Carrier rocket cable network beam splitting data processing method, device and equipment

Abstract

The invention provides a carrier rocket cable network beam splitting data processing method, device and equipment, belongs to the technical field of rocket manufacturing, and solves the problems of unreasonable layout, poor assembly compatibility and incapability of dynamically responding to system change in carrier rocket cable beam splitting design. The method comprises the following steps: acquiring rocket appearance data and cabin section layout data; analyzing and processing the rocket appearance data and the cabin section layout data to obtain spatial constraint data; determining a trunk line path according to the spatial constraint data; according to the cabin section layout data and the main line path, determining segmented current data; determining cable line diameter data according to the segmented current data; and determining rocket cable beam splitting data according to the cabin section layout data and the cable wire diameter data. According to the scheme, the layout reliability is improved, the space utilization rate is increased, and the electrical stability of the rocket is guaranteed.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket manufacturing, in particular to a launch vehicle cable network beam splitting data processing method, device and equipment. BACKGROUND

[0002] The traditional beam splitting design of rocket cable network mainly relies on traditional experience method and static layout planning, lacking systematic data-driven analysis. In the prior art, the design process is usually based on the experience judgment of engineers, and the cable path is planned through two-dimensional drawings or simple three-dimensional models, which fails to fully integrate multi-dimensional factors such as rocket structure characteristics, electrical instrument distribution and dynamic environment constraints, etc. The main problems can be summarized as three points: first, the design optimization is insufficient; the current beam splitting optimization design mainly relies on experience and traditional design method, lacking comprehensive analysis of factors such as rocket structure characteristics, electrical instrument equipment quantity, space limitation, etc. This leads to unreasonable distribution of cable bundles in different cabin sections of the rocket, causing space waste or excessive concentration of cable bundles, increasing the risk of failure. Second, the transportation and assembly are difficult; the transportation process of the rocket involves segmented transportation, and the cable bundles need to be reasonably distributed and connected between different cabin sections. The existing technology often fails to fully consider the special requirements of segmented transportation in the beam splitting design, which easily causes problems such as poor interface connection of cable bundles and cabin sections or mismatched cable length, leading to increased difficulty in rocket assembly and measurement. Third, the ability of dynamic adjustment is lacking; the current cable beam splitting optimization design is usually static, i.e. fixed layout based on the requirements in the design stage. However, as the design progresses, other systems of the rocket may change, leading to the original cable layout no longer applicable. The existing technology has weak ability for dynamic adjustment, leading to a large amount of rework and modification, prolonging the development cycle and increasing the cost. SUMMARY

[0003] The present application provides a launch vehicle cable network beam splitting data processing method, device and equipment, which solves the problems of unreasonable layout, poor assembly compatibility and inability to dynamically respond to system changes in rocket cable beam splitting design.

[0004] To solve the above technical problems, the technical solutions of the present application are as follows: The present application provides a launch vehicle cable network beam splitting data processing method, device and equipment, which solves the problems of unreasonable layout, poor assembly compatibility and inability to dynamically respond to system changes in rocket cable beam splitting design. obtaining rocket shape data and cabin layout data; analyzing and processing the rocket shape data and the cabin layout data to obtain space constraint data; determining a main line path according to the space constraint data; determining segmented current data according to the cabin layout data and the main line path; determining cable network wire diameter data according to the segmented current data; Based on the compartment layout data and the cable network diameter data, the rocket cable bundle data is determined.

[0005] Optionally, obtain rocket shape data and section layout data, including: The rocket's design model is analyzed to obtain rocket shape data and compartment layout data. The rocket shape data includes at least one of diameter variation, compartment length, and compartment docking surface position. The compartment layout data includes at least one of internal space range, high-risk area range, cable fixing structure position, and instrument information.

[0006] Optionally, the rocket's external shape data and the compartment layout data are parsed to obtain spatial constraint data, including: The rocket's external shape data is identified to determine the axial baseline and the location of the docking surfaces of the modules; Based on the axial reference line, determine the axial centerline coordinate sequence; Based on the location of the docking surface of the compartment, determine the coordinate set of the docking surface of the compartment; The compartment layout data is identified to determine the internal space range, high-risk area range, cable fixing structure location, and instrument information; Based on the scope of the high-risk area, a set of prohibited passage zones is determined; Based on the location of the cable fixing structure, determine the set of cable fixing points; Based on the instrument information, determine the location data and safety distance data of the electromagnetically sensitive equipment; The internal space range is discretized according to a preset value to determine multiple grid units; Based on the axial centerline coordinate sequence, the set of docking surface coordinates of the compartments, the set of prohibited passage areas, the set of cable fixing points, the location data of the electromagnetically sensitive equipment, and the safety distance data, the multiple grid cells are labeled to obtain spatial constraint data.

[0007] Optionally, determining the trunk route based on the spatial constraint data includes: Based on the spatial constraint data, the axial centerline coordinate sequence is traversed to obtain an initial path set; The initial path set is smoothed to obtain a smoothed initial path set; The smoothed initial path set and the spatial constraint data are processed by the path optimization model to obtain the trunk path.

[0008] Optionally, based on the compartment layout data and the main line path, segmented current data is determined, including: The instrument information in the compartment layout data is traversed to obtain an instrument database, which includes parameter information of multiple instruments. Based on the parameter information of multiple instruments in the instrument database, the effective current of multiple instruments is calculated to obtain the instrument effective current set; The main route is segmented at preset intervals to obtain multiple segmented routes; The multiple segmented paths and the effective current set of the instrument are mapped to obtain segmented current data.

