36 results about "Configuration design" patented technology

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 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 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.

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 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 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 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.

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.

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.

The application discloses a kind of manta ray submarine cluster propulsion modeling and numerical calculation method, belong to underwater bionic robot technical field.The method includes: establishing initial cluster model;By applying coordinate transformation to surface grid node, the parameterization flexible adjustment of different cluster formation is realized;For each individual, configure active flapping motion equation, and by setting motion frequency, phase, wave number and other coupling parameters, the motion coupling relationship between individuals is established;Based on the immersed boundary method, the parameterized cluster model is coupled to the flow field solver, high-fidelity numerical calculation is carried out, and the hydrodynamic performance and full flow field information of the cluster and individual are obtained;Analysis of performance data and flow field structure reveals the cluster propulsion gain mechanism.The present application first systematically solves the problem of bionic multi-body cluster modeling and efficient calculation with active deformation, fills the technical gap in this field, and provides a key theoretical basis and design tool for the configuration design and cooperative control of bionic underwater vehicle cluster.

The invention discloses a data center PDU configuration real-time verification and energy efficiency optimization system and method, relates to the technical field of data center power supply and distribution, and aims to solve the problems of single data source, limited analysis dimension, lagged recognition period, low accuracy and the like in the existing PDU configuration design. The system comprises a data input module, a verification analysis module, an optimization recommendation module and a result output module. The data input module receives and analyzes PDU configuration information including an IT equipment list, PDU model capacity, power supply topology and load parameters. And the verification analysis module performs multi-dimensional real-time verification of overload risk, three-phase imbalance and single-point fault on the PDU scheme in a design configuration stage through a parallel verification circuit. The optimization recommendation module is internally provided with an AI optimization engine, verifies an extreme scene through peak load Monte Carlo simulation based on historical case learning, adopts a genetic algorithm to generate a phase sequence optimization scheme, and recommends a proper PDU model based on a knowledge base. And the result output module outputs a verification result, risk early warning, optimization suggestion and energy efficiency analysis in real time. According to the system, efficient and accurate verification and intelligent optimization in the design stage are achieved, the change cost is remarkably reduced, the reliability and energy efficiency of the system are improved, and the system is suitable for intelligent assistance of PDU configuration design of the data center.

The invention belongs to the technical field of overall design of aircrafts, and particularly relates to a low-resistance modeling design method of an unmanned helicopter. Comprising the following steps: 1, selecting a control point set of longitudinal and transverse contours of an unmanned helicopter body, respectively establishing longitudinal and transverse contour parameterized control curves passing through the control points, and determining initial values of tension proportion parameters of the control points on the longitudinal and transverse curves; 2, constructing a corresponding parameterized control curve as an internal load space control optimization model, and solving the internal load space control optimization model by adopting a genetic algorithm on the basis of an optimization target with the minimum windward area and by taking the equipment and part loading space, the mounting gap and the process manufacturing as constraint conditions, so as to obtain a control curve of a typical section of a fuselage; and 3, importing the fuselage three-dimensional model into a fluid dynamic tool to calculate aerodynamic resistance, obtaining a fuselage sample aerodynamic data set, constructing an agent model for optimization, and obtaining an optimal unmanned helicopter model.

The application discloses a network algorithm integrated multi-core particle integrated system network design method, which designs the network layer in the multi-core particle integrated system by integrating an operation unit in a network unit. The method mainly comprises router micro-architecture design, task mapping and software and hardware collaborative design; the router micro-architecture design is the hardware implementation, flow control, pipeline design and arbitration design of the router, and part of the calculation amount that needs to be aggregated is transplanted from the processor to the network for processing; the task mapping is the mapping of the tasks in the application system flow diagram to the multi-core particle integrated system; and the software and hardware collaborative design is the optimal software and hardware configuration designed in the mode of software and hardware combination with the minimum application running time as the target. The application can realize calculation in the data transmission process, reduces the data amount of network transmission and communication delay, thereby accelerating the running speed of the application on the multi-core particle integrated system.

The invention relates to a method for designing a central line of a meridian flow channel of a tubular diffuser, which comprises the following steps of: dividing the central line of the meridian flow channel of the diffuser into three parts, namely an inlet straight line section, a bent pipe transition section and an outlet axial straight line section; and the dip angle distribution, changing along with normalization, of the central line of the meridian flow channel of the diffuser is defined, the total length of the central line of the meridian flow channel of the diffuser is calculated, finally, the coordinate distribution of the central line of the meridian flow channel of the diffuser obtained through design is calculated and output, and the configuration design of the central line of the meridian flow channel of the diffuser is completed. According to the method, the tubular diffuser structure meeting the engineering requirements can be rapidly constructed, meanwhile, the high geometrical configuration freedom degree is achieved, subsequent aerodynamic performance optimization design of the tubular diffuser is facilitated, and the engineering applicability and design space of the tubular diffuser are remarkably expanded.

The invention discloses a wind turbine blade anti-icing and de-icing integrated heating assembly and a design method and system. The technical problems that in an existing electric heating anti-icing and de-icing technology, assembly design precision is low, energy consumption is high, and universality is poor are solved. According to the heating assembly, an ultrathin graphene film serves as a heating element, the ultrathin graphene film and a composite material are integrally formed, and configuration design is completed through high-precision simulation of a flow field, a water drop field, icing and a thermal load in combination with an improved NSGA-III multi-objective optimization algorithm; according to the anti-icing and de-icing system, based on thermal load characteristics of components, an integrated solution of component accurate design and system cooperative control is formed through scientific partitioning, three-dimensional simulation verification and multi-mode multi-stage power control law design. Accurate matching of the heating assembly and the non-uniform thermal load of the blade is achieved, system energy consumption is remarkably reduced, the intelligent degree of control is high, wind turbine blades of different models are adapted, and the economical efficiency and safety of operation of a wind turbine generator in the severe cold area are greatly improved.

