373results about How to "Reduce the number of trials" patented technology

The invention provides an electric bus integrated control hardware in-loop test platform and a test method. The electric bus integrated control hardware in-loop test platform is formed by an air source component, a line control air brake system, a conventional brake component, a driving control component, a signal simulation component, a target machine, and a host computer based on line control air brake, and the electric bus integrated control hardware in-loop test method comprises an acceleration test, a brake test and a steering test. According to the test platform and the test method, accurate adjustment of the brake pressure of four wheels is realized through front and rear axle proportion relay valves and four ABS solenoid valves in a line control air brake system, and integrated control of electric buses is realized with the combination of signal simulation components including a two-degree-of-freedom rotation platform and a wheel speed simulation motor and the corresponding test method.

The invention relates to a method for predicting a fluid-solid coupled characteristic value of an elastic hydrofoil and belongs to the technical field of turbomachinery simulation. The method comprises the steps of establishing a two-dimensional drainage basin-hydrofoil geometric model, dividing the gridding of a two-dimensional drainage basin, establishing a computational fluid mechanical model, calculating an initial steady flow field value and an unsteady flow field fluid-solid coupled value, and then performing after-processing on the calculation results to obtain the dynamic change process of the deformation of the flow field structure and the hydrofoil with time. The method for predicting the fluid-solid coupled characteristic value of the elastic hydrofoil has the advantages that the influence of an added mass effect on flowing is taken into account so that the stability of value calculation and the reliability of a numerical prediction result are improved, quick high-accuracy numerical prediction on an oscillation phenomenon induced by flowing around the elastic hydrofoil can be realized, and the flexibility of selection of numerical computation methods can be enhanced by virtue of secondary development of computational fluid mechanical software in combination with an embedded fluid-solid coupled algorithm.

The invention discloses an optimization method for a plastic injection molding technological parameter and belongs to technological parameter optimization methods, solving the problems that an existing optimization method for the plastic injection molding technological parameter is large in actual deviation, difficult to adjust accurately and tedious in a technological parameter setting process. The optimization method comprises an initial optimization step and a secondary optimization step, wherein primary and secondary factors of the technological parameter and optimal levels of the factors can be rapidly established in the initial optimization step, the obtained technological parameter serves as the initial technological parameter of the secondary optimization step, and thus testing times on an injection molding machine are greatly reduced; the secondary optimization step adopts a learning algorithm to perform online optimization, so that an optimizing iteration process can be sped up, the convergence of the iteration process can be ensured, and the optimal injection molding technological parameter can be obtained through several times of testing.

The invention relates to a turbine disk probability failure physical life predicting method based on Bayes information update, which comprises the following steps that 1, failure physical information of a turbine disk is determined in a reliability analyzing method based on physics of failure according to the structural characteristics of the aircraft engine turbine disk; 2, the failure physical information of the aircraft engine turbine disk obtained in step 1 and the existing failure information obtained by maintenance data statistics are analyzed in an FTA (failure tree analysis) /FMECA (failure mode, effects & criticality analysis) method to obtain the main failure mode and the failure position of the turbine disk, and uncertain factors and inaccurate data of the turbine disk facing whole life cycle are collected and cleared up; and 3, a failure physical life predicting model of the aircraft engine turbine disk is established according to the main failure mode and the failure position of the turbine disk obtained in step 2. The method disclosed by the invention has the beneficial effects that the design cycle of the aircraft engine turbine disk can be obviously shortened, the development cost is reduced, and the life reliability of the aircraft engine turbine disk can be obviously improved.

A bending-forging machine for manufacturing the large crankshaft or bellcrank used by ship is composed of upper die with lower arc end, bending lower die, upper and lower flat stocks, and insertion plate with lower arc end. Its forging method includes such steps as upsetting a steel ingot to become a flat square billet, drawing it to become a blank with shoulder, pressing V-shaped die on the middle of blank to form symmetric two V-shaped slots, bending by upper and lower dies, removing the upper and lower dies, inserting the insertion plate for finishing, trimming, and removing insertion plate.

