjacent universal shaft, each driving shaft is connected with the lower end of a main spherical shell, the other side of each auxiliary spherical shell is connected with the other side of an adjacent auxiliary spherical shell through a spherical hinge mechanism, the middle of each universal shaft is connected with the lower end of a connecting rod, and the upper end of each connecting rod is connected with the corresponding spherical hinge mechanism. The sunflower type solid antenna capable of being spread is used for the field of antennas.

The invention discloses a satellite-borne solid-surface deployable antenna which is composed of a solid-surface reflector, a deployable mechanism and a driving component. The deployable mechanism is composed of multiple synchronous three-bar deployable units and synchronous two-bar deployable units combined in an array. The solid-surface reflector is composed of a plurality of rigid sheets. The driving component includes a driving motor and an elastic energy storage element. The solid-surface reflector and the deployable mechanism are connected through a universal hinge. Under the action of the driving motor, the solid-surface reflector realizes first spatial synchronous deployment through the deployable mechanism. Under the action of the elastic energy storage element and a compression spring, the solid-surface reflector realizes second spatial synchronous deployment. After deployment, any two adjacent panels of the solid-surface reflector are hinged and locked by a locking mechanism,and the whole antenna is stabilized in a fully deployed state. The satellite-borne solid-surface deployable antenna has the characteristics of large deployment aperture, high deployment and support stiffness, and high precision of surface profile, and can be used as a reflector or a collector in space or on the ground.

The invention provides a manufacturing method for a large-scale thin-wall skin with inner ribs and complex mold cavities. The manufacturing method comprises the steps that 1, simulation flattening is conducted on the skin according to a skin parameter, a parameter of the flattened skin is collected, a rough machining programming and a finish machining programming are conducted, and a minimum workblank is calculated; 2, the minimum workblank is selected to be machined roughly in order to release residual stress inside the workblank in advance; 3, a roughly machined skin plate is adsorbed and fixed through a vacuum tire, finish machining is conducted on the skin plate, and the rib strips and the weight reducing cavities inside the skin are machined out through numerical control milling machining; 4, a plurality of base plates which can fill and level up each weight reducing cavity are prepared, it is ensured that the skin machined through the step 3 again becomes a slab with the flat surface after each base plate is cushioned, and then the skin is machined to be formed through a matched mould thermal forming method, and 5, annealing and stress-relieving are conducted. According to the manufacturing method for the large-scale thin-wall skin with the inner ribs and the complex mold cavities, the deformation of the thin-wall skin in the machining process is effectively controlled, and the molded surface precision of the skin is greatly improved.

The invention belongs to the technical field of antennas and discloses a cable net parabolic cylindrical deployable antenna device based on a double-scissor truss mechanism. The metal mesh reflector adopts soft gold-plated molybdenum wires or tungsten wires to be woven into a mesh. The supporting cable net comprises transverse flexible cables, longitudinal flexible cables and vertical adjusting cables, each longitudinal flexible cable is parabolic, and is woven with the transverse flexible cables to form a front and a rear parabolic cylindrical net surface, and the vertical adjusting cables are connected with the front and the rear net surfaces; A parabolic cylindrical support cable net formed by braiding flexible cables; A metal wire mesh is fix on that cable net to form a parabolic cylindrical reflecting surface, and the shape surface accuracy of the metal wire mesh reflecting surface is adjust by adjusting the force on the flexible cables in the supporting cable net; The deployabletruss is used to suspend the supporting cable network to deploy the antenna. The deployable truss mechanism is integrally square, and is formed by a plurality of deployable units A in series. The invention does not need to add a complex driving mechanism and an additional synchronous mechanism, has a simple and reliable structure, and reduces the complexity of antenna design.

The invention relates to a forming method of a complex structural part, and belongs to the technical field of precision forming machining. The complex structural part is of an equal-cross-section structure with a transverse rib or a boss (except for the transverse rib or the boss, the other portion is of the equal-cross-section structure), or is of a double-side asymmetric deep cavity structure with a web plate. The composite manufacturing method of combining the arc additive and hot extrusion makes full use of the characteristics of high efficiency and low cost of the hot extrusion and arc additive manufacturing technology, so that the defect that the arc additive method and the hot extrusion method can only form a relatively simple structural part is avoided, and rapid and efficient manufacturing of the complex structural part is realized; and secondly, the mechanism based on the fact that the melting depth can be increased by an active agent is utilized to coat a region needs to undergo arc additive manufacturing on an extrusion substrate with a layer of active agent, so that the connecting performance of an interface is further improved, and the high-performance manufacturing of the complex structural part is realized.

