Generation method, device and equipment for arrangement diagram of electrical instruments of carrier rocket

Abstract

The embodiment of the invention provides a method, a device and equipment for generating an electrical instrument arrangement diagram of a carrier rocket. The method comprises the following steps: acquiring characteristic parameters of electrical instruments required by the carrier rocket; determining a digital electrical instrument corresponding to the required electrical instrument according to the characteristic parameters; generating an electrical instrument arrangement diagram of the carrier rocket according to the digital electrical instrument and a preset digital carrier rocket basis; according to the electrical instrument arrangement diagram, obtaining an inspection result of the electrical instrument arrangement diagram; determining a target rule from preset rules in a preset rule base according to the feature parameters; according to the target rule and the inspection result, adjusting the electrical instrument arrangement diagram to enable the inspection result to accord with the target rule, and obtaining a target electrical instrument arrangement diagram; the construction process of the preset rule base comprises the following steps: acquiring the arrangement specification of the electrical instrument of the carrier rocket; converting the arrangement specification into a preset rule; and storing the preset rule in a preset rule base. According to the embodiment of the invention, digital automatic design verification can be realized.

Description

TECHNICAL FIELD

[0001] The embodiment of the present application relates to the field of launch vehicle control, in particular to a launch vehicle electrical instrument layout generation method, device and equipment. BACKGROUND

[0002] In the field of launch vehicle overall design, the electrical instrument layout design is a key link connecting the electrical system design and the vehicle assembly production. The design quality directly affects the reliability, safety, test maintenance and lightweight level of the rocket.

[0003] In the traditional process, the overall layout, structure design and electrical system design are often performed in series. The electrical designer starts the device placement and cable routing design after the structure layout is basically finalized, which often leads to problems such as insufficient space and serious interference, resulting in a large amount of design rework and coordination cost, and prolonging the design cycle.

[0004] A large amount of information transmission and collaborative design is dependent on two-dimensional drawings, which has inherent defects such as non-intuitive information, errors, omissions, collisions and lack between different professional drawings, and is difficult to find. For complex three-dimensional space layout and cable laying, the expression and checking capabilities of two-dimensional drawings are very limited.

[0005] The layout design is heavily dependent on the personal experience of the designer, and lacks systematic and digital design criteria and specification library support. The quality of designs by different personnel varies greatly, making it difficult to ensure the consistency and optimality of the design.

[0006] Design problems are often not discovered until the manufacturing or assembly stage, such as insufficient device installation space, cable laying problems, insufficient operation space, etc., at which point the modification cost is extremely high.

[0007] Currently, three-dimensional digital design software has been adopted in the aerospace field for electrical layout design, realizing the transition from two-dimensional to three-dimensional. However, there are still cases of component interference in the electrical instrument layout of the launch vehicle, resulting in quality defects, and the need for manual secondary conversion, which is prone to errors and low efficiency. SUMMARY

[0008] The technical problem to be solved by the embodiment of the present application is to provide a launch vehicle electrical instrument layout generation method, device and equipment, which can realize digital and automatic design verification, improve quality and efficiency, reduce cost and error, and strengthen collaboration and reuse.

[0009] To solve the above technical problems, the technical solution of the embodiment of the present application is as follows: A launch vehicle electrical instrument layout generation method, comprising: obtaining characteristic parameters of required electrical instruments of the launch vehicle; determine a digital electrical instrument corresponding to the required electrical instrument according to the characteristic parameter; generate an electrical instrument layout of the launch vehicle according to the digital electrical instrument and a preset digital launch vehicle base; obtain an inspection result of the electrical instrument layout according to the electrical instrument layout; determine a target rule from preset rules in a preset rule library according to the characteristic parameter; adjust the electrical instrument layout according to the target rule and the inspection result, so that the inspection result meets the target rule, and obtain a target electrical instrument layout; output the target electrical instrument layout; The construction process of the preset rule library comprises: obtaining a layout specification of electrical instruments of a launch vehicle; converting the layout specification into a preset rule; and storing the preset rule into a preset rule library.

[0010] Optionally, converting the layout specification into a preset rule comprises: The preset rule comprises a rule type, an applicable scenario, and a parameter threshold.

[0011] Optionally, determining a digital electrical instrument corresponding to the required electrical instrument according to the characteristic parameter comprises: matching a digital electrical instrument consistent with the characteristic parameter from a preset electrical equipment standard library, the characteristic parameter comprising a size, a weight, an interface type, a power consumption, and an electromagnetic compatibility level of the electrical instrument.

[0012] Optionally, generating an electrical instrument layout of the launch vehicle according to the digital electrical instrument and a preset digital launch vehicle base comprises: placing the digital electrical instrument in the preset digital launch vehicle base according to a preset layout template to form a preliminary device layout; forming a cable path on the preliminary device layout according to a connection relationship of the required electrical instrument to generate an electrical instrument layout of the launch vehicle.