The invention belongs to the field of forging, and particularly relates to a process and a device for forming a straight-edge conical cylinder forged piece of a nuclear power evaporator, which are applicable to the nuclear power and the process design and manufacturing process for the straight-edge conical cylinder forged piece of a hydrogenation reactor. The forming process comprises the following steps: (1) primary forming of a blank; (2) forming of a conical cylinder structure and a thin-wall conical cylinder structure with equal wall thickness; and (3) forming of the straight-edge conical cylinder forged piece of the nuclear power evaporator. The forming device is provided with a trestle, a saddle and a correcting twist block, wherein the saddle is placed on the trestle; the saddle is matched with an upper flat anvil outside the forged piece blank; and the correcting twist block is matched with the saddle. The operation of the process is simple and convenient, the structure of the device is simple, and the problem that the straight-edge conical cylinder forged piece is difficult to form and the like is solved. The straight-edge conical cylinder forged piece forged by the process has even processing allowance, and the size of each part can meet the requirement of components.

The invention discloses a tactical missile weapon system precision simulation and verification method, which comprises the steps of building a flight simulation mathematic model of a missile; developing missile full trajectory simulation software, selecting a corresponding algorithm meeting the precision to convert the mathematic model into a computer program, and performing flight simulation under the theoretical condition; verifying the model; analyzing various interference factors influencing the hitting precision of the missile, and building mathematic models for the interferences; according to the influence mechanism of various interferences on the flight of the missile, adding the interference factors to the flight simulation mathematic model to be subjected to simulation calculation to obtain corresponding results; performing simulation by adopting a Monte Carlo trajectory based on a uniform design method, and performing statistic analysis on the simulation results by arranging a simulation experiment table to screen out the factors having obvious influence on the precision of the missile. Through the technical scheme of the invention, the simulation amount can be effectively reduced.

The invention relates to the technical field of a concrete mixing ratio design, in particular to a concrete mixing ratio design method based on artificial intelligence, which comprises the following steps of : (1) adopting an artificial neural network method to establish a relation between concrete performance index and concrete mixing ratio so as to obtain a concrete performance prediction artificial neural network model; (2) based on the concrete performance prediction artificial neural network model, adopting genetic algorithm, aiming at meeting all performance requirements and leading the cost to be lowest, designing and optimizing to the concrete mixing ratio; and (3) retraining the concrete performance prediction artificial neural network model if the concrete mixing ratio obtained by optimization is not in the learned range of the artificial neural network. The concrete mixing ratio design method based on artificial intelligence is beneficial to quickly and accurately designing a concrete mixing ratio which can meet a plurality of performance requirements and has lower cost.

Provided is a testing device for directly measuring jet-flow thrust. The device includes a central ventilation support rod, a ripple tube, a casing, small jet nozzles, a thrust vector scale/sensor, a fairing cone, an outer tube, a fairing plate, a transition section and an exhaust nozzle; the front end of the central ventilation support rod is fixedly connected with an external ventilation support device, ventilation holes are uniformly formed in the central ventilation support rod in the circumferential direction, the back end of the central ventilation support rod is connected with a fixed end of the thrust vector scale/sensor, the exterior of the central ventilation support rod is sequentially sleeved with the ripple tube and the casing, ventilation holes are uniformly formed in the ripple tube and the casing in the circumferential direction, the positions of the ventilation holes in the ripple tube and the casing accord with the positions of the ventilation holes in the central ventilation support rod, the ventilation holes at the same positions are communicated through the small jet nozzles, the front end of the ripple tube and the front the of the casing are fixedly connected with the outer tube, the back end of the ripple tube is connected with a floating end of the thrust vector scale/sensor and fixedly connected with the back end of the casing, the fairing cone is connected to the back end of the ripple tube in a sleeved mode, the outer tube and the exhaust nozzle are connected through the transition section, and the fairing plate is installed between the outer tube and the transition section and located in front of a contraction section of the exhaust nozzle.

