Carrier rocket equipotential data processing method, device and equipment

Abstract

The invention provides a carrier rocket equipotential data processing method, a carrier rocket equipotential data processing device and carrier rocket equipotential data processing equipment, belongs to the technical field of rocket electrical design, and solves the problems of long rocket equipotential design period and poor collaboration. The method comprises the steps that rocket equipotential design constraint data and rocket lap joint assembly data are acquired; determining an equipotential design knowledge database according to the rocket equipotential design constraint data and the rocket lap joint assembly data; obtaining a rocket design model; according to the equipotential design knowledge database, verifying the rocket design model to obtain a rocket equipotential design model; and performing performance analysis on the rocket equipotential design model to obtain carrier rocket equipotential design data. According to the scheme, digitization and collaboration of rocket equipotential design are realized.

Description

Technical Field

[0001] This invention relates to the field of rocket electrical design technology, and in particular to a method, apparatus and equipment for processing equipotential data of launch vehicles. Background Technology

[0002] In the electrical system design of launch vehicles, equipotential bonding is a core element in ensuring electromagnetic compatibility, lightning protection, and signal integrity. Current technologies primarily rely on traditional, document-based, and experience-driven design processes. Specifically, a "distributed overlap design" model is typically employed, where the structural and electrical departments work separately: the structural department designs connection schemes for components such as modules and flanges based on mechanical requirements, achieving physical connections through bolts, riveting, etc.; the electrical department then submits overall performance requirements, such as overlap resistance and the number of overlap points, in document form. The transfer of design requirements between different disciplines depends on manual interpretation of two-dimensional drawings and technical specifications, lacking a system-level, data-driven collaborative platform. Furthermore, design verification is severely delayed; the compliance of equipotential performance can only be confirmed after the rocket's final assembly, through on-site resistance measurements or large-scale ground tests. This series of sequential processes, centered on "post-launch verification through testing," constitutes the current mainstream technical state in the field of launch vehicle equipotential bonding design.

[0003] Existing technical solutions suffer from several systemic flaws and are no longer able to meet the high reliability and short development cycle requirements of modern aerospace models. First, the design process suffers from low collaboration efficiency and is prone to errors. Document-based specification transmission inherently suffers from information attenuation and misunderstanding. Electrical engineers' requirements for lap resistance are difficult for structural engineers to accurately implement in 3D models, and structural design changes cannot be fed back to the electrical team in real time for electrical performance evaluation. This professional barrier leads to design blind spots, easily resulting in underlying defects such as unreasonable lap point placement and discontinuous lap paths. Second, design verification is severely delayed and costly. The true nature of equipotential performance is only revealed after final assembly or even before testing. Once tests reveal excessive resistance or potential difference, large-scale physical rework is required, involving disassembly, reprocessing, and even component scrapping, leading to extended development cycles and soaring costs. Third, design quality relies excessively on personal experience, making it difficult to pass on knowledge and ensure consistency. Design level is strongly correlated with the personal experience of senior engineers; their tacit knowledge fails to be transformed into reusable explicit design rules, resulting in a lack of repeatable reliability guarantees for design outcomes. Finally, existing methods lack forward-looking simulation analysis capabilities, making it impossible to predict the transient potential distribution at the moment of a lightning strike or identify potential electromagnetic interference risks during the design phase. This makes it possible for rocket electrical systems to be shipped with "potential defects," posing a deep-seated safety risk. Summary of the Invention

[0004] This invention provides a method, apparatus, and equipment for processing equipotential data of launch vehicles, which solves the problems of long design cycles, poor coordination, and lack of verification in rocket equipotential design.

[0005] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows: This invention provides a method for processing equipotential data of a launch vehicle, comprising: Obtain rocket equipotential design constraint data and rocket assembly component data; Based on the rocket equipotential design constraint data and rocket assembly data, an equipotential design knowledge database is determined. Obtain rocket design models; Based on the equipotential design knowledge database, the rocket design model is verified to obtain the rocket equipotential design model. The performance of the rocket equipotential design model was analyzed to obtain the equipotential design data of the launch vehicle.

[0006] Optionally, based on the rocket equipotential design constraint data and rocket assembly data, an equipotential design knowledge database is determined, including: The rocket's equipotential design constraint data is parsed and processed to obtain an equipotential design constraint set, which includes interface data, maximum overlap resistance value, minimum number of overlap points, and maximum overlap spacing. The rocket splicing component data is classified and processed to obtain a rocket standard component database, which includes a component database of component material properties, cross-sectional area parameters, and resistivity parameters; Logical association processing is performed on the equipotential design constraint set and the rocket standard component database to obtain the equipotential design knowledge database.

[0007] Optionally, the rocket design model is verified based on the equipotential design knowledge database to obtain a rocket equipotential design model, including: The rocket design model is subjected to electrical interface identification processing to obtain interface data; Based on the interface data, the equipotential design knowledge database is extracted and processed to obtain the overlapping component data; Based on the data of the overlapping components, the electrical performance parameters of the interface are determined, including the overlapping resistance value, the number of overlapping points, and the overlapping spacing. Based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

[0008] Optionally, based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model, including: The overlap resistance value is compared with the maximum overlap resistance value in the equipotential design knowledge database to obtain the overlap resistance comparison result; The number of overlapping points is compared with the minimum number of overlapping points in the equipotential design knowledge database to obtain the comparison result of the number of overlapping points. The overlap spacing is compared with the maximum overlap spacing in the equipotential design knowledge database to obtain the overlap spacing comparison result; Based on the comparison results of the overlap resistance, the number of overlap points, and the overlap spacing, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

[0009] Optionally, performance analysis is performed on the rocket equipotential design model to obtain equipotential design data for the launch vehicle, including: The rocket equipotential design model is transformed into equivalent data to obtain circuit network data. Transient simulation analysis was performed on the circuit network data to obtain the rocket body potential distribution data; The equipotential performance of the rocket body potential distribution data was verified to obtain the equipotential design data of the launch vehicle.