[0013] Optionally, obtaining an inspection result of the electrical instrument layout according to the electrical instrument layout comprises: performing full-model batch inspection on the electrical instrument layout to obtain an inspection result of the electrical instrument layout, the inspection result comprising interference between devices, interference between devices and structures, interference between cables and other objects, and electrical instrument layout spacing, cable bending radius, support natural frequency, and operation space.

[0014] Optionally, determining a target rule from preset rules in a preset rule library according to the characteristic parameter comprises: According to the size, weight, interface type in the characteristic parameters, a corresponding space layout rule and structure adaptation rule are matched from preset rules in a preset rule library; According to the power consumption and electromagnetic compatibility level in the characteristic parameters, a corresponding electromagnetic compatibility rule and thermal environment adaptability rule are matched from preset rules in a preset rule library; The space layout rule, structure adaptation rule, electromagnetic compatibility rule and thermal environment adaptability rule are taken as the target rule.

[0015] Optionally, according to the target rule and the check result, the electrical instrument layout is adjusted so that the check result meets the target rule, and a target electrical instrument layout is obtained, including: For an item in the check result that violates the target rule, a visual alarm is generated in the electrical instrument layout and a problem position is located; If there is a digital electrical instrument layout spacing problem, the placement position of a low-priority digital electrical instrument in a preset digital carrier rocket is preferentially adjusted; if adjusting a single digital electrical instrument cannot meet the requirement, the layout of multiple digital electrical instruments in the region is re-planned until the spacing meets the target rule; If there is a cable bending radius problem, the cable bending curvature is preferentially increased; if increasing the cable bending curvature cannot meet the requirement, the cable path in the region is re-planned to ensure that the cable bending radius meets the target rule; If there is a bracket natural frequency problem, the structure parameters of the bracket are adjusted or the bracket material is replaced, the bracket natural frequency is re-calculated, and the target rule is met until the target rule is met; If there is an operation space problem or an interference problem, the installation position of related equipment is adjusted, the cable path is optimized, or the local structure is modified until the problem is solved; After the adjustment is completed, the check process is re-executed on the adjusted electrical instrument layout; if there is still an item that violates the target rule, the above adjustment steps are repeated until all the check results meet the target rule; The electrical instrument layout in which all the check results meet the target rule is determined as the target electrical instrument layout.

[0016] The embodiment of the application also provides an electrical instrument layout generation device of a carrier rocket, including: An acquisition module is configured to acquire characteristic parameters of required electrical instruments of a carrier rocket; The processing module is configured to: determine a digital electrical instrument corresponding to the required electrical instrument according to the characteristic parameter; generate an electrical instrument layout of the carrier rocket according to the digital electrical instrument and a preset digital carrier rocket foundation; obtain an inspection result of the electrical instrument layout according to the electrical instrument layout; determine a target rule from preset rules in a preset rule library according to the characteristic parameter; adjust the electrical instrument layout according to the target rule and the inspection result, so that the inspection result meets the target rule, and obtain a target electrical instrument layout; and output the target electrical instrument layout; wherein the preset rule library is constructed by: obtaining an arrangement specification of the electrical instrument of the carrier rocket; converting the arrangement specification into a preset rule; and storing the preset rule into the preset rule library.

[0017] Embodiments of the application also provide a computing device, comprising: one or more processors; a storage device configured to store one or more programs, which, when executed by the one or more processors, cause the one or more processors to implement the method described above.

[0018] Embodiments of the application also provide a computing device readable storage medium, which stores a program that, when executed by a processor, implements the method described above.

[0019] The above scheme of the embodiments of the application has at least the following beneficial effects: The above scheme of the embodiments of the application combines the digital electrical instrument with the preset digital rocket foundation, realizes multi-specialty parallel design, avoids problems such as insufficient space and interference caused by electrical design after structure is finalized, reduces rework and coordination costs, and shortens the cycle.

[0020] Based on the three-dimensional digital generation of the layout, automatic inspection and adjustment are performed in cooperation with the preset rule library, problems such as difficult discovery of non-intuitive, missing, and collision of two-dimensional drawing information are solved, and the expression and inspection capability of complex layout is improved.

[0021] With the preset rule converted from the arrangement specification as support, the dependence on personal experience of the designer is reduced, the design consistency and optimality are ensured, and the quality fluctuation caused by personnel difference is reduced.

[0022] Problems such as installation and cable laying are discovered in the design stage through rule checking, so that the problems are avoided to be left to the manufacturing or assembly stage, the modification cost is greatly reduced, and the multi-specialty collaboration and knowledge reuse capability are enhanced. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is a flowchart of a method for generating an electrical instrument layout of a carrier rocket provided by an embodiment of the application.

