83 results about "Configuration design" patented technology

The invention discloses a simulation part design method based on stress gradient fitting and a blade root characteristic simulation part. The simulation part design method comprises the following steps that S1, a dangerous area of a blade root part is determined based on simulation analysis of a turbine blade under a real working condition, and characteristic parameters are extracted; s2, designing a simulation piece examination section configuration based on a low-cycle fatigue simulation piece design criterion and the extracted characteristic parameters; s3, extracting the maximum stress gradient of the maximum first principal stress point of the blade root part of the turbine blade in a preset range in a preset direction, and carrying out normalization processing to obtain a stress gradient range of the blade root part of the real blade; s4, extracting the stress gradient of the simulation piece examination section, performing same normalization processing, comparing stress gradient fitting conditions, and performing fitting on the stress gradient by modifying and adjusting non-characteristic parameters of the simulation piece examination section and simulation piece configuration to control a stress gradient error; s5, a clamping section and a transition section are designed, and the strength of the clamping section and the strength of the transition section meet the requirement; and S6, the overall configuration design of the blade root feature simulation part is completed.

The invention discloses a deep-sea mining VTS configuration optimization design method based on data driving, and belongs to the technical field of deep-sea mining engineering and optimizing.The method comprises the steps that firstly, a mechanical response model of a VTS is constructed through a VFIFE method, and mechanical response is calculated in combination with VTS structure parameters and borne external force; then generating a prediction agent model based on CPO-BP, and realizing relation modeling between the configuration design variable and the mechanical response of the VTS; and finally, the prediction agent model is embedded into the MODA-DE, the VTS configuration is optimized based on the MODA-DE, and VTS configuration design variables meeting the multi-objective optimization requirements are finally obtained through multi-generation iteration. According to the scheme, the three links of VFIFE, CPO-BP and MODA-DE are closely combined, an efficient multi-target optimization technology is formed, collaborative improvement from high-precision prediction to global optimization is achieved in mining pipeline configuration design, and the method has high actual popularization and application value.

1. The name of the design product: asset allocation graphical user interface for electronic device and its main body. 2. The use of the design product: an electronic device. 3. The design points of the design product: the part in the graphical user interface, the part outside the dotted line is the claimed part. 4. The picture or photo that best shows the design points: design 1 front view. 5. Design 1 is designated as the basic design. 6. The use of the graphical user interface: the overall interface is used to adjust asset allocation for financial planning; the use of the claimed part of the interface is the same as that of the overall interface. 7. The human-computer interaction mode of the graphical user interface: in design 1 front view, the user can search for content in the search bar, click the "save for 30 days" or "save for 90 days" option control to switch the deposit period, slide the joystick control on the slide rail left and right to adjust the deposit amount and view the corresponding estimated interest, and click the "transfer to "save and take out"" control to complete asset allocation. In design 2 front view, the user can search for content in the search bar, click the "save and take out" or "save for 30 days" option control to switch the deposit period, slide the joystick control on the slide rail left and right to adjust the deposit amount and view the corresponding estimated interest, and click the "transfer to "90 days"" control to complete asset allocation. The human-computer interaction mode of design 3 is the same as that of design 1. In design 4 front view, when the user clicks the "save for 90 days" option control to switch the deposit period, the cartoon figure's hand on the barbell and expression change (the shorter the deposit period, the lower the interest rate, and the more relaxed the cartoon figure's expression; the longer the period, the higher the interest rate, and the more difficult the cartoon figure's expression), presenting the interface change from design 4 front view to design 4 interface change state diagram. In design 5 front view, when the user long-presses the joystick control on the slide rail and slides it to the right, the deposit amount and the corresponding estimated interest are changed, presenting the interface change from design 5 front view to design 5 interface change state diagram. The human-computer interaction mode of design 6 is the same as that of design 1.

The invention relates to a large-bearing memory alloy driven unlocking separation nut mechanism, and belongs to the technical field of spaceflight structures. The memory alloy separation nut comprises a shell assembly, a split nut assembly, a bearing force transmission assembly, a memory alloy driving assembly and a nut separation assembly, a modular design concept is adopted, configuration design is carried out on the memory alloy separation nut according to three functional parts of driving, transmission and execution, the bearing efficiency and the unlocking reliability are improved in a targeted mode, and the memory alloy separation nut is suitable for being used for a large-scale industrial production. The unlocking impact is reduced, and the separation nut is more convenient to use.