[0010] Optionally, the potential distribution data of the rocket body is subjected to equipotential performance verification to obtain the equipotential design data of the launch vehicle, including: Based on the rocket body potential distribution data, multiple equipment installation points were determined; Based on the plurality of device installation points, determine the maximum transient potential difference between the plurality of device installation points; The maximum transient potential difference is compared with a preset withstand voltage threshold to obtain the verification result; Based on the rocket body potential distribution data and the verification results, the equipotential design data of the launch vehicle are determined.

[0011] Optionally, the method for processing equipotential data of the launch vehicle further includes: The equipotential design data of the launch vehicle is extracted and processed to obtain the installation data of the overlapping components. The component installation data includes the installation position data, attitude data and connection relationship data of the overlapping components. Based on the installation data of the overlapping components, the equipotential design knowledge database is traversed to obtain the resistance data of the overlapping points. The installation position data, attitude data, connection relationship data, and joint resistance data of the overlapping components are integrated to obtain and output the rocket equipotential test document data.

[0012] This invention provides a launch vehicle equipotential data processing device, comprising: The acquisition module is used to acquire rocket equipotential design constraint data and rocket assembly component data; The processing module is used to determine the equipotential design knowledge database based on the rocket equipotential design constraint data and rocket assembly data. The acquisition module is also used to acquire rocket design models; The determination module is used to verify the rocket design model based on the equipotential design knowledge database to obtain the rocket equipotential design model; and to perform performance analysis on the rocket equipotential design model to obtain the launch vehicle equipotential design data.

[0013] This invention also provides a computing device, including: a processor and a memory storing a computer program, wherein the computer program, when run by the processor, executes the above-described method.

[0014] This invention also provides a computer-readable storage medium storing instructions that, when executed on a computer, cause the computer to perform the above-described method.

[0015] The technical solution of the present invention has at least the following effects: The above-described solution of the present invention acquires rocket equipotential design constraint data and rocket assembly data; determines an equipotential design knowledge database based on the rocket equipotential design constraint data and rocket assembly data; acquires a rocket design model; verifies the rocket design model based on the equipotential design knowledge database to obtain a rocket equipotential design model; and performs performance analysis on the rocket equipotential design model to obtain launch vehicle equipotential design data; thus realizing the digitalization, collaboration, and forward-looking verification of rocket equipotential design. Attached Figure Description

[0016] Figure 1 This is a flowchart of the equipotential data processing method for launch vehicles provided in an embodiment of the present invention; Figure 2 This is a schematic flowchart of the equipotential data processing method for launch vehicles provided in this embodiment of the invention; Figure 3 This is a structural diagram of the launch vehicle equipotential data processing device provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the structure of the computing device provided in an embodiment of the present invention. Detailed Implementation

[0017] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0018] like Figure 1 As shown, an embodiment of the present invention proposes a method for processing equipotential data of a launch vehicle, comprising: Step 11: Obtain rocket equipotential design constraint data and rocket assembly component data; Step 12: Determine the equipotential design knowledge database based on the rocket equipotential design constraint data and rocket assembly data; Step 13, Obtain the rocket design model; Step 14: Verify the rocket design model based on the equipotential design knowledge database to obtain the rocket equipotential design model; Step 15: Perform performance analysis on the rocket equipotential design model to obtain the launch vehicle equipotential design data.

[0019] In step 11 of this embodiment, unstructured equipotential design constraint data, such as maximum overlap resistance, required number of overlap points, and current carrying capacity of the current discharge path, are extracted from design specifications, standards, corporate design manuals, summaries of historical project experience, and expert review opinions. Simultaneously, rocket overlap component data, including the component's physical dimensions, material resistivity, cross-sectional area, and current capacity, are obtained from the bill of materials, supplier manuals, and material databases. This data serves as the raw input for constructing the knowledge base.

[0020] In step 12, the design constraint data is first parsed into a structured set of digital rules. For example, the text requirement "resistance value of a single overlap point between the engine and the compartment ≤ 2mΩ" is converted into a logical unit "Application interface: engine-compartment && parameter: single-point resistance ≤ value: 0.002Ω". Secondly, the overlap component data is parameterized to build a standard component library, defining key attributes for each component (such as material resistivity ρ, cross-sectional area A). Then, the rules are integrated with the components to form an interactive knowledge database, and its accuracy and applicability are verified through historical cases. The core of the knowledge database includes a pre-calculated model of the overlap component resistance.

[0021] In step 13, the overall three-dimensional structural model of the rocket is loaded. This model contains geometric information of each section, engine, separation mechanism, etc., serving as the basic platform for equipotential design. The model must include the definition of areas such as metal sections and composite material components to facilitate the subsequent identification of equipotential bonding and insulation isolation areas.

[0022] In step 14, the structural areas and key interfaces (such as the engine-cabin interface) requiring equipotential bonding are identified in the 3D model; suitable overlapping components are selected from the knowledge database and arranged in the model; the system calculates the resistance value of each component in real time and performs compliance verification, such as whether the resistance value exceeds the limit and whether the spacing between overlapping points is uniform; the design is optimized based on the verification results, such as replacing components or adjusting the layout, until all indicators are compliant, and finally outputs a 3D equipotential design model containing complete overlapping component information and electrical connection network.

[0023] In step 15, the 3D model is converted into an equivalent circuit model for simulation analysis, including lightning strikes, to calculate transient potentials and potential differences. High-risk areas are identified and optimization suggestions are generated through heatmap visualization. Finally, based on the validated model, production and inspection data, such as installation diagrams, component lists, resistance requirement tables, and test plans, are automatically output, forming structured data directly usable for manufacturing and inspection. Performance analysis ensures the design meets equipotential requirements and achieves a closed loop of design-simulation-optimization.