[0024] Figure 2 is a module schematic diagram of a generation device of an electrical instrument layout of a launch vehicle provided by an embodiment of the present application. DETAILED DESCRIPTION

[0025] Exemplary embodiments of the present application will be described in greater detail below with reference to the accompanying drawings. Although exemplary embodiments of the present application are shown in the drawings, it is understood that the present application can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present application can be more thoroughly understood, and the scope of the present application can be accurately conveyed to those skilled in the art.

[0026] As Figure 1 shown, an embodiment of the present application provides a generation method of an electrical instrument layout of a launch vehicle, comprising: Step 11, obtaining characteristic parameters of required electrical instruments of a launch vehicle; Step 12, determining corresponding digital electrical instruments of the required electrical instruments according to the characteristic parameters; Step 13, generating an electrical instrument layout of a launch vehicle according to the digital electrical instruments and a preset digital launch vehicle foundation; Step 14, obtaining an inspection result of the electrical instrument layout according to the electrical instrument layout; Step 15, determining a target rule from preset rules in a preset rule library according to the characteristic parameters; Step 16, adjusting the electrical instrument layout according to the target rule and the inspection result, so that the inspection result conforms to the target rule, to obtain a target electrical instrument layout; Step 17, outputting the target electrical instrument layout; Wherein, the construction process of the preset rule library comprises: Step 101, obtaining a layout specification of electrical instruments of a launch vehicle; Step 102, converting the layout specification into a preset rule; Step 103, storing the preset rule into a preset rule library.

[0027] In this embodiment, digital electrical instruments are combined with a preset digital launch vehicle foundation to realize multi-specialty parallel design, avoid problems such as insufficient space and interference caused by electrical design after structure is finalized, reduce rework and coordination costs, and shorten the cycle.

[0028] Based on three-dimensional digital generation of the layout, automatic inspection and adjustment are performed with the preset rule library to solve the problem of difficult discovery of information not intuitive, errors, omissions, and collisions in two-dimensional drawings, and to improve the expression and inspection capability of complex layout.

[0029] With the support of preset rules converted from the arrangement specification, the dependence on the personal experience of the designer is reduced, the design consistency and optimality are ensured, and the quality fluctuation caused by personnel differences is reduced.

[0030] In the design stage, problems such as installation and cable laying are found through rule checking, so that the problems are avoided to be left to the manufacturing or assembly stage, the modification cost is greatly reduced, and the multi-specialty collaboration and knowledge reuse capability are enhanced.

[0031] In an optional embodiment of the present application, in step 101, the arrangement specification of the electrical instrument of the launch vehicle is acquired.

[0032] Specifically, the full-quantity specification related to the electrical instrument arrangement of the launch vehicle can be collected by consulting public standards in the aerospace field, internal technical documents and historical design verification data of the enterprise; The public standards include aerospace industry standards (such as standards related to equipment installation and electromagnetic compatibility), the internal technical documents include process requirements for electrical instrument layout, cable laying guidelines and mechanical specifications for support design, and the historical design verification data includes problem rectification records of past rocket electrical arrangement and constraint conditions corresponding to qualified design cases.

[0033] In this embodiment, through multi-channel collection of public standards + internal documents + historical data, full-dimensional requirements such as equipment installation, electromagnetic compatibility and cable laying are covered, and there is no specification blind area. The public standards ensure authority, the internal documents are suitable for production, the historical data incorporate experience and lessons, the specification is ensured to have authority and operability, and the design and production deviation is reduced. Complete input is provided for step 102 specification rule conversion, rule loopholes are avoided, and the design material searching and coordination cost is reduced, thereby indirectly shortening the cycle.

[0034] In an optional embodiment of the present application, in step 102, the arrangement specification is converted into preset rules, which include: In step 1021, the arrangement specification is converted into preset rules, and the preset rules include: rule type, applicable scene and parameter threshold.

[0035] Specifically, the collected text type arrangement specification can be disassembled and quantified: For electromagnetic compatibility type specification, it is disassembled into spacing rules, the applicable scene is sensitive equipment and interference source equipment, and the parameter threshold is set to spacing> 500mm combined with engineering verification data; For cable laying type specification, it is disassembled into bending radius rules, the applicable scene is all cable bundle laying, and the parameter threshold is set to bending radius> 5 times cable diameter according to the characteristics of cable material and diameter; For the support mechanical specification, it is disassembled into frequency rules, and the applicable scene is all equipment installation support, and the parameter threshold is set as first order natural frequency > 100Hz according to the rocket vibration environment requirement; For the operation and maintenance specification, it is disassembled into operation space rules, and the applicable scene is the peripheral area of the equipment maintenance interface, and the parameter threshold is set as operation space > 300mm. Meanwhile, a unique rule identifier is allocated to each preset rule.

