62results about How to "Reduce manufacturing risk" patented technology

The invention provides a process design method and system based on a system packaging technology, a medium and an apparatus. The process design method based on the system packaging technology comprises the following steps of acquiring the design data of a layout and the three-dimensional model data associated with the layout; associating and matching the design data and the three-dimensional modeldata according to the design element attribute information in the design data, and assembling the design data and the three-dimensional model data into an integral packaging model; performing assembly process analysis on the integral packaging model to analyze unreasonable design points used as design modification and reference; or directly exporting a packaging process manufacturing procedure for production and manufacturing from the integral packaging model. According to the method, more repeated work can be removed, the manual work is replaced with automation, and compared with an originalmethod, the method saves 60%-80% of the time, and meanwhile, the working difficulty is reduced, and the process from design to simulation and production manufacturing is simplified, so that the competitiveness of an electronic product is greatly improved.

The invention discloses a method for checking the intensity of a wind power locking disk, belonging to the field of design of wind power generating equipment. The method comprises the following checking steps of: (1) computing the positive pressure of each conical contact surface between an outer sleeve and an inner ring; (2) computing the pressure intensity and interference magnitude of each conical contact surface between the outer sleeve and the inner ring after a bolt is screwed and ensuring the maximum pressure intensity and interference magnitude on the premise of ensuring that each component is not deformed plastically; (3) computing the pressure intensity and interference magnitude of a contact surface between the inner ring and a shaft sleeve after a bolt is screwed and ensuring the maximum pressure intensity and interference magnitude on the premise of ensuring that each component is not deformed plastically; (4) computing the pressure intensity and interference magnitude ofa contact surface between a shaft sleeve and a main shaft after a bolt is screwed and ensuring the maximum pressure intensity and interference magnitude on the premise of ensuring that each componentis not deformed plastically; and (5) computing the maximum torque which can be transferred by the contact surface between the main shaft and the shaft sleeve. According to the method, plastic deformation of each component material and the capabilities of the shaft sleeve and the main shaft for transferring a rated torque after the wind power locking disk is locked can be verified, the rationalityof the design size of the locking disk can be verified effectively, the manufacturing risk is lowered, and the product yield is increased.

The invention discloses a visual detection device for a press fitting sheet of an engine cylinder locking plate. The visual detection device for the press fitting sheet of the engine cylinder locking plate comprises a movable working platform, a detection head component and a controlling detecting system, wherein the movable working platform is used for containing installation components of engine valves to be detected, the platform can move horizontally on an X-axis and a Y-axis, the detection head component comprises a high-precision charge coupled device (CCD) and a prime lens, and the controlling detecting system comprises an X-axis, Y-axis and Z-axis movement control system and an identification system. The visual detection device for the press fitting sheet of the engine cylinder locking plate detects problems that a locking plate leaks pressure and press fitting is not in place after an automatic press fitting device of a cylinder cover split-assembling line locking plate is used, can avoid negligence and omissions caused by human factors, improves identification capability of press fitting defects, and reduces manufacturing risks. Meanwhile detection with equipment can quantify detection standards, solidify detection means, and guarantee stability and reliability of quality of products.

The invention belongs to the technical field of preparation of an aero-engine fixation guider, relates to an aero-engine ceramic matrix composite fixation guider blade structure and a molding method thereof, and is to overcome the structural defects that an existing CMC guider blade prefabricated body is unreasonable in design and poor in blade root strength. A turbine guider blade manufactured in an integrated assembly mode comprises multiple stages of guide blades, parts are integrally assembled in a riveting mode, and an assembly structure adopts a SiC ceramic matrix to achieve welding; aneffective space between an upper edge plate and an outer casing is fully utilized, the blade body and the upper edge plate are installed and positioned through limiting rivets and a limiting table, the SiC ceramic matrix is deposited on the whole product through the CVI technology, and integrated preparation is completed; by means of the structure, the complex SiC / SiC multi-connected high-pressure guide blade has good manufacturability, the edge plate and the blade are easier to manufacture and more reliable to install, and the dimensional precision of a final product is easier to guarantee;and the structure can be fully applied to medium-sized and large-sized engines and five-generation engines.

Present invention relates to computer fittings technology field, in particular referring to inner thermal pipe of computer radiator. Said thermal pipe has a hollow copper tube with sintered copper ball powder layer, which contains different kinds of easy hydroscopic inorganic salt ball and has different adding proportion in different section of copper tube. Said copper tube has obstruct layer in inner wall without generating sintering reaction with copper at lower 800 degree centigrade, which makes copper ball powder layer not sintering with copper tube. Due to copper tube inner wall having obstruct layer, copper ball powder layer can form a thin layer gap which forms the water duct to increase water storage, to make water flow unhindered, and reducing knee bend or stress for avoiding fracture.

The invention discloses an early warning method for equipment manufacturing quality problems, which comprises the following steps: inspecting supervision outline or detailed rules in the manufacturingprocess of structured equipment; Establishing the database of inspection supervision outline or detailed rules on the cloud server, and establishing the template of basic inspection supervision outline or detailed rules for users to use; Establishing the problem summary database, wherein when the equipment has the record containing the quality problem, the system extracts the information of the quality problem; When the user inspects the supervision outline or detailed rules of the template supervision outline or detailed rules according to the equipment, Based on the name of the verified device, Category, the cloud platform pushes historical quality issues as alert information, and the user further perfects the inspection requirements according to the warning information.The invention provides a cloud database for effectively recording quality problems based on the cloud platform. The quality problems originate from the daily inspection work of all users. The invention has extremelyhigh reliability, effectively reduces the manufacturing risk and saves the cost..