[0024] The technical solution described in this embodiment transforms scattered design specifications, standard requirements, and best practices into automatically executable verification rules by constructing a digital equipotential design rule knowledge base. Based on a unified 3D model platform, it enables parallel collaborative design between electrical and structural professionals in key areas such as engine interfaces and separation surfaces, and calculates lap resistance in real time and automatically performs compliance checks. Furthermore, it simulates electrical performance such as lightning strikes by establishing equivalent circuit models, proactively predicting the overall rocket potential distribution and risk areas during the design phase. Finally, it automatically outputs structured data that can be directly used for production and inspection, realizing the transformation of rocket equipotential design from the traditional model relying on personal experience and later physical verification to a data-driven, intelligent verification digital design model, improving the first-time success rate of the design and the overall electrical safety of the rocket. It breaks down professional barriers, effectively reduces later rework, and shortens the development cycle. At the same time, through a standardized knowledge base and automated data output, it ensures the consistency and reliability of design quality, providing a comprehensive, efficient, and reliable solution for launch vehicle equipotential design.

[0025] In an optional embodiment of the present invention, step 12, determining the equipotential design knowledge database based on the rocket equipotential design constraint data and rocket assembly data, may include: Step 121: The rocket equipotential design constraint data is parsed and processed to obtain an equipotential design constraint set, which includes interface data, maximum overlap resistance value, minimum number of overlap points, and maximum overlap spacing. Step 122: Classify the rocket splicing component data to obtain a rocket standard component database, which includes a component database of component material properties, cross-sectional area parameters and resistivity parameters; Step 123: Perform logical association processing on the equipotential design constraint set and the rocket standard component database to obtain the equipotential design knowledge database.

[0026] In step 121 of this embodiment, unstructured raw constraint data collected from standards, specifications, design manuals, and expert experience is parsed and summarized to identify and extract key design parameters and logical conditions, which are then transformed into computer-processable "attribute-operator-value" structured rules. The equipotential design constraint set mainly includes: (1) Interface data: Identifies the specific interface to which the rules apply, such as "engine-section interface" or "interstage separation surface".

[0027] (2) Maximum lap resistance value: For example, “the resistance value of a single lap point between the engine and the compartment is ≤2mΩ”, which is interpreted as the rule: [Application interface: engine-compartment]&&[parameter: single point resistance]<=[value:0.002](Ω).

[0028] (3) Minimum number of overlap points: For example, “the separation surface needs at least 4 overlap points evenly distributed in the circumference” is interpreted as the rule: [Application interface: separation surface]&&[parameter: number of overlap points]>=[value:4].

[0029] (4) Maximum overlap spacing: Used to ensure the uniformity of the layout of multiple overlap points on the same interface, and is resolved as the rule: [Application interface: separation surface]&&[parameter: overlap point spacing]<=[value:0.6](m).

[0030] In step 122, based on the bill of materials, supplier manuals, and material database, digital model entries are created for each standard specification of overlapping component, such as copper strips and aluminum strips of different sizes, and their key physical and electrical property parameters are defined. The rocket standard component database mainly includes: (1) Component material properties: such as defining the material as 'Copper' or 'Aluminumalloy2A12'.

[0031] (2) Cross-sectional area parameter (A): For example, for a copper strip of 25mm × 3mm, its cross-sectional area A = (25 × 10 -3 )×(3×10 -3 ) = 75 × 10 -6 m 2 .

[0032] (3) Resistivity parameter (ρ): For example, the resistivity of copper is ρ≈1.68×10 -8 Ω·m, the resistivity of aluminum is ρ≈2.82×10 -8 Ω·m.

[0033] This database provides the foundation for subsequent real-time resistance calculations.

[0034] In step 123, structured design rules are mapped and associated with parametric standard components. For example, when a rule specifies the requirements of "engine-cabin section" interface and "resistance ≤ 2mΩ", the system can automatically filter candidate components (such as CU_STRAP_25×3mm) that meet the resistivity and cross-sectional area requirements from the component library. At the same time, association rules between materials and processes are established (such as automatically associating "conductive oxidation" when "aluminum alloy 2A12" is selected). The integrated knowledge base is verified and initialized using historical design cases to ensure that its output (such as compliance judgment and component recommendation) conforms to engineering practice. Finally, an integrated, interactive equipotential design knowledge database containing rules, components and their internal relationships is formed.

[0035] In an optional embodiment of the present invention, step 14, verifying the rocket design model according to the equipotential design knowledge database to obtain the rocket equipotential design model, may include: Step 141: Perform electrical interface identification processing on the rocket design model to obtain interface data; Step 142: Based on the interface data, extract and process the equipotential design knowledge database to obtain the overlapping component data; Step 143: Determine the interface electrical performance parameters based on the overlapping component data. The interface electrical performance parameters include the overlapping resistance value, the number of overlapping points, and the overlapping spacing. Step 144: Based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

[0036] In step 141 of this embodiment, on the loaded three-dimensional structural model of the rocket, electrical designers, guided by the equipotential design knowledge database, identify and mark all critical electrical connection interfaces. This interface data clarifies the structural connection parts that require focused equipotential design and verification, mainly including: the connection interface between the engine and the compartment, the interstage separation surface interface between the compartments, and the grounding interface between the rocket body and the ground.

[0037] In step 142, based on the specific interface type identified in step 141 (such as "engine-cabin interface"), the system automatically matches and extracts the design rules applicable to the interface and a list of recommended standard lap joint components from the equipotential design knowledge database. For example, the system will filter out candidate components in the knowledge base that meet the resistance and current capacity requirements specified by the rules for this interface, such as CU_STRAP_25x3mm (25mm wide, 3mm thick copper strip) and its complete attribute data (material, resistivity ρ, cross-sectional area A, etc.).