[0036] In the embodiment, the text arrangement specification is disassembled into structured preset rules containing rule type, applicable scene and parameter threshold, for example, the qualitative requirement of electromagnetic compatibility is converted into the quantitative standard of distance > 500mm, so that the problems that the traditional text specification is difficult to be recognized by the computer system and cannot be automatically executed are solved, and the foundation is laid for subsequent automatic design checking.

[0037] According to the specification type, the disassembly is classified (electromagnetic-distance rule, cable-bending radius rule, etc.), and a unique identifier is allocated to the rule, so that different designers can call unified rules, design inconsistencies caused by individual differences in understanding the text specification are avoided, and the standardization level of electrical instrument arrangement is improved.

[0038] The parameter threshold is set in combination with engineering verification data, cable characteristics and rocket vibration environment (such as 5 times the cable diameter and 100Hz natural frequency), so that the rule meets the general specification requirement and is adapted to the actual working condition of the carrier rocket, excessive constraints or insufficient constraints are avoided, and the design quality and feasibility are ensured.

[0039] The design requirements (such as operation space and support frequency) scattered in the text specification are converted into clear rule modules, the conversion of design knowledge from implicit text to explicit rules is realized, the reuse and inheritance of knowledge are facilitated, and the dependence on personal experience of designers is reduced.

[0040] In an optional embodiment of the present application, in step 103, the preset rules are stored in a preset rule library.

[0041] Specifically, the rule type, applicable scene and parameter threshold in the preset rule are respectively stored in the rule basic information table, the applicable scene association table and the parameter threshold table in the preset rule library.

[0042] In this embodiment, the rules are stored according to type-scene-threshold, forming a clear rule data architecture. When calling rules in subsequent design (such as checking the distance between devices), the corresponding information in the table can be quickly located, avoiding query delay caused by rule data confusion. The separate and associated rule components (type, scene, threshold) can be accurately maintained for a single data item (such as updating the threshold) without affecting other components, while ensuring that all rule storage formats are uniform, avoiding rule execution deviation caused by storage confusion, and providing reliable data support for subsequent automated inspection.

[0043] In an optional embodiment of the present application, in step 11, the characteristic parameters of the required electrical instruments of the launch vehicle are obtained.

[0044] Specifically, the type and functional requirements of the required electrical instruments are imported from the overall design task book of the launch vehicle; the characteristic parameters of the corresponding instruments are extracted from the enterprise electrical equipment attribute database, including the size, weight, interface type, power consumption and electromagnetic compatibility level of the electrical instruments.

[0045] In this embodiment, the instrument type and functional requirements are imported from the overall design task book, which is consistent with the overall design goal of the rocket; the parameters are extracted from the enterprise equipment attribute database, and the data is verified by history to avoid manual input errors and ensure the accuracy and reliability of core parameters such as size and electromagnetic compatibility level. Covering key dimensions such as size, weight and interface, it provides complete basis for matching digital instruments in step 12 and lays a foundation for determining target rules such as electromagnetic compatibility and structure adaptation in step 15, avoiding design interruption or rework due to missing parameters, and improving design continuity and efficiency.

[0046] In an optional embodiment of the present application, in step 12, a digital electrical instrument corresponding to the required electrical instrument is determined according to the characteristic parameters, including: Step 121, matching the digital electrical instrument consistent with the characteristic parameters from the preset electrical equipment standard library, the characteristic parameters including: size, weight, interface type, power consumption and electromagnetic compatibility level of the electrical instrument.

[0047] Specifically, the preset electrical equipment standard library stores digital electrical instruments (parameterized three-dimensional models) of all mainstream electrical instruments, and each digital electrical instrument is associated with a complete attribute label. The characteristic parameters obtained in step 11 are compared with the model attribute label in the library: if the five parameters of size, weight, interface type, power consumption and electromagnetic compatibility level are completely consistent, the corresponding parameterized three-dimensional model is matched.

[0048] In this embodiment, by comparing five core parameters such as size and weight in full dimension, it is avoided that digital electrical instruments do not match the actual required electrical instruments due to missing or biased parameters, and it is ensured that subsequent layout design is consistent with the real equipment characteristics, and rework due to equipment adaptation problems in the later stage is reduced. Relying on the preset electrical equipment standard library, the parameterized three-dimensional model with consistent parameters is directly matched, without the need for designers to build the model from zero, which greatly shortens the preparation time of digital instruments and speeds up the overall progress of electrical instrument layout design. The matched digital electrical instruments contain complete attribute labels, which can be directly used for layout design in step 13 and rule checking in step 14 (such as judging sensitive equipment based on electromagnetic compatibility level), to ensure data continuity in each link of design and avoid affecting collaborative design and automatic verification effect due to missing digital instrument attributes.