A design generation and simulation workflow for generating design layouts and executing simulations of the design layouts to generate energy and comfort performance metrics that indicate the energy efficiency and occupant-comfort levels associated with the design layouts. As described herein, the design workflow includes five phases including 1) configuring a design generation application, 2) generating design layouts via the design generation application, 3) generating energy models for the design layouts, 4) configuring simulations on the energy models, and 5) executing the configured simulations on the energy models and generating comparative results based on the simulation results of multiple simulations.

The invention relates to the technical field of reactor design, and particularly discloses a micro-channel reactor design method and device based on multi-objective Bayesian optimization and a storage medium, and the method comprises the steps: executing parameter sampling operation, and generating an initial parameter combination; executing a physical field simulation operation aiming at the microchannel reactor based on the initial parameter combination, and generating initial simulation information which comprises a plurality of simulation indexes; performing multi-target scoring calculation on the initial simulation information, adjusting the simulation indexes based on a scoring calculation result, and generating adjusted simulation information; optimizing the adjusted simulation information based on a preset iterative optimization algorithm to generate optimized information; and performing configuration design on the micro-channel reactor based on the optimized information. The existing micro-channel reactor is simulated and analyzed from multiple aspects, so that the efficient and rapid micro-channel reactor design is realized.

The invention discloses an earth-moon translation point orbit spacecraft formation relative motion configuration design and control method, and belongs to the technical field of spacecraft orbit dynamics and control. The method comprises the following steps: firstly, constructing a double-layer dynamic model consisting of a circular restrictive three-body problem model and a high-precision ephemeris model, and defining an orbit amplitude difference and a phase difference as configuration parameters; then, according to different track amplitude difference and phase difference combinations, three types of natural relative motion configurations are set, a periodic track is rapidly generated under a circular restrictive three-body problem model, and multi-circle correction is conducted through a high-precision ephemeris model and two-stage multiple targeting; a hierarchical constraint model is established for a controlled task surrounding a fixed position, a plane and a space, and a control pulse is solved by adopting a two-stage optimization strategy. According to the method, efficient design and stable control of formation configuration in a complex dynamic environment are realized, and the method is suitable for various translation point orbit tasks.

The invention relates to the technical field of spacecraft docking and docking interfaces, and discloses a standard interface device for spacecraft docking and docking, which comprises a first docking assembly and a second docking assembly, the first docking assembly and the second docking assembly adopt identical configuration design, and through dynamic switching of active and passive working modes, when one is an active end to execute capturing and locking functions, the other is a passive end to execute capturing and locking functions; and vice versa, two-way exchange of active and passive performance is realized, flexible docking requirements of spacecrafts with different roles are met, and the interface universality is improved. The capturing and locking assembly at the waist of the first butt-joint assembly comprises symmetrical locking arms and can be opened and closed to achieve rigid locking, the two butt-joint assemblies are each provided with a T-shaped structure used for bearing and a butterfly-shaped structure, the design breaks through the function fixing limitation of a traditional connector, position deviation is corrected through the butterfly-shaped structures, loads are evenly transmitted through the inverted-T-shaped structures, and the locking effect is good. The design is simplified, and the universality, the adaptability and the connection reliability are improved at the same time.

The invention provides a configuration design method of a high-orbit flat plate type satellite. The configuration design method comprises the following steps: determining a layout type and an appearance envelope of a satellite configuration; defining configuration design parameters; performing layout planning according to the solar wing type; establishing a satellite size optimization model; verifying whether the sum of the satellite surface area and the expandable heat radiator area is greater than or equal to the heat dissipation area requirement; and iteratively solving optimal configuration parameters, and performing engineering rounding processing. Therefore, through a technical innovation method of parametric modeling solution, the configuration design is quantified, the coordination problem of the outboard high-storage-ratio equipment layout, the satellite heat dissipation requirement and the carrying launching space is solved, the satellite body volume ratio and the body space utilization rate are effectively improved, and a one-rocket multi-satellite low-cost launching mode is achieved.

