36results about How to "Guaranteed coaxiality accuracy" patented technology

The invention discloses a process method for controlling welding deformation with high precision. The process method is embodied in effective control of form and location tolerance in a welding structure, and comprises a preparation stage, a positioning stage and a welding stage. In the preparation stage, a trunnion block combination and a fan-shaped block are machined and assembled respectively,and a weld groove is machined; in the positioning stage, a position of a trunnion is aligned, and then a marking device is arranged, so that the offset condition of the trunnion is conveniently detected in the welding stage; in the welding stage, welding is conducted in a symmetrical and synchronous mode, deformation conditions are monitored by means of marks and a dial indicator, and welding parameters are adjusted in real time. The process method changes the conventional process, finish machining of the two trunnion parts is firstly completed, then assembling and welding are conducted on thesame, the welding stress is made to be in a relatively low and symmetrical balance state by adopting a high-precision detection control method, a reasonable welding sequence and a flexible control means, and therefore the purposes of controlling connection deformation and guaranteeing the workpiece precision are achieved.

The invention discloses an end face sealing test device for a liquid rocket engine turbine pump under a low-temperature and a high-speed. The device is applied to a sampling test of an end face sealing assembly of a rocket engine of a liquid hydrogen liquid oxygen propellant, in a running-in test and a research performance test, an end face sealing assembly product ( such as an engine static ringassembly and an engine moving ring ) is assembled in the test device of the invention, a working environment of the engine turbine pump is simulated, the sealing performance and the structural rationality of the sealing assembly product are checked, and the sealing performance of the sealing assembly product can be quantitatively detected. According to the device, the test device does not contractand deform under a low-temperature environment, and runs stably at a high speed, the device provides an important basis for improving various problems in the design of the end face sealing assembly product.

The invention provides a low-temperature and high-speed floating ring sealing test device for a rocket engine, which includes a casing, which includes a casing I, a casing II and a casing III; a stepped main shaft arranged inside the casing; The front floating ring seal assembly and the rear floating ring seal assembly; the front floating ring seal assembly and the rear floating ring seal assembly form a test chamber in the housing II. The low-temperature and high-speed floating ring sealing test device for a rocket engine according to the present invention has strong functionality, good compatibility, good performance at low temperature and high speed, and can carry out various low-temperature sealing tests of floating rings, which can verify the integrity of the floating ring assembly. The sealing performance can also be used to assess the rationality of the floating ring structure.

The invention relates to a device for on-load testing and accuracy calibration of steering engine component, and belongs to the technical field of high-precision steering engine testing. On the basisof the steering engine component and a substrate, the on-load testing part is coaxially connected with the output shaft of the one-way steering engine to test the rated load of the steering engine successfully; the precision calibration part is coaxially connected with the output shaft of the side one-way steering engine and achieves high coaxial precision, high-precision transmission angle and torque, so that the precision calibration of the steering engine is realized; the whole device can simultaneously realize the on-load testing and precision calibration of the steering engine component,has the advantages of simple structure, high integration level and convenient operation.

The invention discloses a processing technology of a robot RV speed reducer needle gear shell, and belongs to the technical field of robot RV speed reducer processing. The processing technology includes the steps that precise casting or forging is carried out on a needle gear shell blank; the needle gear shell blank is clamped after the surface of the needle gear shell blank is machined, and the rotation center of the needle gear shell blank is taken as a positioning reference; the end face of the needle gear shell blank, a bearing position of a roller pin bearing and bearing positions of two main bearings are machined; finish machining is carried out on the inner surface of the roller pin bearing according to the positioning reference; finish machining is carried out on a roller pin groove in line contact with a roller pin of the roller pin bearing according to the positioning reference; inner grooves are simultaneously machined in the bearing positions of the two main bearings in a finish machining mode according to the positioning reference; finish machining is carried out on the outer surface of the needle gear blank. The needle gear shell machined according to the steps improves machining precision and the parallelism degree of the bearing positions of the main bearings, guarantees coaxiality, the position degree and cylindricity of the main bearings after installation, achieves one-time clamping, can meet requirements of multiple process parameters, improves machining precision and installation precision of the needle gear shell, reduces accumulated errors, meets the high-precision requirements, and prolongs service life.