[0049] In an optional embodiment of the present application, in step 13, an electrical instrument layout of a launch vehicle is generated according to the digital electrical instruments and a preset digital launch vehicle base, comprising: In step 131, the digital electrical instruments are placed in the preset digital launch vehicle base according to a preset layout template to form a preliminary equipment layout. Specifically, the preset digital launch vehicle base is a three-dimensional digital prototype of a launch vehicle, which contains complete three-dimensional data such as body structure (such as cabin section, stringer, support mounting interface) and equipment mounting constraint area (such as forbidden installation area, preferred installation area). The preset layout template contains verified layout scheme templates for different cabin sections (first stage tail end, first stage inter-bay section, two-oxygen rear short shell, instrument cabin, payload support) and functional areas (integrated electronic area, power supply area, telemetry area, external measurement area), and the digital electrical instruments determined in step 121 are placed in the preset positions according to the preset layout template. If there are special instruments not covered by the preset layout template, the designer manually adjusts the placement position, and at the same time, real-time prompts whether the equipment mounting interface is matched (such as whether the support aperture and the equipment mounting hole are consistent), and finally forms a preliminary equipment layout. In step 132, a cable path is formed on the preliminary equipment layout according to the connection relationship of the required electrical instruments to generate an electrical instrument layout of a launch vehicle. Specifically, the connection relationship of the required electrical instruments (such as signal connection between flight control computer and IMU, power connection between high-power power supply and sensor) is imported, and based on the three-dimensional space data of the preliminary equipment layout, a cable recommended path is generated: preferentially selecting the shortest path, avoiding equipment-intensive areas, and paths away from interference sources, for example, cables connecting IMU preferentially avoid the surrounding area of high-power power supply. The designer can manually optimize the recommended path through the three-dimensional view (such as dragging the path point to adjust the direction), and the system displays the cable length and bending condition in real time during the optimization process. After determining the final cable path, the system integrates the preliminary equipment layout and the final cable path, automatically adds label information such as equipment position number and cable identification, and generates a complete electrical instrument layout of a launch vehicle.

[0050] In this embodiment, relying on the three-dimensional digital mockup containing the complete missile body structure and the constraint area, combined with the verification template placement equipment of the divided cabin section and the divided function, the spatial conflict and the layout blindness are reduced; the interface matching is checked in real time during the manual adjustment of the special instrument, the installation adaptation problem is avoided, and the reliable preliminary layout is quickly formed.

[0051] The cable path is automatically generated according to the short path, the dense area is avoided, and the interference source is far away (such as avoiding the interference source around the IMU), the manual optimization is matched with the real-time display length and the bending condition, the efficiency and the compliance are considered, and the electromagnetic interference and the cable laying risk are reduced.

[0052] The equipment layout and the cable path are integrated, the label information is automatically added, the complete layout diagram is generated, the data fragmentation in each link is avoided, a unified and coherent design basis is provided for subsequent checking and adjustment, and the subsequent data completion and correction work is reduced.

[0053] In an optional embodiment of the present application, in step 14, an inspection result of the electrical instrument layout diagram is obtained according to the electrical instrument layout diagram, including: In step 141, a full-model batch inspection is performed on the electrical instrument layout diagram to obtain an inspection result of the electrical instrument layout diagram, and the inspection result includes: interference conditions between devices, devices, cables and other objects, and electrical instrument layout spacing, cable bending radius, support natural frequency and operation space.

[0054] Specifically, the interference condition inspection can call a three-dimensional collision detection algorithm to calculate the minimum spatial distance between devices, devices, cables and structures (such as cabin walls and stringers) in the electrical instrument layout diagram. If the distance is less than 5mm (a preset safety threshold), it is determined that there is interference, and the interference object label, interference position coordinates and interference distance are recorded; The electrical instrument layout spacing inspection can be performed according to to determine the electrical instrument layout spacing; wherein, d is the electrical instrument layout spacing, x 1, y 1, z 1) is a sensitive device coordinate, x 2, y 2, z 2) is an interference source device coordinate; The cable bending radius inspection can be performed according to to determine the cable bending radius; wherein, R is the cable bending radius, x 3, y 3,z 3), ( x 4, y 4, z 4), ( x 5, y 5, z 5) These are three adjacent path points along the cable path. L 1 is ( x 3, y 3, z 3), ( x 4, y 4, z 4) The distance between them (which can be calculated using the spacing formula above). L 2 is ( x 4, y 4, z 4), ( x 5, y 5, z 5) The distance between them θ for L 1 and L The included angle of 2; The stent's natural frequency can be checked according to Determine the natural frequency of the support; in, f For the inherent frequency of the support, E The elastic modulus of the support material. I Let the moment of inertia of the support section be , m For the quality of the support, L This refers to the support length of the bracket; The operating space check can be performed by checking whether the space within 300mm around the maintenance interface of the computing device is occupied by other objects.