This positioning configuration design device includes a positioning configuration setting unit that excludes facilities which are likely to be able to be excluded from facilities respectively positioned at a plurality of locations and sets a positioning configuration of the facilities; a feasibility confirmation unit that judges whether predetermined conditions are feasible or not in the set positioning configuration of the facilities; an exclusion candidate list updating unit that registers, in an exclusion candidate list, information of the facilities excluded in the positioning configuration in which the conditions are feasible, a non-excludable list updating unit that registers, in a non-excludable list, information of the facilities excluded in the positioning configuration in which the conditions are not feasible; and a control unit that repeatedly executes confirmation processing including setting of the positioning configuration and judgment of feasibility of the conditions while incrementing the number of facilities to be excluded one at a time until a positioning configuration in which the conditions are feasible and no further facilities are able to be excluded is able to be calculated.

The invention discloses a regionalization design method for improving PCB design efficiency and consistency, and the method comprises the following steps: creating and defining a plurality of regionalization design units based on a function modular structure of a circuit in a printed circuit board design environment; configuring a design rule for the regionalized design unit; completing layout and wiring design in a source regionalization design unit; and mapping and multiplexing layout and wiring information in the source regionalization design unit into one or more target regionalization design units through format copying operation. The method has the advantages that the completed module layout and wiring design can be quickly reused for other modules of the same structure through the format copying function, the manual layout and wiring time is greatly saved, repeated labor is avoided, and the problem of the consistency between the efficiency of complex printed circuit board design and physical implementation is practically solved through the method.

The invention discloses a planetary gear kinematics calculation method based on a structure matrix, and the method comprises the steps: defining a composite two-stage planetary gear train configuration design space, and building a three-node lever model of a planetary gear; generating a classification numbering rule representing a node interconnection scheme according to a parallel connection relation of internal nodes of the two-stage planetary gear train; based on a classification numbering rule, node lengths of the three-node lever model are subjected to normalization processing, a four-node composite lever model is established, and a composite lever length matrix is obtained; an integration matrix is constructed based on the connection relation between the planet rows and the power assembly distribution mode; constructing a normalized matrix based on the composite lever model and the planet row characteristic parameters; based on the integrated matrix and the normalized matrix, constructing a kinematics calculation formula of the structure matrix; and inputting the composite lever length matrix into a kinematics calculation formula of the structure matrix, and outputting transmission ratio information.

1. The name of the present design product: doctor program control software graphical user interface for electronic equipment. 2. The use of the present design product: an electronic equipment. 3. The design points of the present design product: in the graphical user interface. 4. The picture or photo that best indicates the design points: design 1 front view. 5. The electronic equipment of the present design product is of conventional design, and the rear view, left view, right view, top view and bottom view are omitted. 6. Design 1 is designated as the basic design. 7. The use of the graphical user interface: the interface of the present design product is an application display interface. 8. The human-computer interaction mode of the graphical user interface: design 1 front view shows the graphical user interface of the doctor program control software. The user can drag the electrodes on the right side of design 1 front view to the electrode configuration area in the middle of design 1 front view to configure the electrodes. Design 2 front view shows the graphical user interface of the doctor program control software. Compared with design 1 front view, in design 2 front view, the user has dragged the electrodes on the right side of the front view to the electrode configuration area in the middle of design 2 front view, and the clicks have been tested. The user can click / touch the "cable configuration" button on the lower left side of design 2 front view to configure the cable. Design 3 front view shows the graphical user interface of the doctor program control software. The user can drag the cable and / or aircraft clamp on the right side of design 3 front view to the cable configuration area on the left side of design 3 front view to configure the cable. Design 4 front view shows the graphical user interface of the doctor program control software. The cable configuration area on the left side of design 4 front view has been configured with an aircraft clamp. The user can click / touch the "electrode test" button on the lower side of design 4 front view to perform electrode test. Design 5 front view shows the graphical user interface of the doctor program control software. The cable configuration area on the left side of design 5 front view has been configured with a cable. The user can click / touch the "electrode test" button on the lower side of the front view to perform electrode test. Design 6 front view shows the graphical user page of the doctor program control software. The left side of design 6 front view shows multiple interface information of the pulse generator, and the right side of design 6 front view shows electrode information. The user can click / touch the "start configuration" button on the lower side to match the pulse generator and the electrode.

This invention discloses a multistable connecting joint and a folding method. The multistable folding joint is based on a single-vertex six-fold origami configuration, with vertical panels set at the edges of the planar fold structure to form a connecting unit with spatial folding and rotation capabilities. The folding joint mainly consists of oppositely arranged rigid body units and folding units between them. Through the coordinated design of the fold configuration and panel layout, the joint can form multiple stable configurations under different folding states. The folding method of this invention, through the design of the fold geometry and panel spatial arrangement, achieves reversible transformation between multiple stable states of the folding joint, and maintains structural stability without the need for additional locking mechanisms. This method enables the configuration design of multistable folding joints under different initial configuration conditions, and is suitable for the design and application of reconfigurable origami mechanisms and deformable structures.