[0009] Optionally, based on the segmented current data, the wire diameter data of the cable network is determined, including: Acquire rocket performance data, which includes electrical design data and internal environment data; Based on the electrical design data and the segmented current data, determine the base wire diameter data; Voltage correction is applied to the basic wire diameter data to obtain wire diameter data after voltage drop compensation; Environmental correction is applied to the voltage drop compensated wire diameter data to obtain environmentally corrected wire diameter data. The wire diameter data after environmental correction is processed to obtain the wire diameter data of the cable network.

[0010] Optionally, based on the compartment layout data and the cable network diameter data, the rocket cable bundle data is determined, including: Based on the compartment layout data, the cable network diameter data is divided according to the compartment to obtain the first bundle group data; The initial bundle data is subjected to bundle diameter compatibility verification to obtain the second bundle data; according to: Determine the equivalent diameter of the cable bundle; in, D bundle The equivalent diameter of the cable bundle d i For the first i The diameter of the cable, 1≤ i ≤n, n This refers to the number of cables in the second bundle. K 1 represents the bundling redundancy coefficient. K 2 represents the sheath thickness margin; Based on the data from the second bundle, determine the sheath material data; Based on the sheath material data and the equivalent diameter of the cable bundle, the rocket cable bundle data is determined.

[0011] This invention also provides a data processing device for cable network bundling in a launch vehicle, comprising: The acquisition module is used to acquire rocket shape data and compartment layout data; The processing module is used to parse and process the rocket's external shape data and the compartment layout data to obtain spatial constraint data; determine the main trunk line path based on the spatial constraint data; determine the segment current data based on the compartment layout data and the main trunk line path; and determine the rocket cable bundle data based on the segment current data. The determination module is used to determine the rocket cable bundle data based on the compartment layout data and the cable network diameter data.

[0012] 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.

[0013] 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.

[0014] The technical solution of the present invention has at least the following effects: The above-mentioned solution of the present invention improves the layout reliability, increases space utilization, and ensures the electrical stability of the rocket by acquiring rocket shape data and compartment layout data; analyzing and processing the rocket shape data and compartment layout data to obtain space constraint data; determining the main trunk line path based on the space constraint data; determining the segment current data based on the compartment layout data and main trunk line path; determining the cable network diameter data based on the segment current data; and determining the rocket cable bundle data based on the compartment layout data and cable network diameter data. Attached Figure Description

[0015] Figure 1 This is a flowchart of the method for processing bundled data of a launch vehicle cable network provided in an embodiment of the present invention; Figure 2 This is a structural diagram of the launch vehicle cable network bundle data processing device provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of the computing device provided in an embodiment of the present invention. Detailed Implementation

[0016] 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.

[0017] likeFigure 1 As shown, an embodiment of the present invention proposes a method for processing bundled data of a launch vehicle cable network, including: Step 11: Obtain rocket shape data and compartment layout data; Step 12: Analyze the rocket's shape data and the compartment layout data to obtain spatial constraint data; Step 13: Determine the main route based on the spatial constraint data; Step 14: Determine the segmented current data based on the compartment layout data and the main line path; Step 15: Determine the cable network diameter data based on the segmented current data; Step 16: Determine the rocket cable bundle data based on the compartment layout data and the cable network diameter data.

[0018] In this embodiment, the rocket shape data includes information such as the overall size of the rocket, surface shape, and relative positions of components. This information can be used to determine the main route and spatial layout of the cable network. The compartment layout data describes the internal structure, functional zoning, and installation points of each compartment. This information is used to determine the reasonable distribution of the cable network among the compartments and avoid conflicts with equipment or pipelines.

[0019] The analysis and processing of the rocket's external shape data and the module layout data involves extracting key spatial constraint information from the rocket's external shape data and the module layout data, such as the location of the module docking surface, prohibited passage areas, and available fixing points. This spatial constraint data will serve as an important basis for subsequent trunk line path planning and cable bundle design, ensuring that the cable network design not only conforms to the rocket's structural characteristics but also meets the requirements of electrical connections.

[0020] Determining the trunk route requires comprehensive consideration of the rocket's structure, flight performance, safety, and spatial constraints. Route planning should follow principles such as path shortestization, avoidance of high-risk areas, structural dependence, and electromagnetic compatibility to ensure that the trunk route can efficiently and safely transmit power and signals. In practice, 3D modeling software can be used for path simulation and conflict detection to ensure the feasibility and safety of the trunk route.

[0021] Determining segmented current data requires statistical analysis of electrical instruments within each segment, based on the segment layout data and main line path. By statistically analyzing the power requirements, operating current, and transmission signal characteristics of the electrical instruments, the current distribution within each segment can be calculated, thus obtaining segmented current data. This segmented current data can be used to determine the cable network diameter subsequently.

[0022] Determining the cable network diameter data requires comprehensive consideration of factors such as segmented current data, cable length, environmental correction factor, and safety margin. Through overcurrent capacity modeling and calculation, the cable specifications and diameter that meet the current requirements of each section can be determined. The selection of cable diameter should ensure the safety and efficiency of power transmission, while also considering the optimization of the rocket's weight and volume.

[0023] Determining the cable bundle data for rockets requires basing the data on the compartment layout and the cable network diameter, and designing the cable network for bundle distribution. The bundle distribution design should consider the cable layout, avoid crossing, overlapping, or unreasonable routing, and select appropriate sheath materials to protect the cables. Through bundle distribution design, it is possible to ensure that the cables can smoothly transmit power and signals between different compartments of the rocket, while improving the overall space utilization efficiency of the rocket.

[0024] In this embodiment, the launch vehicle cable network bundle data processing method employs a systematic approach. Starting with acquiring rocket shape data and compartment layout data, it progressively analyzes and processes spatial constraint data to determine the main trunk path, segmented current data, and cable network diameter data, ultimately determining the rocket cable bundle data. This ensures the accuracy, reliability, and efficiency of the cable network design, providing a stable and reliable guarantee for the rocket's electrical system.