[0038] In step 143, a specific overlapping component is selected from the recommended candidate components and placed at the corresponding interface location in the 3D model. The system then automatically calculates and determines the electrical performance parameters of the interface based on the 3D model. Overlap resistance value: For each overlapping component in the arrangement, use the formula R = ρ × l / A Its resistance value is calculated in real time. Among these, resistivity... ρ and cross-sectional area A Valid length is obtained from component data. l The coordinates of the two mounting points of the component in three-dimensional space are automatically calculated by the system.

[0039] Number of overlap points: The system automatically counts the total number of overlap components placed for this interface.

[0040] Overlap spacing: The system calculates the three-dimensional spatial distance between any two overlap points on the same interface, finds the minimum spacing, and evaluates its distribution uniformity.

[0041] In step 144, the system automatically compares and verifies the compliance of the real-time performance parameters (overlap resistance value, number of points, and spacing) calculated in step 143 with the constraint rules set for this interface in the knowledge database (such as maximum resistance limit, minimum number of points, and maximum allowable spacing). If the parameters do not meet the rules (e.g., the calculated resistance exceeds the limit or the number of points is insufficient), the system will issue an alarm and provide correction guidance (such as suggesting replacing with a component with a larger cross-sectional area or adjusting the installation position to shorten the length). l (Or increase the number of overlap points). Following the guidelines, optimize the design, recalculate and verify the system until all electrical performance parameters of the interface conform to the knowledge base rules. Finally, output a three-dimensional rocket equipotential design model containing a complete overlap network, with all interfaces verified.

[0042] In an optional embodiment of the present invention, step 144, which involves correcting the interface electrical performance parameters based on the equipotential design knowledge database to obtain a rocket equipotential design model, may include: Step 1441: Compare the lap resistance value with the maximum lap resistance value in the equipotential design knowledge database to obtain the lap resistance comparison result; Step 1442: Compare the number of overlapping points with the minimum number of overlapping points in the equipotential design knowledge database to obtain the comparison result of the number of overlapping points; Step 1443: Compare the overlap spacing with the maximum overlap spacing in the equipotential design knowledge database to obtain the overlap spacing comparison result; Step 1444: Based on the comparison results of the overlap resistance, the number of overlap points, and the overlap spacing, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

[0043] In step 1441 of this embodiment, according to the formula: R = ρ × l / A ; The resistance value of each lap component is calculated in real time and compared one by one with the maximum lap resistance value set in the knowledge database for that specific interface rule (e.g., "engine-cabin interface resistance ≤ 2mΩ"). The comparison result will clearly identify each component as "compliant" (calculated resistance ≤ maximum limit) or "exceeding the limit" (calculated resistance > maximum limit), and visually alert components that exceed the limit (e.g., highlighted in red). It may also suggest correction directions, such as "recommend replacing with a component with lower resistivity or larger cross-sectional area" or "optimize wiring route to shorten length". l ".

[0044] In step 1442, the number of all overlapping components deployed for the current interface is automatically counted, and this number of overlapping points is compared with the minimum number of overlapping points required by the rules for this interface in the knowledge database (e.g., "the separation surface must have at least 4 overlapping points evenly distributed around the circumference"). The comparison result will clearly indicate whether the interface is "compliant" (actual number ≥ minimum number) or "insufficient" (actual number < minimum number), and an alarm will be issued for interfaces with insufficient numbers, prompting that more overlapping points need to be added.

[0045] In step 1443, the three-dimensional spatial distance between all pairs of overlapping points on the same interface is calculated, and these distances are compared with the maximum overlapping spacing (e.g., 0.6 meters) defined by rules in the knowledge database. The comparison results will identify all point pairs that exceed the maximum allowable spacing, evaluate the uniformity of the overall layout, and issue alarms for areas with excessive spacing or uneven distribution, prompting that the installation positions of the overlapping points need to be adjusted to achieve a more uniform distribution.

[0046] In step 1444, all the comparison results above are synthesized to provide designers with clear correction guidelines. The 3D model can then be iteratively optimized according to these guidelines. If the resistance exceeds the standard, measures such as replacing components or optimizing the path should be taken.

[0047] If there are not enough points, add more overlap points.

[0048] If the spacing exceeds the standard, adjust the position of the existing points.

[0049] After each modification, the system re-executes steps 143 and 1441 to 1443 for real-time calculation and verification until all electrical performance parameters (resistance, quantity, spacing) of the interface meet the rule requirements in the knowledge base. Once all interfaces have passed verification, the system finally outputs a corrected and optimized rocket equipotential design model with all equipotential design indicators showing compliance.

[0050] In an optional embodiment of the present invention, step 15, performing performance analysis on the rocket equipotential design model to obtain launch vehicle equipotential design data, may include: Step 151: Perform equivalent transformation on the rocket equipotential design model to obtain circuit network data; Step 152: Perform transient simulation analysis on the circuit network data to obtain the rocket body potential distribution data; Step 153: Verify the equipotential performance of the rocket body potential distribution data to obtain the equipotential design data of the launch vehicle.

[0051] In step 151 of this embodiment, the three-dimensional physical model containing the complete overlap network is converted into an equivalent circuit model composed of lumped parameter elements for simulation analysis. Each overlap component (such as an overlap strip) is modeled as a resistor R and a parasitic inductance connected in series with it. L parasitic Its value is given by the formula L parasitic = μ 0×( l / (2π))×ln(4× l / d )Calculated, where μ 0 is the permeability of free space. l For component length, d (Equivalent diameter). Each conductive structure (such as a metal section shell) is simplified to a corresponding distributed or lumped parameter impedance model based on its geometry and material properties. All these components are correctly connected in the circuit according to their physical connections in the 3D model, ultimately outputting a complete equipotential equivalent circuit model of the rocket, i.e., circuit network data, which can be used for circuit simulation.

