66 results about "Configuration design" patented technology

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.

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 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.

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.

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.

The invention discloses an aerodynamic heat management configuration design method for a large-airspace and wide-speed-domain hypersonic aircraft. The aerodynamic heat management configuration design method comprises the steps that a reference aerodynamic layout is determined, and appearance design oriented to heat flow distribution optimization is carried out; establishing a thermal environment database through multi-working-condition numerical simulation; dividing the surface of the aircraft into thermal management areas of different grades based on the thermal environment database; configuring a thermal protection material and designing a gradient thermal protection structure for each thermal management area to realize conformal integration with the reference aerodynamic layout; the integrity and reliability of the integrated structure under the heat / force load are verified through heat / structure coupling simulation analysis; and carrying out performance evaluation and iterative optimization, and if the design indexes are not met, returning to corresponding steps for optimization until the design is converged. Integrated collaborative design and closed-loop iterative optimization of aerodynamic configuration and thermal management performance are realized from a design source, and the problems of overweight of a thermal protection system, poor thermal environment adaptability and low design efficiency caused by a traditional serial method are effectively solved.

The present invention realizes an update support system capable of optimizing a QoS during an update of a system. An update support system according to the present invention comprises: a design unit that designs an updated concrete configuration of a target system providing a service by repeatedly executing, with respect to a service requirement, a concretization procedure in which a plurality of concretization rules defining a method for concretizing an abstract configuration of the target system are referred to, and one or more of the concretization rules corresponding to the abstract configuration are specified and applied to generate one or more abstract configurations or concrete configurations, and generates an operation model of the target system corresponding to the updated concrete configuration; a generation unit that generates a QoS evaluation function for evaluating, when updating the abstract configuration of the target system to the concrete configuration designed by the design unit, a quality of service (QoS) of the configuration of the target system in the middle of the update; and a planning unit that plans, by using the operation model and the QoS evaluation function, an update procedure satisfying a QoS-based criterion.

This invention provides a composite material carrier structure design method, comprising the following steps: S100, performing external load constraint analysis to form external load design constraints; S200, performing platform constraint analysis to form platform design constraints; S300, performing static design based on external load design constraints and platform design constraints to obtain static design results; S400, performing dynamic design based on platform design constraints and static design results to output a composite material carrier structure design scheme. This invention solves the problems of composite material carriers being unable to meet complex multi-source constraints, slow design iteration convergence, and poor reliability through systematic constraint analysis, configuration design based on loads, multidisciplinary optimization, and rigorous static / dynamic performance verification iteration.

This application discloses a method, apparatus, device, and storage medium for generating SCADA configuration screens based on generative AI, relating to the field of industrial control technology. The method includes: collecting natural language design requirements using an intent understanding module and the perception layer in an AI Agent cognitive architecture; obtaining state acquisition data and integrating it before inputting it to the cognitive layer; the inference engine and large language model in the cognitive layer decompose the configuration design task of the integrated data, generating a configuration design operation instruction set and inputting it to the execution layer; the execution layer processes the operation instruction set to obtain each component to be laid out in the configuration screen and its configuration data; the layout engine determines the component layout result in the configuration canvas; the variable binding engine binds and maps each component to the real-time data points of the SCADA system; and the target configuration screen is generated by combining the Shell command security module and the security layered architecture to improve the efficiency of generating SCADA configuration screens.

The application discloses a kind of based on RFLP's warship power steam system digital configuration design method, belong to warship power steam system design technical field, including system requirement analysis, system function analysis, logic architecture generation, logic to physical architecture mapping 4 design stages.Based on the design mode of RFLP, the basic idea is to replace document with digital modeling into system scheme design, the vocabulary, parameter of system structure, function, performance, specification and requirement described in design document are all expressed with digital model.Taking model as center, then create or generate other artifacts from it, including automatically generating document, report, chart and table.This method enhances traceability and consistency, improves design efficiency.

This invention relates to the field of bridge technology and provides a design method for a passive cooling system for cables. The method involves obtaining the fire heat flux density acting on the outer surface of the cable's protective layer, using this fire heat flux density as a heat input benchmark to determine the thermal configuration design parameters of the phase change material layer and the heat dissipation configuration design parameters of the thermosiphon cycle. A comprehensive thermal verification is then performed by combining the fire heat flux density, design buffer time, and the critical failure temperature of the cable material to determine the first dimensional design parameters related to the phase change material layer and the second dimensional design parameters related to the condensation section. These first and second dimensional design parameters are then used as the system design result. This application enables active and efficient cooling that is completely independent of external energy and control. It can self-sense and self-start when a fire occurs and continuously provide protection for the cable using its own physical mechanisms, thereby bridging the technological gap between passive delay and complex active cooling.

A method, apparatus, and system for network slice instance topology design may be provided and may include, receiving, by a network service management function of a network, at least one input slice / service requirement; generating, by the network service management function, a network slice instance (NSI) and network slice subnet instance (NSSI) topology and configuration design based on the at least one input slice / service requirement using a network slice design function; previewing, by the network service management function, the generated design including outputting design phase feasibility result for the design; sending, by the network service management function, an input service profile and NSI / NSSI design guidance to a network slice management function (NSMF) of the network based on the design; and sending, by the network service management function, an input slice profile and NSSI design guidance to a network slice subnet management function (NSSMF) of the network based on the design.

The application discloses a kind of heat network system measuring point information synchronization method and device, the method includes: obtaining the configuration file and data configuration file of each controller;Each functional block of each controller is traversed, and the functional block of reference measuring point information is determined;Based on the functional block of reference measuring point information, the actual measuring point information corresponding to the functional block is found in the measuring point library of controller;Reference measuring point information is compared with actual measuring point information;If the measuring point page number and / or measuring point description of reference measuring point information and actual measuring point information are inconsistent, then the reference measuring point information in the functional block is synchronized to actual measuring point information;After the reference measuring point information of all functional blocks in controller is synchronized, the data object structure of each controller after synchronization is written into disk.The application can synchronize the reference information in all controllers before configuration is downloaded, and improve the efficiency of configuration design, modification, migration and debugging.