The invention belongs to the technical field of water turbine runners, and particularly relates to a bucket root configuration design method based on a negative Gaussian curved surface. According to the technical scheme, the bucket root configuration design method based on the negative Gaussian curved surface comprises the following steps that S1, a hydraulic design model is obtained and preliminarily analyzed; s2, rounding the part outside the high-stress area of the root in the step S1; s3, constructing a negative Gaussian curved surface of an unprocessed part in the step S2; s4, completing the structure and performing simulation calculation; and S5, according to the calculation result of the step S4, adjusting the parameters in the steps S2 and S3 until the parameters meet the requirements. According to the bucket root configuration design method based on the negative Gaussian curved surface, the root stress is reduced by constructing the negative Gaussian curved surface, the method does not depend on experience of users any more, meanwhile, mutual influence of parameters in different steps is reduced as much as possible, and the number of attempts of the users is reduced.

This invention relates to a process architecture for optimizing ship hydrodynamic configurations based on artificial intelligence technology. The architecture includes modules such as expert experience, historical sample data of ship hydrodynamic configurations, design input for ship hydrodynamic configurations, a knowledge base for ship hydrodynamic configuration design and evaluation, a parametric model of ship hydrodynamic configurations, knowledge-driven reconstruction of the ship hydrodynamic model, AI-based optimization design of ship hydrodynamic configurations, rapid evaluation of ship hydrodynamic performance, and a comprehensive evaluation index model for ship hydrodynamic performance. This invention fully leverages the design experience contained in historical sample data, extracting the experience of numerous experts into design knowledge and integrating it into the ship hydrodynamic configuration optimization design process. The process architecture drives intelligent reconstruction of the ship hydrodynamic model through design knowledge, and improves upon the shortcomings of traditional ship hydrodynamic performance prediction methods, such as time consumption and low efficiency, by establishing a rapid prediction proxy model for hydrodynamic performance based on machine learning algorithms.

A precision control method for a spliced curved-surface fixed-surface antenna comprises three steps of configuration design, precision design and precision realization for the spliced curved-surface fixed-surface antenna, especially an incomplete cylindrical-surface antenna, and comprises the steps of initial configuration design, curved-surface precision reference establishment, precision transfer function determination, and fine tuning and adaptation determination. The precision design comprises precision index distribution and precision index simulation analysis, and can solve the problems that a large space deployable curved surface structure is difficult in launching state folding layout, large in multi-surface pressing error, difficult in deploying precision and rigidity maintenance, poor in overall thermal stability of an antenna and the like, and the contradiction between high-precision pointing and large errors of initial installation and butt joint.

The invention discloses a grain configuration reverse design method and device of a solid propellant, and relates to the technical field of charging design, the method comprises the following steps: determining a design variable and a variation range of the grain, and sampling the design variable to generate a plurality of sample points; performing inner trajectory calculation based on the sample points to obtain a time sequence data set; encoding the time sequence data set into a multi-channel image, and constructing a multi-channel image set; training a neural network model by taking the multi-channel image set as input and the design variable as output to obtain a grain configuration prediction model; and encoding the target time sequence data set into a target multi-channel image as the input of the grain configuration prediction model to obtain a corresponding grain configuration. The problems that an existing grain configuration design scheme is poor in applicability and low in efficiency are solved, then the grain configuration meeting the performance requirement can be rapidly generated, the research and development period of a solid rocket engine is shortened, and the research and development efficiency is improved. The application range is wider, and the mobility is higher.

The invention provides a product commissioning method and device, electronic equipment, a medium and a computer program product. The method and the device can be used in the technical field of automatic testing and finance. The product commissioning method comprises the steps of obtaining m demand items of a product version commissioned this time, technical parameter configurations designed in one-to-one correspondence with the m demand items, and a mapping relation between the demand items and the technical parameter configurations; the technical parameter configuration and the product version of the m demand items are tested through a pre-configured technical parameter management and control platform, a technical management and control report is obtained, and the technical parameter management and control platform is configured to be capable of testing the design quality and function of the technical parameter configuration; the commissioning process and the commissioning content of the product version can be tested; and when the technical management and control report is passed, commissioning the version of the product commissioned this time.

The application discloses a parameterizable configuration digital LDO automatic generation method and device, aiming at the problems of long cycle and high cost of repeated simulation verification and modification of a schematic layout in an existing digital LDO design method, based on a given digital LDO architecture, performing configuration design on changeable design parameters in the digital LDO circuit, corresponding the configurable performance parameters and the circuit design parameters, and only needing to input specified performance parameters to generate corresponding digital LDO net list files and layout files. The design time of the circuit is greatly reduced, and agile design is realized.