[0052] In step 152, simulation conditions are set on the equivalent circuit model according to standards in the knowledge base (such as lightning protection standards). For example, a standard lightning current waveform (such as a pulse current with an amplitude of 200kA) is injected as an excitation source at key locations such as the top of the fairing. Simultaneously, key equipment installation points and compartment interfaces requiring potential monitoring are defined as observation points in the circuit model. Subsequently, a circuit simulator (such as one based on the SPICE engine) is called to perform transient time-domain analysis. By solving the linear equation system: [G]{V}={I}, where [G] is the admittance matrix, {V} is the node voltage vector, and {I} is the excitation current vector, the potential change V(t) of each observation point over time, as well as the current data of each branch, are calculated throughout the simulation time under transient excitation. These data together constitute detailed rocket body potential distribution data.

[0053] In step 153, calculate the maximum transient potential difference between any two critical equipment installation points (e.g., point A and point B): Δ V AB =| V A (t)- V B (t)| max The calculated maximum potential difference is compared with the device interface withstand voltage limit (e.g., 50V) defined in the knowledge base to determine whether the equipotential performance is up to standard. Simultaneously, the system maps the potential distribution data back to the 3D model, visually displaying the potential levels of various parts of the rocket body in the form of a heatmap, and highlighting and warning areas where the potential difference exceeds the limit. Finally, the system outputs equipotential design data for the launch vehicle, including compliance judgment results, a visual simulation report, and optimization design guidelines (such as indicating risk areas requiring additional bonding paths). If verification is successful, this data can be used as the final output; if there are exceedances, this data will provide precise evidence for returning to the design stage for optimization.

[0054] In an optional embodiment of the present invention, step 153, verifying the equipotential performance of the rocket body potential distribution data to obtain the equipotential design data of the launch vehicle, may include: Step 1531: Determine multiple equipment installation points based on the rocket body potential distribution data; Step 1532: Determine the maximum transient potential difference between the plurality of device installation points based on the plurality of device installation points; Step 1533: Compare the maximum transient potential difference with a preset withstand voltage threshold to obtain the verification result; Step 1534: Determine the equipotential design data of the launch vehicle based on the potential distribution data of the rocket body and the verification results.

[0055] In step 1531 of this embodiment, the data nodes corresponding to the specific installation locations of key electronic devices, sensitive instruments, or electrical interfaces on the rocket are located and extracted from the full-rocket potential distribution data output from the transient simulation analysis in step 152. These equipment installation points (such as point A, point B, point C, etc.) are the core focus areas for equipotential performance verification. Their selection is based on the electrical system architecture, equipment importance, and potential risk area analysis, such as the installation interfaces of navigation system equipment, control computers, energy management units, etc.

[0056] In step 1532, all device installation points determined in step 1531 are paired. For each pair (e.g., device A and device B), the absolute value of the instantaneous potential difference between them is calculated over the entire transient simulation time range, and the maximum value of this potential difference during the entire transient process is found. This calculation needs to be performed on all possible device pairs to determine the maximum transient potential difference existing in the entire system.

[0057] In step 1533, the maximum transient potential difference between each pair of devices calculated in step 1532 is compared with a preset withstand voltage threshold obtained from the equipotential design knowledge database. This threshold is a pre-set qualification criterion based on the electrical withstand capability of the device interface circuit (such as the 50V withstand voltage specified in the standard). The comparison result generates a verification result, clearly determining whether it is "compliant" (i.e., the maximum transient potential difference between all pairs of devices does not exceed the withstand voltage threshold) or "exceeds the standard" (i.e., the maximum transient potential difference between at least one pair of devices exceeds the withstand voltage threshold), and specifically identifying which pairs of devices have the risk of exceeding the standard.

[0058] In step 1534, all results from the system comprehensive simulation analysis are used to generate the final deliverable. This includes: The potential distribution data of the rocket body is mapped back to the three-dimensional model to generate a potential distribution heat map, which intuitively displays high-risk areas.

[0059] Generate a detailed equipotential performance verification report, including the verification results of step 1533, a list of out-of-specification devices, and the specific out-of-specification potential difference values.

[0060] Based on the verification results and potential distribution, design optimization guidelines are provided, such as: "An overlap path needs to be added in the area between device A and device B to reduce the potential difference."

[0061] The final packaged output of the launch vehicle's equipotential design data includes a simulation-verified design model, compliance conclusions, and necessary optimization suggestions. If the verification is successful, this data can be used as the basis for the final design; if it fails, it will guide the next round of design iterations.

[0062] In an optional embodiment of the present invention, the method for processing equipotential data of a launch vehicle may further include: Step 16: Extract and process the equipotential design data of the launch vehicle to obtain the installation data of the overlapping components. The component installation data includes the installation position data, attitude data and connection relationship data of the overlapping components. Step 17: Based on the installation data of the overlapping components, traverse the equipotential design knowledge database to obtain the resistance data of the overlapping points; Step 18: Integrate the installation position data, attitude data, connection relationship data, and joint resistance data of the overlapping components to obtain rocket equipotential test document data and output it.

[0063] In step 16 of this embodiment, the system automatically identifies and extracts precise information about each overlapping component (such as overlapping strips and conductive pads) from the rocket equipotential design model that has been simulated, verified, and finalized. This information constitutes the overlapping component installation data, which mainly includes: Installation location data: The precise coordinates of the two installation points of each overlapping component in the rocket's three-dimensional coordinate system.