[0025] In an optional embodiment of the present invention, step 11 may include: Step 111: Analyze the rocket design model to obtain rocket shape data and compartment layout data. The rocket shape data includes at least one of diameter variation, compartment length, and compartment docking surface position. The compartment layout data includes at least one of internal space range, high-risk area range, cable fixing structure position, and instrument information.

[0026] In this embodiment, the rocket's design model includes its three-dimensional geometric information, which can be created and maintained using computer-aided design (CAD) software or other 3D modeling tools. The rocket's external shape data includes, but is not limited to, information such as diameter variations, section lengths, and section docking surface positions. This data can be used to determine the macroscopic path of the cable network on the rocket. For example, diameter variation information helps determine the bending radius and spatial constraints of the cable network in different sections; section lengths are used to calculate the distribution length of the cable network within each section; and the section docking surface positions determine the penetration points and interface design of the cable network when connecting across sections.

[0027] Similar to acquiring rocket shape data, obtaining module layout data also involves analyzing the rocket design model, primarily focusing on detailed internal layout information of the modules. Module layout data includes the internal space extent, high-risk area range, cable fixing structure locations, and instrument information. Internal space extent information is used to determine the specific routing and distribution of the cable network within the module; high-risk area ranges (such as high-temperature zones near engine nozzles and fuel tanks) are used to avoid these hazardous areas when planning the cable network, ensuring its safety and reliability; cable fixing structure location information is used to determine the fixing points and support methods of the cable network within the module, ensuring its stability and mechanical strength; instrument information includes the specific locations and power requirements of electrical instruments, control systems, sensors, etc., installed within the module.

[0028] Through the above process, comprehensive and accurate data on the rocket's external shape and compartment layout can be obtained, providing a data foundation for subsequent cable network bundle data processing methods. This data not only helps determine the main cable network routes and bundle schemes, but also ensures the rational distribution and efficient transmission of the cable network on the rocket, improving the stability and reliability of the rocket's electrical system.

[0029] In an optional embodiment of the present invention, step 12 may include: Step 121: Identify the rocket's external shape data to determine the axial baseline and the position of the docking surface of the modules; Step 122: Determine the axial centerline coordinate sequence based on the axial reference line; Step 123: Determine the coordinate set of the docking surface of the compartment based on the location of the docking surface of the compartment; Step 124: Identify the compartment layout data to determine the internal space range, high-risk area range, cable fixing structure location, and instrument information; Step 125: Determine the set of prohibited passage areas based on the high-risk area range; Step 126: Determine the set of cable fixing points based on the location of the cable fixing structure; Step 127: Determine the location data and safety distance data of the electromagnetically sensitive device based on the instrument information; Step 128: Discretize the internal space range according to a preset value to determine multiple grid units; Step 129: Based on the axial centerline coordinate sequence, the section docking surface coordinate set, the prohibited passage area set, the cable fixing point set, the electromagnetic sensitive equipment location data, and the safety distance data, the multiple grid cells are labeled to obtain spatial constraint data.

[0030] In steps 121 to 123 of this embodiment, firstly, the axial reference line is extracted from the rocket's external shape drawing, that is, the rocket's longitudinal axis centerline is used as the reference path of the main cable line, and a coordinate sequence of the rocket's axial centerline is generated. These coordinate sequences provide the precise position information of the rocket's axial centerline in three-dimensional space to ensure the shortest transmission distance. Then, the docking surface coordinate positions of each section (such as the first stage, second stage, and payload compartment) are identified. These docking surface positions are key nodes for the connection of the cable network between different sections. Finally, a set of section docking surface coordinates is generated. This set of coordinates is used to plan the penetration points of cross-section cables. In steps 124 to 127, high-risk areas (such as engine nozzles, fuel tanks, and hydraulic lines) are identified from the compartment layout diagram, and their safety boundaries are calculated to generate a set of prohibited passage areas. High-risk areas are defined as those whose distance from high-risk equipment is less than or equal to the minimum safe distance. Then, structural components within the compartment that can be used for cable fixing (such as longitudinal beams and bulkhead supports) are extracted to form a set of cable fixing points. Finally, the positions of high-power equipment (such as servo mechanisms) are marked, and the minimum parallel spacing is set to 300mm to generate electromagnetically sensitive equipment location data and safety distance data. In step 128, the internal space of the rocket is discretized into grid cells, and the attributes of each cell are labeled. These attribute values ​​include: passable, prohibited, or fixed point, which can be represented as: ; in,( x , y , z () is a point in the rocket's three-dimensional coordinate system. for( x , y , z The attribute values ​​of the points; the constraint rules for generating path planning are: (1) The main route must meet the following requirements: the distance from high-risk equipment must be greater than the minimum safe distance; (2) The cable fixing point shall not exceed 1m to meet the vibration resistance requirements; (3) The parallel distance from high-power equipment shall not be less than 300mm; In step 129, the various data obtained in the above steps are comprehensively utilized to perform detailed annotations on the determined multiple grid cells. The annotation content includes, but is not limited to, the axial centerline coordinate sequence, the set of docking surface coordinates of the compartments, the set of prohibited passage areas, the set of cable fixing points, the location data of electromagnetically sensitive equipment, and the safety distance data. Through these annotations, spatial constraint data is obtained. This data provides comprehensive spatial constraint information for subsequent cable network path planning, ensuring that the cable network can be laid out efficiently and safely while meeting all constraint conditions.