[0055] In this embodiment, multiple key dimensions such as interference, spacing, and cable bending radius are covered, and each inspection item is quantitatively calculated based on algorithms or formulas (such as calculating interference using 3D collision detection and calculating spacing using coordinate formulas), avoiding subjective omissions and errors in manual inspection, ensuring that there are no blind spots in the problem and that the judgment is accurate. For example, standards such as a 5mm safety threshold and a 300mm operating space can be strictly implemented.

[0056] Problems such as equipment interference and non-standard spacing can be identified in batches during the design phase rather than the manufacturing or final assembly phase, thus avoiding the high costs of later rectification. For example, if the inherent frequency of the support is found to be non-compliant in advance, the structure can be adjusted directly in the 3D model without disassembling the physical rocket body.

[0057] The calculation logic of each check item (such as the bending radius formula and the natural frequency formula) can be automatically called by the system, without the need for repeated manual calculation, thereby improving the checking efficiency, ensuring the uniformity of the checking standards in different design scenarios, avoiding inconsistent judgments due to differences in personnel experience, and providing clear basis for accurate adjustment in the subsequent step 16.

[0058] The layout diagram is ensured to meet the core requirements of electromagnetic compatibility, mechanical vibration, operation and maintenance, such as sensitive equipment spacing and cable bending radius, which can reduce the risk of electromagnetic interference and cable damage, and ultimately improve the reliability and safety of the electrical system of the launch vehicle.

[0059] In an optional embodiment of the present application, in step 15, the target rule is determined from the pre-set rules in the pre-set rule library according to the characteristic parameters, including: In step 151, the corresponding spatial layout rule and structure adaptation rule are matched from the pre-set rules in the pre-set rule library according to the size, weight and interface type in the characteristic parameters; specifically, the size (such as equipment length, width and height > 500 mm) in the characteristic parameters is analyzed to determine that the equipment needs to occupy a large installation space, and the spatial layout rule (such as large equipment needs to be separately occupied on a support to avoid stacking with small equipment, and the parameter threshold is that the distance between the equipment and the surrounding small equipment > 200 mm) is matched from the pre-set rule library; the structure adaptation rule (such as equipment with a weight > 10 kg needs to be installed on a reinforced support, and the parameter threshold is that the bearing capacity of the support > 1.5 times the weight of the equipment) is matched according to the weight (such as equipment weight > 10 kg); and the interface layout rule (such as multi-interface equipment needs to reserve an interface operation space > 150 mm) is matched according to the interface type (such as equipment containing multiple aviation plug interfaces); In step 152, the corresponding electromagnetic compatibility rule and thermal environment adaptability rule are matched from the pre-set rules in the pre-set rule library according to the power consumption and electromagnetic compatibility level in the characteristic parameters; specifically, the thermal environment adaptability rule (such as equipment with a power consumption > 50 W needs to maintain a heat dissipation distance > 150 mm from other equipment to avoid heat accumulation) is matched from the pre-set rule library according to the power consumption (such as equipment power consumption > 50 W) to determine that the equipment is a high-heat equipment; the electromagnetic compatibility rule (such as the distance between a first-level sensitive equipment and all interference source equipment > 500 mm, and the cable connected to the first-level sensitive equipment needs to use a shielded cable) is matched according to the electromagnetic compatibility level (such as the equipment is marked as a first-level sensitive equipment); and the interference source constraint rule (such as a second-level interference source equipment needs to be kept away from an antenna area > 300 mm) is matched if the equipment is marked as a second-level interference source. Step 153, the space layout rule, structure adaptation rule, electromagnetic compatibility rule and thermal environment adaptability rule are taken as the target rule; specifically, the space layout rule matched in step 151, the structure adaptation rule, the electromagnetic compatibility rule matched in step 152 and the thermal environment adaptability rule are de-duplicated and prioritized: if different rules have parameter conflicts (for example, the space layout rule requires a distance > 200 mm, and the electromagnetic compatibility rule requires a distance > 500 mm), the rule with the stricter parameter is used as the reference (that is, the distance of 500 mm is used as the reference); at the same time, the rule priority is marked (for example, the electromagnetic compatibility rule priority > the space layout rule), and in subsequent adjustment, the high-priority rule is satisfied first; finally, the sorted rule set is determined as the target rule, and a target rule list (including rule label, parameter threshold and priority) is formed.

[0060] In this embodiment, the rules are matched based on feature parameters in different dimensions, such as matching the space layout and structure adaptation rules by size and weight, and matching the electromagnetic compatibility and thermal environment rules by power consumption and electromagnetic compatibility level, to ensure that the rules are highly consistent with the characteristics of the equipment, such as accurately matching the heat dissipation distance rule for high-heat equipment, avoiding the insufficient adaptation of general rules to special equipment, and making the target rules more targeted.