[0064] Attitude data: Spatial orientation and angle of the component between mounting points.

[0065] Connection relationship data: The topological relationship between two specific structural components to which a component is connected (e.g., “section A flange” connects to “section B flange”) is defined.

[0066] In step 17, based on the installation data extracted in step 16, especially the component model and the effective length l calculated from the installation point coordinates, the standard component library in the equipotential design knowledge database is automatically traversed and queried. The predefined material resistivity ρ and cross-sectional area A of the component model are obtained from the component library. Then, the core physical model encapsulated in the knowledge base is called to calculate the theoretical design resistance value for each joint in this installation state. This process generates a complete list of joint resistance data for all joints.

[0067] In step 18, all structured data obtained in the previous steps are automatically correlated, summarized, and formatted to generate a rocket equipotential testing document data package that can directly guide post-assembly inspection work. This data package mainly includes: Equipotential measurement point layout diagram: Mark the physical location and unique number of each joint point on the rocket assembly drawing (e.g., generated according to the rule "P-" + area code + "-" + serial number).

[0068] Overlap Resistance Requirement Table: A structured table listing the overlapping components, installation locations, theoretical design resistance values, and acceptance upper limit resistance values ​​for each test point number.

[0069] Equipotential testing procedure: specifies the measuring instruments to be used (such as micro-ohmmeters), the measurement procedures (such as using the four-wire measurement method to measure the DC resistance between the measuring points PX and PY), and the pass / fail criteria for comparing the measured values ​​with the required values ​​in the document.

[0070] like Figure 2 As shown, a specific embodiment of the equipotential data processing method for launch vehicles provided by this invention is as follows: Step 1: Obtain rocket equipotential design constraint data and rocket assembly component data; Collect all unstructured texts and requirements related to equipotential bonding design from standards, corporate design specifications, summaries of past project experience, and expert review opinions. This data includes, but is not limited to: the maximum permissible lap resistance value (e.g., 2mΩ) for different interfaces (e.g., engine-section, interstage separation surface), the minimum number of lap points (e.g., 4), the maximum lap spacing (e.g., 0.6 meters), the current carrying capacity requirements for lightning current discharge paths (e.g., 200kA), and material and surface treatment requirements.

[0071] Collect detailed parameters for all standard lap joint components (such as copper strips, aluminum strips, and connectors of different specifications) from bills of materials, supplier manuals, and material databases. This data includes: component model, material type, and geometric dimensions (used to calculate cross-sectional area). A ), material resistivity ρ And rated current capacity, etc.

[0072] Step 2: Based on the rocket equipotential design constraint data and rocket assembly data, determine the equipotential design knowledge database; The design constraint data is parsed into computer-processable "attribute-operator-value" logical units. For example, "the resistance value of a single lap point between the engine and the compartment is ≤2mΩ" is parsed into the rule: [Application interface: engine-compartment]&&[parameter: single point resistance]<=[value:0.002](Ω).

[0073] Create a digital model for each standard lap joint component and define its key properties. For example, define the properties for component CU_STRAP_25x3mm as: {Material: 'Copper', Cross-sectional area: 75e-6m²}. 2 Resistivity: 1.68e-8Ω·m, Current capacity: 100000A.

[0074] The system associates structured design rules with a parametric component library. For example, when a rule specifies the "engine-cabin" interface and resistance requirements, the system can automatically filter out candidate components such as CU_STRAP_25x3mm. Simultaneously, it establishes rules linking materials and processes (e.g., automatically associating "conductive anodizing" surface treatment when "aluminum alloy 2A12" is selected).

[0075] The integrated knowledge base was tested and fine-tuned using historical design cases to ensure its output conforms to engineering realities, ultimately forming a validated and usable equipotential design knowledge database. This knowledge base encapsulates core calculation models, such as the formula for calculating the DC resistance of lap joint components: R=ρ×L / A.

[0076] Step 3: Obtain the rocket design model; Import the overall three-dimensional structural model of the launch vehicle, which includes the geometric information of all key components such as each section, engine, and separation mechanism.

[0077] In the 3D model, guided by the knowledge base, the metal areas that need to be equipotentially connected and the composite material areas that need to be insulated are initially identified.

[0078] Step 4: Verify the rocket design model based on the equipotential design knowledge database to obtain the rocket equipotential design model; Identify key electrical interfaces (such as engine-cabin interfaces) in the 3D model. Select appropriate lap components for each interface from the knowledge base and place them between the two connection points in the 3D model.

[0079] The system will automatically perform the following operations in the background: Calculate its effective length based on the component's three-dimensional coordinates. l .

[0080] Call the formula R=ρ× from the knowledge base l / A, calculates the resistance value of each lapped component in real time.

[0081] The calculated resistance value is compared in real time with the rule limits for that interface in the knowledge base.

[0082] Check whether the number of overlaps and the circumferential spacing meet the requirements of the rules.

[0083] The verification results are displayed instantly in a visual manner (e.g., color highlighting). If the resistance exceeds the limit, the number of points is insufficient, or the spacing is uneven, the designer can optimize according to the prompts, such as replacing components, shortening the length, or adjusting the position of the points. Electrical and structural engineers collaborate on modifications on a unified platform until all verification indicators show compliance.

[0084] Finally, a rocket equipotential design model containing a complete electrical connection network is generated, in which all equipotential designs have passed real-time verification.

[0085] Step 5: Perform performance analysis on the rocket equipotential design model to obtain the launch vehicle equipotential design data; The three-dimensional equipotential design model is converted into an equivalent circuit network model composed of lumped parameter elements such as resistors and parasitic inductances.