[0031] In an optional embodiment of the present invention, step 13 may include: Step 131: Based on the spatial constraint data, traverse the axial centerline coordinate sequence to obtain an initial path set; Step 132: Smooth the initial path set to obtain a smoothed initial path set; Step 133: Process the smoothed initial path set and the spatial constraint data input path optimization model to obtain the trunk path.

[0032] In this embodiment, the spatial constraint data obtained in previous steps is first utilized. This data contains detailed restrictions on the rocket's internal space, such as prohibited areas, cable anchoring points, and the locations of electromagnetically sensitive equipment. Next, the axial centerline coordinate sequence is traversed. This sequence represents the precise location of the rocket's designed centerline in three-dimensional space, providing a basic framework for planning the main cable network path. During the traversal, various constraints in the spatial constraint data must be considered, such as avoiding prohibited areas and proximity to cable anchoring points, thereby generating a series of possible initial paths. These initial paths constitute the initial path set, providing candidate solutions for subsequent path optimization. Specifically, using the centerline as a reference, the axial centerline coordinate sequence is traversed to generate initial main path paths (i.e., the initial path set), ensuring the shortest possible path. The constraints that the initial main path paths must satisfy include: the path must pass through the coordinates of all module docking surfaces. In step 132, the paths in the initial path set are not smooth enough due to spatial constraints, containing too many bends or sharp turns. This can lead to difficulties in the installation and maintenance of cable networks in practical applications, and even affect the transmission efficiency of cables. Therefore, it is necessary to smooth the initial path set. Specifically, cubic spline interpolation or Bézier curves are used to smooth the initial trunk path to avoid sharp-angle bends, resulting in a smoothed initial path set. The constraints that the smoothed initial path set must satisfy include: (1) The minimum distance between the path and the prohibited area is ≥ D safe ; (2) The distance between adjacent fixed points is ≤1m.

[0033] (3) Parallel distance from high-power equipment ≥ D EMC When crossing, they pass perpendicularly; in, D safe To ensure the minimum safe distance, it is generally taken as... D safe =50mm; D EMC To minimize the parallel spacing, it is generally taken as... DEMC =300mm In step 133, the smoothed initial path and spatial constraint data are input into the path optimization model for processing. The path optimization model uses the A* algorithm for path optimization; specifically, it searches for the optimal path using path length and curvature as cost functions, which can be expressed as: Path_Opt=A_Star(Path_Smooth,Grid, w 1, w 2); in, w 1 represents the length weight. w 2 represents the curvature weight, Path_Opt is the final path after A* optimization, Path_Smooth is the smoothed initial path, Grid is the discretized 3D grid marking passable / prohibited areas, and A_Star() is the function of the A* path search algorithm.

[0034] The path optimization model also includes: a dynamic vibration verification process, which involves simulating the launch vibration spectrum to verify whether the spacing between fixed points meets the vibration resistance requirements; Constraint: If the vibration value exceeds the threshold, additional fixed points need to be added.

[0035] The final path of the optimized output data is the main trunk path. This path not only meets the spatial constraints but also ensures the efficient and safe transmission of the cable network, providing a stable and reliable guarantee for the rocket's electrical system.

[0036] In an optional embodiment of the present invention, step 14 may include: Step 141: Traverse the instrument information in the compartment layout data to obtain an instrument database, which includes parameter information of multiple instruments. Step 142: Calculate the effective current of multiple instruments based on the parameter information of multiple instruments in the instrument database to obtain a set of instrument effective currents; Step 143: Divide the main line path into segments according to a preset interval to obtain multiple segmented paths; Step 144: Map the multiple segmented paths and the instrument's effective current set to obtain segmented current data.

[0037] In this embodiment, the instrument information in the compartment layout data first needs to be traversed. The compartment layout data includes the structural information, equipment location, and installed electrical instruments inside each compartment of the rocket. The purpose of traversing the instrument information is to extract the parameter information of all electrical instruments in each compartment. These parameters include the instrument's name, model, power requirement, operating current, and transmission signal type. The extracted instrument parameter information is then organized into an instrument database, which will serve as the basis for subsequent calculations of effective current and segmented current data.

[0038] In step 142, after obtaining the instrument database, the effective current of each instrument is calculated based on its parameter information. The calculation of the effective current may consider factors such as the instrument's power requirements, operating voltage, and duty cycle. The calculation method can be determined according to the instrument's characteristics and actual needs. The calculation formula is as follows: ; in, I effective The effective current of the instrument, P For the power requirements of electrical instruments, V The operating voltage of electrical instruments. c The duty cycle of electrical instruments; After calculating the effective current of each instrument, the data are compiled into a set of effective instrument currents. This set will be used for subsequent segmented current data calculations.

[0039] In step 143, after determining the main trunk path, in order to facilitate subsequent calculations and analysis, the main trunk path needs to be segmented according to a preset interval. The size of the segment interval (e.g., every 1m) may be determined based on factors such as the actual structure of the rocket, the layout requirements of the cable network, and the calculation accuracy. After segmentation, the main trunk path is divided into multiple segmented paths, and each segmented path represents a specific route of the cable network inside the rocket.

[0040] In step 144, the segmented paths are mapped to the effective current sets of the instruments. The purpose of the mapping is to determine the instruments connected to each segmented path and the effective current of these instruments. Through the mapping process, the total current requirement of each segmented path can be obtained, i.e., the segmented current data. This data will be used for subsequent cable diameter selection and bundle design to ensure that the cable network can meet the current requirements of each segmented path, while avoiding safety issues such as overload and overheating.