[0061] Through de-duplication and priority sorting (such as the electromagnetic compatibility rule being prior to the space layout rule, and the stricter value being taken in parameter conflicts), the contradictions between different rules are avoided to cause the design to be confused. For example, when the space layout requires a distance of 200 mm and the electromagnetic compatibility requires a distance of 500 mm, the 500 mm standard is used as the reference to ensure that the core constraints (such as electromagnetic safety) are not compromised, and the design meets the key performance requirements of the rocket.

[0062] The rule matching logic and parameter threshold are fixed (such as a weight > 10 kg using a reinforced support and a power consumption > 50 W leaving a heat dissipation distance of 150 mm), so that the designer does not need to screen the rules based on experience, reduces the deviation in the selection of rules caused by individual understanding differences, ensures that the determination logic of the target rules is uniform in different equipment and different design scenarios, and improves the standardization level of the electrical instrument layout.

[0063] The target rule list including the rule label, parameter threshold and priority is formed to make the adjustment direction of step 16 clear, such as preferentially solving the high-priority electromagnetic compatibility problem and then processing the ordinary-priority space layout problem, to avoid disordered adjustment and improve the problem solving efficiency, and at the same time, to ensure that the adjusted design fully meets all core constraints and lays a foundation for the compliance of the final target layout.

[0064] In an optional embodiment of the present application, in step 16, according to the target rule and the check result, the electrical instrument layout is adjusted so that the check result meets the target rule, and a target electrical instrument layout is obtained, which comprises: Step 161, for the items in the check results that violate the target rules, generate a visual alarm in the electrical instrument layout and locate the problem position; specifically, in the three-dimensional view of the electrical instrument layout, the problem items that violate the target rules are highlighted differently: interference problems are marked with a red solid box, spacing does not meet the standard is marked with a yellow dashed box, and bending radius does not meet the standard is marked with an orange line segment; at the same time, a pop-up window displays the problem details, including the target rule label violated, the rule requirement (spacing > 500mm), the current value (420mm), and the problem position coordinates (e.g. X =1500mm, Y =800mm, Z =2000mm), the designer can click the pop-up window to directly jump to the three-dimensional view of the problem position; Step 162, if there is a digital electrical instrument layout spacing problem, adjust the placement position of low-priority digital electrical instruments in the preset digital carrier rocket first; if adjusting a single digital electrical instrument cannot meet the requirements, re-plan the layout of multiple digital electrical instruments in the region until the spacing meets the target rules; specifically, first, retrieve the priority attributes of digital electrical instruments from the preset electrical equipment standard library (e.g., flight control computer, IMU as first priority, auxiliary sensor as third priority), and for the spacing problem (e.g., IMU and high-power power supply spacing 420mm < 500mm), adjust the position of the third priority auxiliary sensor first, release the space, and then recalculate the IMU and high-power power supply spacing; if the spacing is still not up to standard after adjustment, further adjust the second priority equipment (e.g., telemetry equipment); if a single device adjustment cannot meet the requirements, re-plan the layout of all devices in the cabin section, for example, move the high-power power supply to the other side of the cabin section to ensure that the IMU and high-power power supply spacing is ≥ 500mm, and after adjustment, verify the spacing through step 14; Step 163, if there is a cable bending radius problem, preferentially increase the cable bending radius, and if increasing the cable bending radius cannot meet the requirements, re-plan the cable path in the region to ensure that the cable bending radius meets the target rules; specifically, for the bending radius problem (e.g., cable bending radius R =20mm, target rule requires R >25mm, D =5mm), the designer drags the middle path point of the cable path (e.g., moves the path point away from the bending direction) in the three-dimensional view to increase the bending radius, and recalculates the bending radius (through the bending radius formula in step 141); if the path point is still not up to standard after dragging R >5 DIf the space is limited and cannot be moved, the original path is deleted, the cable path planning algorithm is called again, a new path around the edge of the device is selected, for example, from above the device instead of passing through between the devices, and after the new path is generated, the bending radius is checked again until it meets the target rules; Step 164, if there is a problem of not meeting the target rules of the inherent frequency of the bracket, adjust the structure parameters of the bracket or replace the material of the bracket, recalculate the inherent frequency of the bracket, and until it meets the target rules; Specifically, for the problem of not meeting the target rules of the inherent frequency (such as the current frequency of the bracket f = 85 Hz < 100 Hz), first adjust the structure parameters of the bracket: increase the number of bracket ribs (increase the sectional moment of inertia I ), or increase the sectional size of the bracket (such as increasing the width of the bracket from 20 mm to 30 mm), and recalculate the frequency by the inherent frequency formula in step 141; If the frequency still does not meet the target rules after adjusting the structure parameters (such as the space is limited and cannot be increased in size), replace the material of the bracket (such as replacing the aluminum alloy bracket ( E = 70 GPa) with a titanium alloy bracket ( E = 110 GPa)), recalculate the frequency until f ≥ 100 Hz; The adjusted bracket model needs to be updated to the electrical instrument layout simultaneously to ensure compatibility with the device installation interface; Step 165, if there is a problem of not meeting the target rules of the operation space or interference, adjust the installation position of the related device, optimize the cable path, or modify the local structure until the problem is solved; Specifically, for the problem of not meeting the target rules of the operation space (such as the space around the IMU maintenance interface is blocked by the cable, and the operation space < 300 mm), first adjust the path of the blocking cable and move the cable to the other side of the interface; If the cable is still blocked after adjustment, slightly adjust the installation angle of the IMU (such as rotating 15°) to expand the space around the interface; For the interference problem (such as the distance between the device and the cabin wall is 3 mm < 5 mm), adjust the installation position of the device (such as moving 5 mm towards the center of the cabin section), or modify the local cabin wall structure (such as grinding the protruding area of the cabin wall), and after adjustment, check the interference and operation space by the interference check and operation space check in step 141 to ensure that the problem is solved; Step 166, after the adjustment is completed, the adjusted electrical instrument layout is re-executed to check the flow, and if there are still items that violate the target rules, repeat the above adjustment steps until all the check results meet the target rules; Specifically, the electrical instrument layout adjusted in steps 162-165 is re-imported into the full model batch check flow in step 14, and interference, distance, bending radius, inherent frequency, operation space check and VR review are performed to generate a new check report; If there are still items that violate the target rules in the report (such as new cables interfering with devices), return to step 161 and repeat the adjustment operations of steps 162-165 for new problem items; until there are no items that violate the target rules in the check report, stop the adjustment process; Step 167, the electrical instrument layout that all checks meet the target rules is determined as the target electrical instrument layout; specifically, the electrical instrument layout without violation of the target rules is finally confirmed: all items in the check report are marked as conforming to the rules, and the device installation interface and cable connection relationship are consistent with the overall design requirements; after confirming that there is no error, the layout is marked as the target version, the design data is frozen (not allowed to be modified arbitrarily), and at the same time, the key parameters in the adjustment process (such as the distance before and after adjustment, the frequency value) are recorded, forming a design traceability document.