[0086] Extreme operating conditions (such as injecting a 200kA standard lightning current waveform at the top of the fairing) are set on the equivalent circuit, and the installation points of key equipment are defined as observation points. A circuit simulator is called to perform transient time-domain analysis, and the potential data V(t) of all observation points during the transient process is calculated to obtain the potential distribution data of the rocket body.

[0087] Calculate the maximum transient potential difference Δ between any two critical equipment installation points. V ABmax ; calculate Δ V ABmax Compare the device's tolerance voltage threshold (e.g., 50V) as defined in the knowledge base to determine compliance.

[0088] The potential distribution data is mapped back to the 3D model to generate a potential distribution heatmap, and areas exceeding the standard are highlighted and alerted.

[0089] The final output is the launch vehicle's equipotential design data. This data package includes: a simulation-verified design model, a compliance assessment report, visualized simulation results, and clear design optimization guidelines (such as indicating risk areas requiring reinforcement of joints), forming a closed loop of "design-simulation-optimization." If the verification passes, this data becomes the final design outcome; if it fails, the process returns to step four for optimization iterations based on this data.

[0090] The proposed method for processing equipotential data for launch vehicles achieves standardized and intelligent equipotential design through the collaborative design of a digital knowledge base and 3D models. It enables precise prediction of electrical performance during the design phase via real-time calculations and simulations, allowing for early identification and optimization of risks. This resolves problems at the drawing stage, avoiding the high-cost rework caused by traditional methods that rely on experience and only discover issues after assembly and testing. Simultaneously, automated rule checks and data generation ensure the consistency and reliability of design quality, significantly improve cross-disciplinary collaboration efficiency, and streamline the data flow from design to manufacturing and inspection. Ultimately, this drastically shortens the development cycle and reduces costs and risks.

[0091] like Figure 3 As shown, this embodiment of the invention also provides a launch vehicle equipotential data processing device 30, comprising: Module 31 is used to acquire rocket equipotential design constraint data and rocket assembly component data; Processing module 32 is used to determine the equipotential design knowledge database based on the rocket equipotential design constraint data and rocket assembly data; Module 31 is also used to acquire rocket design models; The determination module 33 is used to verify the rocket design model based on the equipotential design knowledge database to obtain the rocket equipotential design model; and to perform performance analysis on the rocket equipotential design model to obtain the launch vehicle equipotential design data.

[0092] Optionally, processing module 32 is specifically used for: The rocket's equipotential design constraint data is parsed and processed to obtain an equipotential design constraint set, which includes interface data, maximum overlap resistance value, minimum number of overlap points, and maximum overlap spacing. The rocket splicing component data is classified and processed to obtain a rocket standard component database, which includes a component database of component material properties, cross-sectional area parameters, and resistivity parameters; Logical association processing is performed on the equipotential design constraint set and the rocket standard component database to obtain the equipotential design knowledge database.

[0093] Optionally, module 33 is specifically used for: The rocket design model is subjected to electrical interface identification processing to obtain interface data; Based on the interface data, the equipotential design knowledge database is extracted and processed to obtain the overlapping component data; Based on the data of the overlapping components, the electrical performance parameters of the interface are determined, including the overlapping resistance value, the number of overlapping points, and the overlapping spacing. Based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

[0094] Optionally, based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model, including: The overlap resistance value is compared with the maximum overlap resistance value in the equipotential design knowledge database to obtain the overlap resistance comparison result; The number of overlapping points is compared with the minimum number of overlapping points in the equipotential design knowledge database to obtain the comparison result of the number of overlapping points. The overlap spacing is compared with the maximum overlap spacing in the equipotential design knowledge database to obtain the overlap spacing comparison result; Based on the comparison results of the overlap resistance, the number of overlap points, and the overlap spacing, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

[0095] Optionally, module 33 is also specifically used for: The rocket equipotential design model is transformed into equivalent data to obtain circuit network data. Transient simulation analysis was performed on the circuit network data to obtain the rocket body potential distribution data; The equipotential performance of the rocket body potential distribution data was verified to obtain the equipotential design data of the launch vehicle.

[0096] Optionally, the potential distribution data of the rocket body is subjected to equipotential performance verification to obtain the equipotential design data of the launch vehicle, including: Based on the rocket body potential distribution data, multiple equipment installation points were determined; Based on the plurality of device installation points, determine the maximum transient potential difference between the plurality of device installation points; The maximum transient potential difference is compared with a preset withstand voltage threshold to obtain the verification result; Based on the rocket body potential distribution data and the verification results, the equipotential design data of the launch vehicle are determined.

[0097] Optionally, the launch vehicle equipotential data processing device 30 further includes: The generation module 34 is used to extract and process the equipotential design data of the launch vehicle to obtain the installation data of the overlapping components. The component installation data includes the installation position data, attitude data, and connection relationship data of the overlapping components. Based on the installation data of the overlapping components, the equipotential design knowledge database is traversed to obtain the resistance data of the overlapping points. The installation position data, attitude data, connection relationship data, and resistance data of the overlapping components are integrated to obtain the rocket equipotential inspection document data and output it.

[0098] It should be noted that this device is a device corresponding to the above method. All implementation methods in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0099] like Figure 4 As shown, this embodiment of the invention also provides a computing device 40, including a processor 41, a memory 42, and a program or instructions stored in the memory 42 and executable on the processor 41. When the program or instructions are executed by the processor 41, they implement the various processes of the above-described embodiment of the launch vehicle equipotential data processing method and achieve the same technical effects. To avoid repetition, they will not be described again here. It should be noted that the computing device in this embodiment of the invention includes the aforementioned mobile electronic devices and non-mobile electronic devices.

[0100] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0101] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0102] In the embodiments provided by this invention, it should be understood that the disclosed apparatus and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between apparatuses or units may be electrical, mechanical, or other forms.

[0103] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0104] In addition, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit.

[0105] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, ROM, RAM, magnetic disks, or optical disks.