The invention provides a method for obtaining a high-efficiency low-noise impeller of a centrifugal pump volute. Firstly main structure sizes: impeller inlet diameter, impeller outer diameter, blade number, blade thickness, blade inlet placing angle, outlet placing angle, blade wrap angle and blade length of a centrifugal pump impeller are obtained through a traditional method. The method includes: 1) measuring centrifugal pump constant performance of the impeller with the structure sizes; 2) predicting centrifugal pump unsteady performance; 3) performing internal flow field analysis and structural improvement on a centrifugal pump; 4) evaluating performance of the improved centrifugal pump, and testing H-Q, N-Q and h-Q performance curves, particle swarm optimization (pos) and program specification block (psb) variation curves; and 5) providing a novel improvement project according to analysis, and evaluating the performance of the centrifugal pump until an ideal centrifugal pump is obtained.

The invention discloses a centrifugal pump flow induction noise numerical prediction method which is used for computing the sound source feature of flow noise on the basis of the test results of a centrifugal pump performance test. The method can well overcome the shortcomings that in a traditional computing method, the influence from a pump body structure on acoustic propagation is not considered, and eddy broadband noise is ignored. Centrifugal pump inner flow analysis and far-field noise value computing results are used in centrifugal pump low-noise waterpower design, test frequency can be reduced, the development cycle can be shortened, development cost can be saved, the design quality of a centrifugal pump can be effectively improved, an interpolation method is used between a fluid mesh and an acoustics mesh, sound source information of flow field calculation can be reserved to the maximum degree, GREEN analysis is used, the contribution degree on noise from different parts of a shell body can be obtained, such study is carried out, and early design or later modifying of the shell body can be optimized.

The invention provides a double-column rotary corrosive-wear testing machine, comprising a testing stand, which is provided with two columns, wherein a crossbeam is arranged on the columns and a through hole is formed in the center of the crossbeam; a crossbeam elevating and driving mechanism, which is arranged on the test stand and connected with the crossbeam; a testing drum, which is arranged on the center of the test stand, wherein an annular temperature control/cooling pipeline is arranged in the lower part of the testing drum; a transmission shaft, which passes through and is arranged in the through hole in the crossbeam; a sample clamping disc, which is fixed at the lower end of the transmission shaft, wherein the upper end surface of the sample clamping disc is provided with an annular groove, and the outer sides of the annular groove are provided with installation through holes; working electrodes, i.e., to-be-tested samples, which are inserted into the installation through holes; an auxiliary electrode, i.e., an annular platinum wire, which is arranged in the annular groove of the sample clamping disc; reference electrodes, which are uniformly distributed on the sample clamping disc at positions corresponding to the working electrodes; and a dynamic connection pool, which comprises annular dovetail cups, wherein the annular dovetail cups sleeve the upper part of the transmission shaft, leading-out circular rings are arranged at the bottom of the inner sides of the annular dovetail cups, the outer sides of the leading-out circular rings are provided with wiring copper columns penetrating the bottoms of the cups, the interior of each annular dovetail cup is provided with an electric needle, the lower ends of the electric needles are certain distance away from the leading-out circular rings, and the working electrodes, the auxiliary electrode and the reference electrodes are connected with the dynamic connection pool through leads.

The invention discloses an injection molding defect online correcting method and an injection molding machine. The method comprises the following steps: (1) determining optimization parameters and number; (2) setting background data according to injection molding technological parameters required to be optimized and defect types; (3) testing a mold and feeding back the quality; (4) carrying out normalization processing on the test mold technological parameters; (5) solving the optimal problem; (6) calculating the optimal hyperplane of the technology; (7) calculating the corrected technological parameters; (8) carrying out inverse normalization on the technological parameters, acquiring the actual test mold technological parameters, and testing the mold. The invention also provides the injection molding machine based on the online correction injection molding defect method. According to the invention, the sample data are subjected to pretreatment, and rules are introduced into the test mold data in the form of background data; the problem of organization and expression difficulty of rules of an expert system and reasoning based on rules, as well as the problems of high requirements for samples and collection difficulty for artificial neural network and living example reasoning can be overcome.