[0041] In an optional embodiment of the present invention, step 15 may include: Step 151: Obtain rocket performance data, which includes electrical design data and internal environment data; Step 152: Determine the base wire diameter data based on the electrical design data and the segmented current data; Step 153: Perform voltage correction on the basic wire diameter data to obtain wire diameter data after voltage drop compensation; Step 154: Perform environmental correction on the voltage drop compensated wire diameter data to obtain environmentally corrected wire diameter data; Step 155: Perform safety margin compensation processing on the environmentally corrected wire diameter data to obtain the wire diameter data of the cable network.

[0042] In this embodiment, the first step is to collect rocket performance data, which forms the basis for determining the cable network diameter. Rocket performance data mainly includes electrical design data and internal environment data. Electrical design data involves the overall architecture of the rocket's electrical system, power distribution, load requirements, etc.; internal environment data includes the temperature range, humidity conditions, vibration characteristics, and electromagnetic environment inside the rocket. This data will provide key inputs for subsequent cable diameter calculations, ensuring that the cable can work stably in various environments inside the rocket.

[0043] In step 152, after obtaining the electrical design data and segmented current data, the basic cable diameter can be determined based on this data. The calculation of the basic cable diameter is based on the current carrying capacity and the physical properties of the cable material. For example, the required basic cable diameter can be calculated based on the segmented current data, using the following formula: ; in, D base To determine the base wire diameter data, I max This is the instrument's maximum operating current. L For cable length, Δ V To allow for voltage drop, it is typically 5% of the rated voltage. p The resistivity of the conductor; The basic wire diameter is the starting point for cable design, and subsequent steps will be based on this for further correction and compensation.

[0044] In step 153, a voltage drop occurs when the cable transmits current, which may cause the voltage at the cable end to be lower than the required value, affecting the normal operation of the equipment. Therefore, voltage correction is needed based on the basic wire diameter data to compensate for the voltage drop. Voltage correction is usually calculated based on factors such as cable length, current magnitude, and resistivity of the cable material, and can be specifically expressed as follows: ; ; Where, Δ V j For the firstj Segmented voltage drop, I j For the first j Total current in segments L j For the first j Segment length, p For conductor resistivity, A base Based on the cross-sectional area of ​​the baseline, K ΔVj For the voltage drop equal to Δ V j Voltage correction factor at time, D compensation This is the wire diameter data after voltage drop compensation; through voltage correction, the wire diameter data after voltage drop compensation can be obtained, and this data is closer to the minimum wire diameter required for actual cables.

[0045] In step 154, the environmental conditions inside the rocket (such as temperature, humidity, vibration, etc.) may affect the performance of the cable; therefore, based on the wire diameter data after voltage drop compensation, environmental correction is also required. Environmental correction typically considers the extreme conditions of the rocket's internal environment, such as the highest temperature, lowest temperature, and maximum vibration amplitude, as well as the impact of these conditions on the cable material performance. The specific formula is as follows: ; in, D env This is the wire diameter data after environmental correction. K temp This is the temperature compensation coefficient. K vib This is the vibration compensation coefficient; By adjusting the environmental parameters, we can obtain the corrected wire diameter data, which is more in line with the actual requirements of the rocket's internal environment.

[0046] In step 155, to ensure the safety and reliability of the cable, a certain safety margin is usually added to the calculated wire diameter. The safety margin compensation takes into account various uncertainties that the cable may encounter during long-term use, such as material aging, load fluctuations, and environmental changes. The specific formula is as follows: ; in, D safety For cable network wire diameter data, K safety The safety margin required by aerospace industry standards is generally taken as 0.2. By applying safety margin compensation, the final cable network diameter data can be obtained. This data not only meets the requirements of the rocket's electrical system but also takes into account the uncertainties and safety requirements in actual engineering.

[0047] In an optional embodiment of the present invention, step 16 may include: Step 161: Based on the compartment layout data, divide the cable network wire diameter data according to the compartment to obtain the first bundle group data; Step 162: Perform intra-beam diameter compatibility verification on the initial bundle data to obtain the second bundle data; Step 163, according to: Determine the equivalent diameter of the cable bundle; in, D bundle The equivalent diameter of the cable bundle d i For the first i The diameter of the cable, 1≤ i ≤n, n This refers to the number of cables in the second bundle. K 1 represents the bundling redundancy coefficient. K 2 represents the sheath thickness margin; Step 164: Determine the sheath material data based on the second bundle data; Step 165: Determine the rocket cable bundle data based on the sheath material data and the equivalent diameter of the cable bundle.

[0048] In this embodiment, the cable network diameter data is first divided according to the different sections of the rocket based on the section layout data. By dividing by section, a set of cable network diameter data for each section can be obtained, namely the first bundle data. This step ensures that the cables in each section can be designed according to their specific space and environmental requirements.

[0049] In steps 162 and 163, after obtaining the data for the first bundle, a compatibility check needs to be performed on the cable diameter within each bundle. The purpose of the compatibility check is to ensure that the cable diameters within the bundle do not interfere with each other and can meet the current and signal transmission requirements of all electrical instruments in the compartment. During the check, factors such as cable bending radius, electromagnetic compatibility, and heat dissipation conditions need to be considered. Through the check, cable diameters that do not meet the requirements are adjusted or replaced to obtain the data for the second bundle. Then, according to the formula: ; To determine the equivalent diameter of the cable bundle; where, K 1 is the bundling redundancy factor, used to account for the actual dimensional changes of the cable bundle during assembly and fixing, and is generally taken as 1.2; K2 represents the sheath thickness margin, used to compensate for the thickness of the cable insulation and sheath layers, and is generally taken as 0.3. Through the above formula, the equivalent diameter of each cable bundle can be obtained, and this data will be used for subsequent sheath material selection and bundle design.