The invention discloses a diversified configuration system and method for a disk read-write test model, and relates to the technical field of computer storage, and the system comprises a configuration design module which is used for defining universal configuration items in an XML file, and reserving specific tool configuration items according to different configuration attributes among test tools; the configuration file analysis module is used for reading and analyzing the XML configuration file according to a standard XML analysis technology; the configuration items are extracted according to a universal or specific tool, classified and stored, an internal data structure is formed, and configuration data are obtained; the tool adaptation module is used for combining the general configuration item and the specific tool configuration item according to the analyzed configuration data and generating specific configuration for each test tool; and the test execution module is used for starting the corresponding test tool to run the disk read-write test model in the operating system according to the specific configuration. The same XML file configuration model is adopted, the configuration time and workload are reduced, and cross-tool and cross-system compatibility is enhanced.

To provide a device for automatically constructing a system operation mechanism, that monitors a system, and generates configuration information of the system so as to generate a required recovery procedure according to a monitoring result.SOLUTION: Means for designing a fault tolerance mechanism generates configuration information of a system satisfying given system requirements, so as to satisfy conditions of generating a recovery procedure of each constituent comprised in the system, and generates a recovery procedure of a constituent in which a fault has occurred, when failure has occurred in any of the constituents. Means for generating a state monitoring procedure generates a state monitoring procedure that is a collection of concrete confirmation tasks for confirming a state of individual constituents comprised in the system. Fault corresponding means monitors the system by using the state monitoring procedure.SELECTED DRAWING: Figure 19

The invention discloses an upper computer computing software custom FBD code generation method and device, the input, output, parameters and other information of an FBD are predefined based on a visual interface, virtual control generates a corresponding custom code according to a software architecture and a system interface, and a user only needs to automatically generate the FBD code at a reserved interface of the code at which the code is automatically generated. And adding corresponding FBD operation logic. After writing of FBD arithmetic logic codes is completed, a compiler interface is automatically called, and custom codes are compiled into a dynamic link library; according to the method, an upper computer computing software FBD programming environment is improved into an open system, so that a user can compile corresponding control logic according to actual application of an industrial site, the user-defined FBD is supported to be added to different task levels, the flexibility and openness of a configuration system are greatly improved, and the method is suitable for application and popularization. And richer configuration design interfaces are provided for configuration designers.

This invention relates to a configuration design method for a single-power-source heavy-duty multi-degree-of-freedom forming device, comprising the following steps: S1, deriving the design constraints of the single-power-source heavy-duty multi-degree-of-freedom forming device; S2, establishing the branch constraint screw system and motion screw system of the single-power-source heavy-duty multi-degree-of-freedom forming device; S3, synthesizing the motion branches that satisfy the design constraints and motion requirements of the single-power-source heavy-duty multi-degree-of-freedom forming device; S4, synthesizing all fully symmetrical configurations of the single-power-source heavy-duty multi-degree-of-freedom forming device; S5, establishing a global velocity Jacobian matrix, and optimizing variable structural parameters based on minimizing global motion errors; S6, finally obtaining the configuration and parameters of the single-power-source heavy-duty multi-degree-of-freedom forming device that satisfy a specific motion trajectory. This invention can realize the configuration synthesis and dimensional synthesis of the single-power-source heavy-duty multi-degree-of-freedom forming device, ensuring low control, low cost, and high speed of the device while achieving specific motion requirements.

Reduce the workload of designers. 【Solution means】The layout design automation system according to the embodiment is a layout design automation system that generates a route connecting a starting point and an ending point. The layout design automation system has a point cloud data processing unit and a route generation unit. The point cloud data processing unit identifies which range of the point cloud data is the range of each structure from the information indicating the building structure and indoor structures composed of the point cloud data, identifies the type of the structure, and generates 3D CAD information of the identified structure. The route generation unit generates a route based on the 3D CAD information generated by the point cloud data processing unit.