The invention discloses a multi-target optimization design method for a machine tool cross beam on the basis of orthogonal test analysis. According to the method, designing is conducted from the three aspects including the cross beam rib plate structure, the rib plate thickness and the inclined angle formed when a guide rail arranged on the cross beam supports a rib plate. The method comprises the following steps that three-dimensional modeling is conducted on an original cross beam, and the static and dynamic characteristics of the original cross beam are analyzed to determine cross beam optimization factors and evaluation indexes; the cross beam rib plate structure, the rib plate thickness and the inclined angle formed when the guide rail arranged on the cross beam supports the rib plate are selected as test factors, the levels of all the factors are determined, a simulation test is conducted on a combination of all the factors by selecting an orthogonal test table, and analytical processing is conducted on simulation data through a comprehensive balance analysis method to obtain an optimal parameter combination; the rationality of the optimization design parameter combination is determined by comparing all the properties of the cross beam before optimization with all the properties of the cross beam after optimization. According to the optimization design method, the optimization test parameter combination is obtained through small test time number, and the method is reasonable, feasible and easy to operate and has the typicality and symmetrical comparability.

The invention belongs to the field of forging, particularly relates to a high-speed train brake disc hub forging die and a design method thereof, and is applicable to design processes of high-speed train brake disc hub dies and preformed blanks. A near-net-shape preformed blank, a preforging upper die, a preforging lower die, a finish-forging upper die and a punch are designed by combination of an analytic method and a finite element modeling method, and cooperating use methods of the different dies are also provided. By the aid of the dies and the preformed blank which are designed by the method, brake disc hub forged parts meeting standards of rolling stock research institution of China academy of railway sciences can be produced. Since the dies designed by the method are used for forging the preformed blanks, the produced brake disc hubs are high in forming quality and have symmetrical appearance, uniform streamline and uniform machining allowance. In addition, as the dies designed by the method are used for manufacturing the high-speed train brake disc hubs, raw materials can be saved, production cycle can be shortened, machining allowance is lowered, and dimensional precision is increased.

The invention discloses a bloom continuous casting soft-reduction process used in steel production, and in particular relates to a method for controlling a bloom continuous casting dynamic soft-reduction pressure interval. The pressure interval is determined according to the central solid-phase rate of each casting blank section in the direction of blank drawing; the central solid-phase rate of each casting blank section relative to the upper limit of the pressure interval is less than or equal to the fs, namely Maxopt which is the maximum value of iopt, of each solute element, wherein the fs and iopt are the central solid-phase rates of a casting blank section relative to the minimum Ki of the solute elements; the Ki is the average solute aliquation index of the solute element i in two phase regions when each casting blank section is slightly pressed; furthermore, the central solid-phase rate of each casting blank section relative to the lower limit of the pressure interval is more than or equal to the fs, namely Minopt which is the minimum value of iopt, of each solute element. The pressure interval determined by the method can effectively improve central aliquation and also reduce cavity, looseness and crack; and the pressure interval has stable use effect and is suitable for bloom continuous casting production.

A method for determining actual heat consumption of a steam extraction heat supply machine resolves the problems of working amount increase in the operation process and low heat consumption accuracy caused by the process that compensation experiments or manual estimations are required to obtain actual heat consumption when actual heat consumption cannot be obtained due to the fact that actual steam extraction quantity is not specific steam extraction quantity in operation of a power plant. The method includes 1 conducting matching on relation between the heat consumption, turbine power and heat supply steam extraction amount; 2 selecting heat supply steam extraction amount; 3 changing the turbine power four times under each steam extraction amount; 4 obtaining heat consumption of each working condition point; 5, determining order of matching polynomial of the working condition points with the same steam extraction amount and conducting matching; 6 converting a coordinate system and conducting matching on the working condition points with the same power; and 7 obtaining heat consumption curve of any heat supply steam extraction amount according to the order of the matching polynomial. The method effectively reduces working amount, improves heat consumption accuracy and is suitable for a steam extraction heat supply machine set.