[0050] In step 164, after obtaining the second bundle data, the sheath material needs to be determined based on this data. The selection of the sheath material needs to consider the internal environmental conditions of the rocket, such as temperature, humidity, vibration, and electromagnetic interference. Different sheath materials have different physical and chemical properties, such as high temperature resistance, low temperature resistance, vibration resistance, and electromagnetic shielding. According to the cable diameter, quantity, and environmental requirements of the compartment in the second bundle data, a suitable sheath material is selected to ensure the safety and reliability of the cable during rocket launch and flight. For example, the environmental coefficient corresponding to the maximum cable diameter in the second bundle data can be used to match the sheath material. The matching relationship between the environmental coefficient and the sheath material is shown in Table 1.

[0051] Table 1. Matching Relationship between Environmental Factors and Sheath Materials

[0052] In step 165, the final rocket cable bundle data is determined by combining the sheath material data and the equivalent diameter of the cable bundle. The rocket cable bundle data includes detailed information for each bundle, such as bundle number, section, cable diameter, quantity, sheath material type, and equivalent diameter. This data will be used to guide the actual production and installation of the cables, ensuring that the cables can be bundled and arranged according to the design requirements.

[0053] A specific embodiment of the data processing method for cable network splitting in a launch vehicle provided by this invention is as follows: Step 1: Obtain the theoretical external shape and module layout diagram of the launch vehicle.

[0054] Defining the shape of the launch vehicle and the layout of its various sections provides a basic reference for subsequent cable network design.

[0055] External Design Drawings: Launch vehicle external design drawings typically include the rocket's dimensions, surface shape, and the relative positions of different components. They provide the overall spatial structure of the rocket (diameter variations, section lengths, and locations of critical components), defining the boundaries of the main cable routes (e.g., extending along the rocket's axial direction). These drawings need to clearly show the positional relationships of all rocket sections and components. Through external design drawings, the rocket's structural characteristics and spatial layout can be clearly understood, providing a framework for the design of the cable network.

[0056] Module Layout Diagram: Based on the rocket's external design, the module layout diagram details the internal structure, functional zones, and installation points of each module. It clearly defines the internal structure of each module (instrument mounting points, structural supports, and piping / fuel tank locations), providing microscopic constraints to keep the main pipeline away from high-risk areas (such as high-temperature / high-frequency vibration sources). Each module has a different function, such as the core first stage, core second stage, and payload compartment. The module layout diagram is fundamental to ensuring that the electrical connections between modules are reasonable and do not interfere with each other.

[0057] Step 2: Determine the layout direction of the main cables of the cable network.

[0058] Determine the main cable network layout to ensure uninterrupted power and signal transmission.

[0059] Cable backbone design: The cable backbone is the core component for transmitting power and signals, and its layout must take into account the rocket's structure, flight performance, and safety. The backbone is typically laid out along the rocket's centerline, major structural components between modules, or a predetermined fixed path.

[0060] Path analysis: When planning the route, it is necessary to consider the vibration, temperature changes and other external factors during rocket launch and flight. The main line should avoid potentially dangerous areas (such as fuel, liquid pipelines, etc.) and avoid electromagnetic interference with other systems.

[0061] Backbone routing: The backbone network layout should be as simple as possible, avoiding excessive bends or complex paths to reduce power loss and improve transmission efficiency. Specific implementation steps include: (1) Extract key constraint information; External shape analysis: Determine the rocket's axial centerline as the baseline path for the main power line (shortest distance, minimum curvature). Identify the docking surfaces of the modules and plan the penetration points (adapter opening locations) for cross-module cables.

[0062] Compartment layout analysis: Mark prohibited areas (high-temperature zone near engine nozzles, fuel tanks). Mark usable anchor points (bulwark mounting brackets, structural longitudinal beams).

[0063] (2) Main route planning; The planning principles and implementation methods are as follows: Shortest path: Arrange along the rocket's central axis to reduce redundant length (optimal path calculated based on axial dimensions in the external shape drawing). Avoid high-risk areas: Based on the equipment distribution in the layout drawing, bypass fuel lines and high-temperature components (maintaining a safety distance of ≥50mm). Structural dependency: Main trunk lines are bound to the longitudinal beams or stiffeners of the compartments (mechanical stability ensured by structural annotations in the layout drawing). Electromagnetic compatibility: Maintain a parallel distance of ≥30cm from high-power equipment (such as servo mechanisms), and pass perpendicularly when crossing (requires coordinates from the layout drawing).

[0064] (3) Dynamic adjustment verification; Conflict detection: Overlay the main route onto the compartment layout diagram to check for conflicts with existing equipment and pipeline spaces (using 3D modeling software for collision detection).

[0065] Environmental adaptability verification: Simulate the launch vibration spectrum to ensure that the spacing between the main line fixed points is ≤1m (the load-bearing structure of the fixed points needs to be marked in the layout diagram).

[0066] Step 3: Perform statistics on the onboard electrical instruments and analyze their overcurrent capacity according to the compartment layout.

[0067] By statistically analyzing the current-carrying capacity of various electrical instruments within the compartment, we ensure that the cable network can meet the load requirements and avoid overload.

[0068] Electrical instrument statistics: Statistics are compiled on the electrical instruments, control systems, sensors, etc. installed in each compartment to clarify their power requirements, operating current, and transmission signal characteristics.

[0069] Overcurrent Capacity Analysis: Based on the statistical analysis of electrical instruments, it is necessary to analyze the overcurrent capacity of cables. Overcurrent capacity refers to the maximum current a cable can withstand for a short period of time. By calculating the power requirements of each electrical instrument and cable, the required current can be analyzed, and thus the rated current of the cable can be determined.

[0070] Load balancing: The load balancing design is carried out according to the power requirements of electrical instruments to avoid overload of certain parts of the cable and ensure the safety and stability of the power system.