The invention discloses a process used for machining an inner gear ring with large module and deep tooth space, which comprises the steps of forging, normalizing, rough turning, finish turning, gear shaping and gear broaching. For forging, 20CrMnTi material is chosen, an excircle with 4mm of thickness is added, an inner diameter is decreased by 4mm, and the total height is increased by 4mm on the basis of a finished product dimension to form a forging dimension; for normalizing, a gear ring is placed at high temperature for heat preservation for a time period and then drawn from a furnace for air cooling; for rough turning, oxide scale and most of allowances are removed for the air-cooled gear ring, and 0.5mm allowance is left at each side; for finish turning, the thickness of the excircle and the total height of the gear ring after rough turning is processed to the desired dimension through finish turning, and the inner hole has 0.2mm allowance left; for gear shaping, gear shaping is carried out to the inner gear ring of the gear ring after finish turning, and an inter-rod distance dimension is shaped to be 0.4 mm less than that of a finished product; and for gear broaching, finally a tooth shape and the small diameter of the inner gear ring are broached to the finished product dimension to obtain the finished product of the inner gear ring. The process of the invention can effectively improve the gear shape precision and the consistency of gear ring dimensions, and reduce the internal stress of the gear ring.

A large mesh antenna reflector profile high-precision test method is provided. By using high-precision industrial digital photogrammetry technology, a single camera is used for separately recording the images of the same scene in a space from different locations and directions. By means of image processing and according to known camera parameters, the three-dimensional coordinates of the scene relative to a coordinate system in the space are calculated. The profile precision of the mesh antenna is obtained by fitting the coordinate values with a theoretical profile. In order to improve the profile measurement precision of a large-caliber small-datum and high-precision large flexible mesh antenna reflector, by means of a designed reference conversion device, a high-precision long reference ruler, the large mesh antenna reflector profile is subjected to high-precision testing by optimal technological parameters of the photogrammetry system.

The invention relates to the technical field of moulds and discloses a mould machining method and system. The mould machining method comprises calculating numerical control data according to the mould machining technical process; performing correction on the numerical control data according to the characteristics of changes of the profile of a mould; obtaining the mould according to the corrected numerical control data. According to the mould machining method and system, profile grinding match workloads of bench workers in the mould machining process and the error produced when the profile is manually finished can be reduced and the accuracy of the profile of the mould can be improved.

The invention discloses a cable section tension variance optimization-based design method for a cable net structure of a deployable satellite-borne antenna. The cable net structure of the deployable satellite-borne antenna consists of a front cable net surface, a back cable net surface and a longitudinal pull cable; when the cable net structure is designed, all cable net surface nodes fall on a paraboloid through a force density iterative method; meanwhile, boundary nodes of the front and back cable net surfaces are subjected to boundary cable section and annular truss reconnection by taking a regular hexagon in the cable net structure as an effective reflective surface, and serve as basic mesh configuration of the cable net structure of the deployable satellite-borne antenna; and then, by taking cable section tension of the front and back cable net surfaces and tension of the longitudinal pull cable as design variables, taking a cable section tension variance of the front and back cable net surfaces as a target function and taking boundary node fixation as a constraint condition, the cable net structure of the deployable satellite-borne antenna is designed. According to the method, excellent structure layout of the deployable satellite-borne antenna is realized, so that the stability and reliability of the deployable satellite-borne antenna can be remarkably improved.

The invention discloses a high-precision numerically-controlled rotor grinding machine which comprises such components as a machine body, a workbench, a head frame, a tail frame, a grinding wheel rack, a precision grinding tool and a grinding wheel mechanism; the machine body adopts a numerically-controlled forming grinding method, a mathematical model that the motion trail of a trimming roller is conjugate with a forming surface is established, and the movement of two shafts of a grinding wheel dresser is controlled through a numerical control device to enable the arc center of a diamond roller to generate linkage in two coordinate directions, and the grinding wheel is dressed into a required forming surface. During processing, the grinding wheel is fully contacted with the outline of a workpiece, and numerically-controlled forming grinding is realized by utilizing lengthwise movement of the workbench, precision indexing movement and transverse feeding movement of the grinding wheel, so that a rotor can be ground into a required shape. The high-precision numerically-controlled rotor grinding machine has the advantages that the grinding profile accuracy reaches 0.01 mm, the tooth surface roughness can be Ra 0.2 to 0.32, the production efficiency is increased by at least two times compared with that of the traditional milling process, and the processing cost is reduced greatly compared with that of milling.

The invention provides an accurate forming method for a large-curvature and high-order-difference edge sealing frame. The accurate forming method is characterized by comprising the following steps that a rectangular blank is blanked, the margin of 15 mm is added to each of the two edges, in the width direction, of the blank on the basis that the part is expanded in the width direction, the length between a die to a transition section of a stretch bending equipment jaw and the length between the die and a clamping section of the stretch bending equipment jaw are added to the blank length during stretch bending forming on the basis of the length of the stretch bending forming die; trichloro ethylene vapor degreasing is conducted on the blank, the surface of a part is cleaned, burrs on the edge of the blank are removed, and an end face is sanded through abrasive paper; and a bending forming machine is used for conducting pre-forming on the blank, the order difference, the bending radius and the angle of the blank are completely the same with those of the part, the blank is pre-bent to form a ruled-surface transition part with a 45-degree Z-shaped section, the two ends of the blank are flattened to have the clamping width of the stretch bending forming machine jaw, and therefore clamping is facilitated.