[0106] Furthermore, it should be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent solutions of the present invention. Moreover, the steps performing the above series of processes can naturally be executed in the order described, but are not necessarily required to be executed in chronological order; some steps can be executed in parallel or independently of each other. Those skilled in the art will understand that all or any step or component of the method and apparatus of the present invention can be implemented in any computing device (including processors, storage media, etc.) or network of computing devices, in hardware, firmware, software, or a combination thereof. This is something that those skilled in the art can achieve by using their basic programming skills after reading the description of the present invention.

[0107] Therefore, the object of the present invention can also be achieved by running a program or a set of programs on any computing device. The computing device can be a known general-purpose device. Therefore, the object of the present invention can also be achieved simply by providing a program product containing program code for implementing the method or apparatus. That is, such a program product also constitutes the present invention, and the storage medium storing such a program product also constitutes the present invention. Obviously, the storage medium can be any known storage medium or any storage medium developed in the future. It should also be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent to the present invention. Furthermore, the steps for performing the above series of processes can naturally be performed in the order described, but are not necessarily required to be performed in chronological order. Some steps can be performed in parallel or independently of each other.

[0108] The above are preferred embodiments of the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for processing equipotential data of a launch vehicle, characterized in that, include: Obtain rocket equipotential design constraint data and rocket assembly component data; Based on the rocket equipotential design constraint data and rocket assembly data, an equipotential design knowledge database is determined. Obtain rocket design models; Based on the equipotential design knowledge database, the rocket design model is verified to obtain the rocket equipotential design model. The performance of the rocket equipotential design model was analyzed to obtain the equipotential design data of the launch vehicle.

2. The method for processing equipotential data of a launch vehicle according to claim 1, characterized in that, Based on the rocket equipotential design constraint data and rocket assembly data, an equipotential design knowledge database is determined, including: The rocket's equipotential design constraint data is parsed and processed to obtain an equipotential design constraint set, which includes interface data, maximum overlap resistance value, minimum number of overlap points, and maximum overlap spacing. The rocket splicing component data is classified and processed to obtain a rocket standard component database, which includes a component database of component material properties, cross-sectional area parameters, and resistivity parameters; Logical association processing is performed on the equipotential design constraint set and the rocket standard component database to obtain the equipotential design knowledge database.

3. The method for processing equipotential data of a launch vehicle according to claim 1, characterized in that, Based on the equipotential design knowledge database, the rocket design model is verified to obtain the rocket equipotential design model, including: The rocket design model is subjected to electrical interface identification processing to obtain interface data; Based on the interface data, the equipotential design knowledge database is extracted and processed to obtain the overlapping component data; Based on the data of the overlapping components, the interface electrical performance parameters are determined, including the overlapping resistance value, the number of overlapping points, and the overlapping spacing. Based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

4. The method for processing equipotential data of a launch vehicle according to claim 3, characterized in that, Based on the equipotential design knowledge database, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model, including: The overlap resistance value is compared with the maximum overlap resistance value in the equipotential design knowledge database to obtain the overlap resistance comparison result; The number of overlapping points is compared with the minimum number of overlapping points in the equipotential design knowledge database to obtain the comparison result of the number of overlapping points. The overlap spacing is compared with the maximum overlap spacing in the equipotential design knowledge database to obtain the overlap spacing comparison result; Based on the comparison results of the overlap resistance, the number of overlap points, and the overlap spacing, the electrical performance parameters of the interface are corrected to obtain the rocket equipotential design model.

5. The method for processing equipotential data of a launch vehicle according to claim 1, characterized in that, The performance of the rocket's equipotential design model was analyzed to obtain the launch vehicle's equipotential design data, including: The rocket equipotential design model is transformed into equivalent data to obtain circuit network data. Transient simulation analysis was performed on the circuit network data to obtain the rocket body potential distribution data; The equipotential performance of the rocket body potential distribution data was verified to obtain the equipotential design data of the launch vehicle.

6. The method for processing equipotential data of a launch vehicle according to claim 5, characterized in that, The equipotential performance of the rocket body potential distribution data is verified to obtain the equipotential design data of the launch vehicle, including: Based on the rocket body potential distribution data, multiple equipment installation points were determined; Based on the plurality of device installation points, determine the maximum transient potential difference between the plurality of device installation points; The maximum transient potential difference is compared with a preset withstand voltage threshold to obtain the verification result; Based on the rocket body potential distribution data and the verification results, the equipotential design data of the launch vehicle are determined.

7. The method for processing equipotential data of a launch vehicle according to claim 1, characterized in that, Also includes: The equipotential design data of the launch vehicle is extracted and processed to obtain the installation data of the overlapping components. The component installation data includes the installation position data, attitude data and connection relationship data of the overlapping components. Based on the installation data of the overlapping components, the equipotential design knowledge database is traversed to obtain the resistance data of the overlapping points. The installation position data, attitude data, connection relationship data, and joint resistance data of the overlapping components are integrated to obtain and output the rocket equipotential test document data.

8. A launch vehicle equipotential data processing device, characterized in that, include: The acquisition module is used to acquire rocket equipotential design constraint data and rocket assembly component data; The processing module is used to determine the equipotential design knowledge database based on the rocket equipotential design constraint data and rocket assembly data. The acquisition module is also used to acquire rocket design models; The determination module is used to verify the rocket design model based on the equipotential design knowledge database to obtain the rocket equipotential design model; and to perform performance analysis on the rocket equipotential design model to obtain the launch vehicle equipotential design data.

9. A computing device, characterized in that, include: A processor, a memory storing a computer program, wherein the computer program, when executed by the processor, performs the method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The system stores instructions that, when executed on a computer, cause the computer to perform the method as described in any one of claims 1 to 7.

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