[0071] Step 4: Determine the wire diameter for different types of cable networks based on the analysis results.

[0072] Based on the power requirements of electrical instruments and the results of overcurrent analysis, determine the cable specifications and wire diameter to ensure safe and efficient power transmission.

[0073] Cable specification selection: Select the appropriate cable specification and diameter based on the power and required current of the electrical instruments in each compartment. The cable diameter is usually determined by the current carrying capacity and cable length. An excessively large diameter may result in unnecessary weight and volume, while an excessively small diameter may lead to overload and safety hazards.

[0074] Step 5, cable network bundle design.

[0075] Based on the main cable network design, cable type, wire diameter, and other information, complete the cable network bundle design and finally determine the cable layout.

[0076] Cable Bundle Design: Within rocket modules, cables are typically bundled into multiple smaller cable networks to accommodate the needs of different modules. Cable bundle design requires careful consideration of cable layout to avoid issues such as crossings, overlaps, or unreasonable routing.

[0077] Cable bundle protection: The design of the cable bundle must take into account environmental factors such as temperature, humidity, and vibration inside the rocket. Appropriate sheath materials need to be selected to protect the cables and ensure they are not damaged by external factors during flight.

[0078] The method for processing bundled data of launch vehicle cable networks proposed in this invention can achieve the following technical effects: (1) Improved design efficiency and accuracy. During the design phase, a comprehensive analysis of instrument distribution and cable wiring ensured the efficient and safe distribution of the cable network, avoiding design oversights and inefficiencies in traditional methods, and improving the overall design efficiency and accuracy. (2) The assembly process is simplified. Through intelligent optimization and dynamic adjustment, the cable network layout is made more modular and standardized, thereby simplifying the rocket assembly work. Traditional designs usually lack dynamic adjustment capabilities. Once the design requirements change, it is easy to cause design incompatibility or rework. This invention, through flexible beam splitting scheme and adaptive design, can adapt to the needs of other system changes during the rocket design process, reducing the amount of rework and cost caused by design adjustments.

[0079] like Figure 2 As shown, this embodiment of the invention also provides a launch vehicle cable network bundle data processing device 20, comprising: Module 21 is used to acquire rocket shape data and compartment layout data; Processing module 22 is used to analyze and process the rocket shape data and the compartment layout data to obtain spatial constraint data; determine the main trunk line path based on the spatial constraint data; determine the segment current data based on the compartment layout data and the main trunk line path; and determine the rocket cable bundle data based on the segment current data. The determination module 23 is used to determine the rocket cable bundle data based on the compartment layout data and the cable network diameter data.

[0080] Optionally, module 21 is specifically used for: The rocket's design model is analyzed to obtain rocket shape data and compartment layout data. The rocket shape data includes at least one of diameter variation, compartment length, and compartment docking surface position. The compartment layout data includes at least one of internal space range, high-risk area range, cable fixing structure position, and instrument information.

[0081] Optionally, processing module 22 is specifically used for: The rocket's external shape data is identified to determine the axial baseline and the location of the docking surfaces of the modules; Based on the axial reference line, determine the axial centerline coordinate sequence; Based on the location of the docking surface of the compartment, determine the coordinate set of the docking surface of the compartment; The compartment layout data is identified to determine the internal space range, high-risk area range, cable fixing structure location, and instrument information; Based on the scope of the high-risk area, a set of prohibited passage zones is determined; Based on the location of the cable fixing structure, determine the set of cable fixing points; Based on the instrument information, determine the location data and safety distance data of the electromagnetically sensitive equipment; The internal space range is discretized according to a preset value to determine multiple grid units; Based on the axial centerline coordinate sequence, the set of docking surface coordinates of the compartments, the set of prohibited passage areas, the set of cable fixing points, the location data of the electromagnetically sensitive equipment, and the safety distance data, the multiple grid cells are labeled to obtain spatial constraint data.

[0082] Optionally, the processing module 22 is also specifically used for: Based on the spatial constraint data, the axial centerline coordinate sequence is traversed to obtain an initial path set; The initial path set is smoothed to obtain a smoothed initial path set; The smoothed initial path set and the spatial constraint data are processed by the path optimization model to obtain the trunk path.

[0083] Optionally, the processing module 22 is also specifically used for: The instrument information in the compartment layout data is traversed to obtain an instrument database, which includes parameter information of multiple instruments. Based on the parameter information of multiple instruments in the instrument database, the effective current of multiple instruments is calculated to obtain the instrument effective current set; The main route is segmented at preset intervals to obtain multiple segmented routes; The multiple segmented paths and the effective current set of the instrument are mapped to obtain segmented current data.

[0084] Optionally, the processing module 22 is also specifically used for: Acquire rocket performance data, which includes electrical design data and internal environment data; Based on the electrical design data and the segmented current data, determine the base wire diameter data; Voltage correction is applied to the basic wire diameter data to obtain wire diameter data after voltage drop compensation; Environmental correction is applied to the voltage drop compensated wire diameter data to obtain environmentally corrected wire diameter data. The wire diameter data after environmental correction is processed to obtain the wire diameter data of the cable network.

[0085] Optionally, module 23 is specifically used for Based on the compartment layout data, the cable network diameter data is divided according to the compartment to obtain the first bundle group data; The initial bundle data is subjected to bundle diameter compatibility verification to obtain the second bundle data; According to: Determine the equivalent diameter of the cable bundle; in, D bundle The equivalent diameter of the cable bundle d i For the first i The diameter of the cable, 1≤ i ≤n, n This refers to the number of cables in the second bundle. K 1 represents the bundling redundancy coefficient. K 2 represents the sheath thickness margin; Based on the data from the second bundle, determine the sheath material data; Based on the sheath material data and the equivalent diameter of the cable bundle, the rocket cable bundle data is determined.