The invention provides a special double-spindle numerical-control boring machine high in precision and efficiency. The special double-spindle numerical-control boring machine comprises a body. A bench is disposed in the middle of the body, carriages are disposed on left and right sides of the body respectively, positioning clamping devices are symmetrically mounted at left and right ends of the top of the bench respectively, a boring power head is mounted above each carriage, two boring tools are mounted on each boring power head, each carriage is connected to the body through a driving device, a guard covering the whole body is disposed above the body, the middle of the guard is provided with a sliding door driven by an air cylinder, each boring tool is provided with at least one group of tool bits, and an automatic scrap discharger, an air pump device, an oil pump device and a cooling pump device are rested on the back of the body. The special double-spindle numerical-control boring machine is provided with the two boring power heads in bilateral symmetry for machining two workpieces simultaneously, each boring power head is provided with two boring tools for machining two holes of each workpiece simultaneously, and the efficiency of the special double-spindle numerical-control boring machine is ten times of that of the common boring machine. The special double-spindle numerical-control boring machine is provided with the guard and the automatic scrap discharger, the whole machining process is under control of a control cabinet, and the machining environment is closed and neat.

The invention belongs to the technical field of hypersonic wind tunnel equipment design, and discloses a structural design method for an axisymmetric nozzle of a hypersonic wind tunnel. The structural design method includes the following steps: aerodynamic segmental design, structural segmental design, processing segmental design, mechanical analysis of each segment, material selection of each segment, machining accuracy, coaxiality, step difference, roughness and gap accuracy of each segment Indicators, the cooling method of each section and the nozzle are sealed with the test section. The structural design method is a structural design method that can ensure that the axisymmetric nozzle of the hypersonic wind tunnel meets the quality requirements of the velocity field of the hypersonic wind tunnel nozzle in the national military standard; it can reduce the risk of design and processing. This structural design method has been applied in the design of axisymmetric nozzles in hypersonic wind tunnels of Ф0.5m, Ф1m and Ф2m levels, and the obtained maximum Mach number deviations in the uniform velocity field of the nozzles are all less than 1 %, meeting the requirements of the national military standard.

The invention discloses a device and method to machine root fitting holes in the sidewall of an inner chamber of a composite part. The device is a six-DOF (degree of freedom) cantilever machining device, comprising an X-directional linear moving part, a Y-directional linear moving part, a Z-directional linear adjusting part, an X'-axis cantilever hole-making unit, a Y'-axis rotary adjusting part and a Z-axis rotary adjusting part. A pneumatic motor is used as a rotary spindle power source, so that the device has small size and high speed and is suitable for machining boreholes in composites innarrow spaces. A grinding hole-making mode herein can provide reduced X'-axis force, thereby reducing deformation of cantilever structure and improving drilling precision. The six-DOF cantilever machining device and a fitting hole machining method provided herein provide integral machining for fitting holes in a deep cavity of semi-enclosed structure by single tool adjusting on a single station,and coaxiality and dimensional precision can be ensured for fitting holes of different diameters in a multi-wall plate.

The invention provides a special positioning fixture for assembling a sapphire crystalbar, which comprises a grip, a screw rod, a positioning apex, a bracket, a platform, an axial positioning base and a crystalbar excircle radial positioning angle plate, wherein the crystalbar excircle radial positioning angle plate implements positioning connection by inserting two positioning pins into two positioning holes in the axial positioning base. The invention has the characteristic of high crystalbar assembling coaxiality and the like, can reduce the required reserved machining allowance to ensure the machining accuracy, and can obviously enhance the subsequent machining efficiency.

The invention relates to a spin-forming device for a powder liner. The device comprises an upper module and a lower module, wherein the upper module comprises an upper template and a male die; the lower module comprises a lower template and a female die; the male die is arranged on the upper template through a floating device; the female die is arranged on the lower template through a low-spin friction device. According to the device, floating male die and adjustable air cushion structures are adopted, so that an original powder charging state can be changed, and powder can be uniformly distributed according to die cavities of the dies; a ball bushing and an elastic support device are adopted for the female die, so that the spinning resistance of the female die is greatly reduced, higher dynamic positioning accuracy and spinning stability are ensured, the flowability of metal powder can be improved, and the uniformity of circumferential density of the liner can be improved; in addition, the working accuracy of the dies is ensured, and requirements on key technical indexes of the liner are met.