The invention relates to a hollow structure forming method. The hollow structure forming method comprises the steps that a welding stop agent is coated between two or more core boards, the core boardsare laminated, heating is performed to reach diffusing connection temperature, and diffusing connection is completed through pressurizing; laminated face boards are placed on two sides of a core board assembly formed after diffusing connection, the peripheries of laminated blank assemblies are soldered and sealed, and an inner layer air channel and an outer layer air channel are reserved; the laminated blank assemblies are put in a super-plastic forming mold, heating is performed to reach the predetermined temperature lower than the diffusing connection temperature, and air introduction for pressurizing is performed through the outer layer air channel, so that the outer-layer face boards are stressed to outward extend and deform and complete super-plastic forming; after super-plastic forming of the face boards, air is discharged for pressure relief through the outer layer air channel, and then air introduction for pressurizing is performed through the outer layer air channel, so thatthe core boards are stressed to outward extend and deform and complete super-plastic forming; after super-plastic forming of the core boards, heating is performed to reach the diffusing connection temperature, heat preservation and pressure maintaining are performed, so that diffusing connection between the outer-layer face boards and the core boards is achieved.

The invention discloses last jump positioning router, multicast route tracking method and the router. The positioning method includes the following steps: receiving inquiry message to judge whether the router is in the network section belongs to received address, and not transmit multi cast data flow; if the network section have movable multi cast member, amending the inquiry message and transmitting to the network second. The router includes receiving module, judging module, and positioning module. The tracking method includes the following steps: positioning the last jump router; transmitting request message to the upper jump; transmitting response message after receiving the first jump router. The invention can exactly locate the last jump router in multi cast router tracking, and increase the success ratio for its positioning and multicast router tracking.

The invention relates to a transport aircraft inlet splash testing method for transport aircraft splash testing. According to the method, before a splash test, configuration of a test aircraft for test flight, various running statues of an engine and test aircraft glide speed point required by testing are determined according to the type of the test aircraft; materials and position of a test pool in a runway, coloring position of an aircraft body and selection of coloring materials, a video-recording method, test aircraft glide modes meeting the testing requirements and the like are determined; tests are performed one by one according to the test aircraft glide speed required by testing. The method has the advantages that splash testing is performed according to the airworthiness regulation for test aircraft, by studying, the configuration state of the test aircraft during splash testing, a building method of the test pool, coloring of the test aircraft for judging test results, a test video-recording technique, acquisition of test key data, final identification modes of data and the like are determined, and a standard set of methods and programs for transport aircraft splash testing is formed.

Provided in the invention is a quantitative squeaking evaluation method based on an orthogonal-paired comparison test and SVR. A testing sample for a training model is obtained by combining an orthogonal test and a paired comparison test; subjective evaluation of an actually measured audio sample is performed; quantification of the squeaking abnormal sound contribution degrees by different pure tones is performed; and a multi-pure-tone squeaking quantitative evaluation model is constructed by combining an exclusion-contrast thought and a grade scoring method and support vector regression and validity detection is performed. The orthogonal test has characteristics of balancing dispersion, evenness and comparability; and the test number can be reduced substantially. The paired test has characteristics of being easy to operate and being performed simply and fast; the requirement on professional knowledge is low; and the target features can be reflected better. Therefore, the quantitative evaluation of the contribution of the prominent squeaking frequency to the total noise can be realized.

The invention relates to a design method of a middle blank and a prefabricating blank during a nuclear power and hydrogenation reaction chamber conical shell forgeable piece forming process, which belongs to the filed of forging and is suitable for the production engineering and a manufacturing process of nuclear power and hydrogenation reaction chamber conical shell forgeable piece forming. The invention adopts a method of combining an analysis method and finite element modeling to develop a dimension relational expression of the prefabricating blank, the middle blank and a final forgeable piece during the nuclear power and hydrogenation reaction chamber conical shell forgeable piece forming process and provides the design method of the middle blank and the prefabricating blank. The design method and a design formula of the middle blank and the prefabricating blank during the nuclear power and hydrogenation reaction chamber conical shell forgeable piece forming process are suitable for producing significant parts, such as megawatt nuclear power conical shells, large-sized hydrogenation reaction chamber conical shells, and the like; when the middle blank and the prefabricating blank designed by the design method are adopted to produce conical shell forgeable pieces, the middle blank and the prefabricating blank designed by the design method can nicely control the conicity of the conical shell forgeable pieces, thereby solving the problem of the difficult forming and the unreliable machining dimension precision of traditional conical shell forgeable pieces.