The invention provides a 3,350mm-level ellipsoid scalloped segment liquid-filling and forming process and a die thereof. A hydromechanical deep drawing forming mode is adopted. The hydromechanical deep drawing forming mode comprises the following specific steps: a, cleaning: removing sundries on a molded surface of the die and the surface of a blank before liquid filling; b, uniformly smearing an integral molded surface of a male die of the die with lubricating oil; c, filling of a liquid filling chamber: enabling a liquid filling chamber of a female die to be filled with hydraulic oil; d, loading: placing the blank on the female die, adjusting the front and rear positions of the blank to enable the blank to be centered, and adjusting the liquid level of the liquid filling chamber to be parallel and level to the blank; e, paving an annular plastic film on one side, which is in contact with a blank holder, of the blank, and paving a plastic film of which the shape is consistent to that of the blank on the other side, which is in contact with the liquid filling chamber, of the blank; f, hydromechanical deep drawing of a part: controlling the matching relation between the pressure of the liquid-filling chamber and a blank holder force, and carrying out hydromechanical deep drawing forming on the blank; and g, unloading. A one-time liquid-filling forming process is adopted, liquid-filling forming of a 3,350mm-level ellipsoid scalloped segment is realized, a qualified product which meets use requirements is obtained, and the quality of the surface of the part and the precision of the molded surface are improved remarkably.

The invention provides a method for manufacturing a suspension bridge tie rod. The method comprises the following steps of: (1) arranging a blank on a machine tool and roughly cutting the tie rod by using a forming tool; (2) tempering and aligning; (3) roughly cutting tooth form of the tie rod by using the forming tool; and (4) finely extruding the tie rod tooth form to obtain the tie rod workpiece. The completely new method for manufacturing the suspension bridge tie rod of the invention has the advantages of high glossiness of the extrusion, high fineness of the tooth form and easiness of cutting of a material by threading, guarantees the quality and also improves the efficiency. The method is a preferred scheme for manufacturing the type of tie rods with diameter of more than phi 50 and long radius ratio of between 20 and 30; and the method grantees the quality, has high manufacturing capacity and high efficiency and is suitable for large-scale use and popularization.

The invention provides a novel continuous molding mould for an ultrathin component. The novel continuous molding mould comprises a left baffle 1, a front baffle 2, a male mould 3, a flexible mould 4, a right baffle 5, a female mould 6 and a rear baffle 7, wherein the male mould 3 has a convex curved surface; the female mould 6 has a concave curved surface at a position corresponding to the convex curved surface; the circular arc radius of the convex curved surface is equal to that of the concave curved surface; the male mould 3 is covered with the flexible mould 4; the left baffle 1, the front baffle 2, the rear baffle 7 and the right baffle 5 are respectively in screw joint to the periphery of the male mould 3 and are used for blocking the flexible mould 4. According to the novel continuous molding mould, the flexible mould and a fixing device of the flexible mould are additionally arranged, so that a composite material component for a large ultrathin non-equal-thickness complex satellite can be prepared with high accuracy; the product is excellent in surface quality, high in accuracy of the molded surface and excellent in performance; the problem of molding of the composite material component for the large ultrathin non-equal-thickness complex satellite can be solved; the problems of poor appearance quality, high porosity and poor accuracy of the molded surface caused by uneven pressure distribution of a metal mould due to the non-equal thickness of the product can be solved.

The invention discloses a simple method for generating a reflecting surface cable net of a cable net antenna, which comprises the following steps: generating a reference spherical surface; dividing the reference spherical surface into six identical sub curved surfaces; taking one of the sub curved surfaces; equally dividing two main cables on the two sides of the sub curved surface at a uniform angle; generating an initial coordinate formula of a group of cable net nodes; according to the difference between each cable unit length and the length ls of a standard cable unit, generating a displacement matrix of free node coordinate correction, and then generating a corrected node coordinate of the free node, obtaining a corrected sub curved surface cable net and the total cable length of thesub curved surface cable net, determining the difference between the total cable length of the sub curved surface for the first time and that for the second time; enabling the difference between the total cable length of the net for the former time and that for the last time to be less than a convergence threshold through multiple iteration corrections; and rotating the obtained sub curved surfacenet by an angle of phi/3 around the central axis of the paraboloid of revolution to generate the entire reflecting surface cable net. Compared with the common projection method and geodesic method, the length of the reflecting surface cable net unit generated through the simple method in the invention is more uniform, especially in the case that the focal length-caliber is relatively small.