The invention relates to the technical field of additive manufacturing, in particular to an additive manufacturing method of a micron-sized runner and application of the additive manufacturing method. The additive manufacturing method for the micron-sized flow channel comprises the following steps that (a) a configuration body is split into a plurality of parallel solid cylinders based on preset distribution of the micron-sized flow channel in a target configuration, an stl model is obtained and sliced, and a slice file is obtained; (b) based on the slice file, metal powder is subjected to additive manufacturing forming through a selective laser melting process, and a target configuration with a micron-sized runner is obtained; in the step (a), the adjacent solid cylinders are tangent or intersected, and a pore defined by every four solid cylinders corresponds to a micron-sized runner. According to the additive manufacturing method, through proper micron-sized runner configuration design, under the condition that SLM equipment and technology are not changed, controllable preparation of the micron-sized runner can be achieved, and the forming precision of an extremely fine structure is remarkably improved.

The application provides a wellbore structure design method for developing a well, comprising the following steps: (1) establishing a probability database of block risk occurrence, wherein the probability database comprises a complex occurrence depth ratio, a complex occurrence probability and a complex treatment cycle; (2) establishing a design well complex risk database, wherein the risk database comprises a design well occurrence depth, a complex occurrence probability and a complex treatment cycle; and (3) establishing a wellbore structure design optimization method, wherein the product of an investment rate of a to-be-selected scheme, a total complex occurrence rate and a total complex treatment cycle is used as a method for judging a target scheme. In the application, the complex occurrence depth is more accurate, the scheme comparison is more comprehensive and accurate, a plurality of complex occurrence probabilities and complex treatment times of the same stratum are combined, one stratum position corresponds to one complex treatment time and one complex occurrence probability, and the calculation parameters are simplified.

The application provides a heavy gas turbine air-cooled turbine aerodynamic layout design method and system, electronic equipment and a storage medium. The method comprises the following steps: step 1: obtaining the design requirements of the heavy gas turbine air-cooled turbine, and determining the turbine stage number; step 2: determining the enthalpy drop and load distribution scheme of each turbine stage; step 3: performing preliminary evaluation on the stress of the blade and the disc, if the requirement is not met, adjusting the load coefficient and the flow coefficient, if the requirement is met, entering step 4; step 4: initial meridian flow passage design, evaluating the strength of the blade and the disc after the meridian flow passage design is completed, if the requirement is not met, repeating steps 2 to 4 to perform parameter optimization, if the requirement is met, entering step 5; step 5: determining the radial distribution law of the turbine stage reaction degree; step 6: determining the radial distribution law of the aerodynamic parameter according to the one-dimensional average parameter design result; step 7: S2 inverse problem calculation; and step 8: aerodynamic performance analysis and optimization. The scheme provided by the application shortens the turbine engineering design cycle.

The invention provides an aviation equipment connection configuration design method based on an FPS model, and the method comprises the following steps: building a certain aviation equipment connection configuration design model based on the FPS model; analyzing user requirements to obtain required function elements, substituting the required function elements into the configuration library, and outputting a configuration sketch; mapping to a performance layer to obtain a required performance element, output connector performance and a design analysis expression; mapping to a structure layer to obtain a substructure and parameter description thereof; establishing a concept structure model; establishing a connection configuration design process scheme; and substituting parameter requirements, and establishing a configuration mathematical model. The method has the beneficial effects that reference is provided for materialization and refinement of the aviation equipment connection configuration design method, the design period of the aviation assembly connection configuration is shortened, the design efficiency and quality are improved, and the method has important significance on development and progress of aviation equipment.

The invention relates to the technical field of numerical control machine tools, and discloses a machine tool configuration evaluation method and device, terminal equipment and a readable storage medium. The method comprises the steps that process planning data is generated based on machining task parameters, a motion subspace is constructed according to the process planning data, and in the shafting range of the motion subspace, the machine tool configuration is evaluated; the method comprises the following steps: mapping processing track data to a dimensionality reduction quotient space, extracting track feature information, reconstructing an operable subunit combination according to a shafting combination constraint condition based on the feature information, generating a candidate configuration set, evaluating the candidate configuration set according to an evaluation criterion, screening out a qualified candidate configuration, and carrying out iterative optimization on the candidate configuration based on an optimization target. And generating an optimal configuration scheme. According to the method, the precision and efficiency of configuration design are remarkably improved, a high-stability and high-reliability configuration scheme is provided for complex machining tasks, meanwhile, full-process automation is achieved, the design period is greatly shortened, the development cost is reduced, and the requirements for efficient and precise machining of the modern manufacturing industry are met.