The invention discloses a preparation method and application of a fluorocalciferol CD ring, and relates to the field of synthesis of medical intermediates. The invention discloses a preparation method of a compound VII with the following structure, and further the compound VII is used for preparing fluorocalciferol. According to the method, a convergence method is used for synthesis, so that the synthesis period is shortened, and the preparation cost is reduced; wherein the reaction yield is high, and the product quality is easy to control; in addition, the use of dangerous reagents is avoided, the preparation risk is reduced, and large-scale preparation is easy to realize.

The present invention relates to damping arrangements for gas turbine combustors. It comprises: a wall having a first inner wall and a second outer wall arranged at a distance from each other; a plurality of cooling channels extending substantially parallel between the first inner wall and the second outer wall; and at least one damping space composed of The cooling channel delimits, further comprising a first passage for supplying cooling medium from the cooling channel into the damping space and a second passage for connecting the damping space to the combustion chamber, characterized in that the end plate fixed to the inner wall will The damping space is separated from the combustion chamber, said end plate is provided with a neck passage and additionally at least one supply plenum for a cooling medium, at least one outlet plenum for a cooling medium and at least one cooling passage, said At least one cooling passage enables a cooling medium to flow from at least one supply plenum to another supply plenum or to at least one outlet plenum.

The invention discloses a method for making double eyelids, which solves the problem of complex double eyelid production procedures in the prior art, high production costs, long production time, large damage to the eyelids, resulting in unpredictable recovery period, and difficult adjustment after production, resulting in final production failure. high rate problem. The main steps of the present invention are: cleaning and disinfecting the four-layer eyelids and tools; then drawing lines on the four-layer eyelids to design the shape of the double eyelids, and marking six embedding points sequentially along the positions of the double eyelids; and then Use a polypropylene monofilament thread with barbs to pass through six embedding points in the same direction in order to fit the first eyelid and the fourth eyelid; finally use scissors to cut the excess polypropylene monofilament thread left on the eyelid Just cut it off and clean the tool. The invention has the advantages of simple production procedure, quick effect, short production time, low production risk, almost no damage to eyelids, no swelling and pain, very short recovery time or no recovery period, and low double eyelid production failure rate.

The invention relates to a fixing guider blade structure and molding thereof, in particular to a ceramic matrix composite material fixing guider blade structure of an aircraft engine and molding thereof, and belongs to the technical field of preparation of fixing guiders of aircraft engines. According to the fixing guider blade structure and the molding thereof, the structural defects of unreasonable design and poor root strength of an existing CMC guider blade prefabricated body are overcome, a turbine guider blade is prepared by adopting an integrated assembly mode, parts are integrally assembled by adopting a riveting mode, the assembly structure adopts a SiC ceramic matrix to realize welding, and then the defect of insufficient root strength caused by conventional sewing the molded prefabricated body is avoided; and multi-part backup and assembly optimization can be realized, the risk of whole component scrapping caused by single part scrapping can be avoided, the preparation riskis reduced, the cost is reduced, and the component quality is improved.

The invention provides a testing method for electric quantity display in a battery column in a portable electronic device. The method comprises the following steps of: S1: supplying power to the portable electronic device through an external power supply which is initially set to be first standard voltage; S2: opening the portable electronic device and enabling the portable electronic device to be in a standby interface state; S3: starting from the first standard voltage, gradually regulating the voltage of the external power supply, and obtaining the actual corresponding relation between the current voltage value and the corresponding current electric quantity display level in the battery column in the portable electronic device; and S4: judging whether the electric quantity display in the battery column in the portable electronic device is qualified or not according to the corresponding relation between the preset reference voltage value of each level and the standard electric quantity display level in the battery column. According to the testing method disclosed by the invention, whether the electric quantity of the battery is correctly displayed on the portable electronic device can be quickly judged, so that the risk during the project manufacturing process is reduced, the quality of software and hardware of the portable electronic device is ensured, and the operation is simple and convenient.

The invention relates to a fixed guide vane structure and molding, in particular to an aero-engine ceramic matrix composite fixed guide vane structure and its molding, and belongs to the technical field of aero-engine fixed guide preparation. The turbine guide vane is prepared by an integrated assembly method, the parts are integrated by riveting, and the assembly structure adopts a SiC ceramic matrix to realize "welding", so as to avoid the defect of insufficient strength of the blade root caused by the conventional sewing-molded prefab; After the protrusions on the edge plate and the second lower edge plate are directly riveted with the blades, they are then riveted with the third lower edge plate and the fourth lower edge plate by riveting rivets, and the SiC ceramic matrix is ​​deposited on the entire product by the CVI process. Complete the integration preparation. The SiC / SiC high-pressure guide vane has good manufacturability, the preparation of the edge plate and the vane is simpler, and the installation is more reliable. This structure can be fully applied to small engines, such as civil turboshaft engines and turbojet engines.

Embodiments of the invention provide a preparation method of a metamaterial. The method comprises the following steps: adding a liquid-state high-molecular material in a mold and heating and curing to a viscous flow state so as to obtain a first flaky sheet material; aligning and pasting a first PCB possessing a metal microstructure array on the first flaky sheet material; further adding the liquid-state high-molecular material in the mold and heating and curing to the viscous flow state, and forming a second flaky sheet material on the first PCB; aligning and pasting a second PCB possessing the metal microstructure array on the second flaky sheet material. The embodiments of the invention also provide the metamaterial prepared by using the above preparation method. By using the method of the invention, malposition of the metal microstructure array on the PCB can be modified. Therefore, a preparation risk can be reduced and metamaterial quality can be guaranteed.

Wide angle fovea lens and a camera design using the lens are described. The lens has three lens groups and includes a single aspherical lens element. The lenses have higher magnification on the optical axis than at angles off the optical axis.