[0086] 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.

[0087] like Figure 3 As shown, this embodiment of the invention also provides a computing device 30, including a processor 31, a memory 32, and a program or instructions stored in the memory 32 and executable on the processor 31. When executed by the processor 31, the program or instructions implement the various processes of the above-described embodiment of the carrier rocket cable network bundle data processing method and achieve the same technical effect. To avoid repetition, further details are omitted here. It should be noted that the computing device in this embodiment includes the aforementioned mobile electronic devices and non-mobile electronic devices.

[0088] 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.

[0089] 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.

[0090] 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.

[0091] 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.

[0092] 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.

[0093] 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.

[0094] 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.

[0095] 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.

[0096] 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 bundled data of a launch vehicle cable network, characterized in that, include: Acquire rocket shape data and compartment layout data; The rocket's external shape data and the compartment layout data are analyzed and processed to obtain spatial constraint data; Based on the spatial constraint data, determine the main route; Based on the compartment layout data and the main line path, determine the segment current data; Based on the segmented current data, determine the cable network wire diameter data; Based on the compartment layout data and the cable network diameter data, the rocket cable bundle data is determined.

2. The method for processing bundled data of launch vehicle cable networks according to claim 1, characterized in that, Obtain rocket shape data and compartment layout data, including: The rocket's design model is analyzed to obtain rocket shape data and compartment layout data. The rocket shape data includes at least one of diameter variation, compartment length, and compartment docking surface position. The compartment layout data includes at least one of internal space range, high-risk area range, cable fixing structure position, and instrument information.

3. The method for processing bundled data of launch vehicle cable networks according to claim 1, characterized in that, The rocket's external shape data and the compartment layout data are analyzed and processed to obtain spatial constraint data, including: The rocket's external shape data is identified to determine the axial baseline and the location of the docking surfaces of the modules; Based on the axial reference line, determine the axial centerline coordinate sequence; Based on the location of the docking surface of the compartment, determine the coordinate set of the docking surface of the compartment; The compartment layout data is identified to determine the internal space range, high-risk area range, cable fixing structure location, and instrument information; Based on the scope of the high-risk area, a set of prohibited passage zones is determined; Based on the location of the cable fixing structure, determine the set of cable fixing points; Based on the instrument information, determine the location data and safety distance data of the electromagnetically sensitive equipment; The internal space range is discretized according to a preset value to determine multiple grid units; Based on the axial centerline coordinate sequence, the set of docking surface coordinates of the compartments, the set of prohibited passage areas, the set of cable fixing points, the location data of the electromagnetically sensitive equipment, and the safety distance data, the multiple grid cells are labeled to obtain spatial constraint data.

4. The method for processing bundled data of launch vehicle cable networks according to claim 3, characterized in that, Based on the spatial constraint data, the main route is determined, including: Based on the spatial constraint data, the axial centerline coordinate sequence is traversed to obtain an initial path set; The initial path set is smoothed to obtain a smoothed initial path set; The smoothed initial path set and the spatial constraint data are processed by the path optimization model to obtain the trunk path.

5. The method for processing bundled data of launch vehicle cable networks according to claim 3, characterized in that, Based on the compartment layout data and the main trunk route, segmented current data are determined, including: The instrument information in the compartment layout data is traversed to obtain an instrument database, which includes parameter information of multiple instruments. Based on the parameter information of multiple instruments in the instrument database, the effective current of multiple instruments is calculated to obtain the instrument effective current set; The main route is segmented at preset intervals to obtain multiple segmented routes; The multiple segmented paths and the effective current set of the instrument are mapped to obtain segmented current data.

6. The method for processing bundled data of launch vehicle cable networks according to claim 1, characterized in that, Based on the segmented current data, the wire diameter data of the cable network is determined, including: Acquire rocket performance data, which includes electrical design data and internal environment data; Based on the electrical design data and the segmented current data, determine the base wire diameter data; Voltage correction is applied to the basic wire diameter data to obtain wire diameter data after voltage drop compensation; Environmental correction is applied to the voltage drop compensated wire diameter data to obtain environmentally corrected wire diameter data. The wire diameter data after environmental correction is processed to obtain the wire diameter data of the cable network.

7. The method for processing bundled data of launch vehicle cable networks according to claim 1, characterized in that, Based on the module layout data and the cable network diameter data, the rocket cable bundle data is determined, including: Based on the compartment layout data, the cable network diameter data is divided according to the compartment to obtain the first bundle group data; The initial bundle data is subjected to bundle diameter compatibility verification to obtain the second bundle data; according to: Determine the equivalent diameter of the cable bundle; in, D bundle The equivalent diameter of the cable bundle d i For the first i The diameter of the cable, 1≤ i ≤n, n This refers to the number of cables in the second bundle. K 1 represents the bundling redundancy coefficient. K 2 represents the sheath thickness margin; Based on the data from the second bundle, determine the sheath material data; Based on the sheath material data and the equivalent diameter of the cable bundle, the rocket cable bundle data is determined.

8. A data processing device for cable network bundling in a launch vehicle, characterized in that, include: The acquisition module is used to acquire rocket shape data and compartment layout data; The processing module is used to parse and process the rocket's external shape data and the compartment layout data to obtain spatial constraint data; determine the main trunk line path based on the spatial constraint data; determine the segment current data based on the compartment layout data and the main trunk line path; and determine the rocket cable bundle data based on the segment current data. The determination module is used to determine the rocket cable bundle data based on the compartment layout data and the cable network diameter 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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