The invention provides an aero-engine part configuration design optimization method and system, and the method comprises the steps: determining an engineering design demand, and taking the engineering design demand as an input, and defining an initialization optimization space; determining a target requirement as an optimization target, establishing a topological optimization model, and carrying out topological optimization calculation to obtain an initial optimization configuration; a high-order curved surface fitting mode is adopted to carry out smoothing processing on the outer contour of the initial optimization configuration, and a topological optimization result of smoothing processing is reconstructed to generate an engineering geometric entity formed by smooth transition connection of regular geometric entities; performing feature recognition on the engineered geometric entity, defining feature control parameters, and realizing parameterization; carrying out convergence judgment on a parameterization result, and if convergence is carried out, outputting a part configuration meeting the requirement; and if not, returning to carry out secondary topological optimization. According to the method, automatic iteration of topological optimization and parameter optimization can be achieved, the final design configuration is obtained from nothing to thing, the development speed is increased, and the development cost is reduced.

The present application relates to a kind of tubular diffuser meridional flow passage center line design method, including the diffuser meridional flow passage center line is divided into inlet straight section, elbow transition section and outlet axial straight section three parts, then after the total length of diffuser meridional flow passage center line is segmented normalization, the inclination angle distribution of diffuser meridional flow passage center line with the normalization change is defined, and the total length of diffuser meridional flow passage center line is calculated, finally the diffuser meridional flow passage center line coordinate distribution obtained by design is calculated and output, complete the configuration design of diffuser meridional flow passage center line.The present application method can quickly build the tubular diffuser structure satisfying engineering demand, with higher geometric configuration freedom degree, facilitate subsequent development its aerodynamic performance optimization design, significantly expand the engineering applicability and design space of tubular diffuser.

This invention belongs to the field of thermal power unit automation control technology, and discloses a configuration batch replacement method and related device based on hash caching technology. The configuration batch replacement method includes: reading a modified measurement point mapping table to obtain all source KKS and target KKS; updating the original hash table cached in memory based on the obtained source KKS and target KKS to obtain an updated hash table; traversing the updated hash table to perform configuration batch replacement; wherein, during configuration replacement, location information is obtained through the measurement point type, and then the source KKS in the indexed variable is replaced with the target KKS through the location information index variable. This invention can achieve fast and accurate replacement of KKS within the configuration, helping engineers to perform efficient configuration design; this invention solves the technical problems of slow configuration replacement speed and high system resource consumption in existing technologies, and has high engineering application value.

The invention discloses a heat supply network system measuring point information synchronization method and device. The method comprises the steps of obtaining a configuration file and a data configuration file of each controller; traversing each function block of each controller, and determining a function block referencing the measurement point information; on the basis of the function block quoting the measurement point information, actual measurement point information corresponding to the function block is searched in a measurement point library of the controller; comparing the reference measuring point information with the actual measuring point information; if the reference measuring point information is inconsistent with the measuring point page number and / or the measuring point description of the actual measuring point information, synchronizing the reference measuring point information in the function block into the actual measuring point information; and after the reference measurement point information of all the functional blocks in the controller is synchronized, writing the synchronized data object structure of each controller into a disk. According to the method and the device, the reference information in all the controllers can be synchronized before the configuration is downloaded, so that the efficiency of configuration design, modification, migration and debugging is improved.

The application discloses a customized product configuration design scheme recommendation method based on a retrieval and sorting model. First, according to historical customer order data and corresponding bill of materials, a screening demand feature vector and an instance feature vector of a corresponding module instance are determined; then, module classification is performed on all module instances to obtain a module instance set of different modules, and retrieval data sets and sorting data sets of the modules are processed and obtained; then, the retrieval data sets of the modules are respectively input into corresponding module retrieval models, and the sorting data sets are input into a sorting model for training, so that trained retrieval models and sorting models corresponding to the modules are obtained; according to new order data, all new data sample features are determined and then input into the two trained models, and each optimal module instance is selected to manufacture a current customized product. The application reduces the difficulty and cost of complex configuration knowledge representation, maintenance and update, and improves the customized product configuration design efficiency.