[0065] In this embodiment, step 161 is marked by differentiating highlight and pop-up details (including rule labels and coordinates), so that the violation items are obvious at a glance, the designer can quickly jump to the problem position, avoid the time-consuming and omission of manual checking, and greatly improve the problem positioning efficiency.

[0066] Different adjustment strategies are formulated for different violation items, the distance problem is adjusted in order according to the device priority (low priority devices are preferred), the cable bending problem is optimized in arc and then the path is re-planned, and the support frequency problem is adjusted in structure and then the material is changed, so as to ensure that the adjustment is not blind and does not damage the core equipment (such as flight control computer and IMU) layout, and the efficiency and design safety are considered.

[0067] Step 166 re-executes full quantity inspection (including VR review) on the layout after adjustment through the adjustment-reinspection-circulation mechanism, so as to prevent the situation that one problem is corrected and another problem is added, ensure that all violation items are cleared, and avoid exposing hidden dangers in the later manufacturing and assembly stage.

[0068] Step 167 marks the version of the qualified layout, freezes the data, and records the key parameters (such as distance and frequency before and after adjustment) at the same time, which prevents the design data from being arbitrarily tampered with, provides clear traceability basis for subsequent design review and model iteration, and guarantees the standardization and inheritance of design results.

[0069] The whole process is adjusted around the target rules to ensure that the final target layout completely meets the core requirements such as electromagnetic compatibility, mechanical vibration and operation and maintenance, such as the compliance of the distance between IMU and power supply and the support frequency, so as to improve the reliability and safety of the launch vehicle electrical system from the design source, and reduce the risk of later failure.

[0070] In an optional embodiment of the present application, in step 17, the target electrical instrument layout is output.

[0071] Specifically, based on the target electrical instrument layout, two types of output results, design files and production data, are generated: Design file: automatically generate equipment installation drawing (mark equipment position number, installation method, fastener model, installation coordinates), cable laying drawing (mark cable identification, path direction, bending radius control point), equipment list (including equipment label, name, quantity, characteristic parameter); Production data: extract cable path coordinates from three-dimensional cable model, generate cable length table (including cable label, diameter, length, two end interfaces) through length calculation (accumulate adjacent path point distance), directly used for cable production; export processing data (such as STL format, numerical control processing code) of bracket three-dimensional model, used for bracket numerical control processing; generate assembly process guide book (including equipment installation sequence, cable laying step, inspection points); all output achievements are stored according to the filing requirements of the launch vehicle model, and are pushed to the downstream assembly, cable production and bracket processing departments, realizing seamless transmission of design data to the production link.

[0072] In this embodiment, two types of achievements, design file and production data, are generated. The design file meets the design filing and auditing requirements, and the production data directly supports the cable production, bracket processing and other links, without the need for secondary conversion. The achievements are stored and pushed to the downstream departments according to the model filing, eliminating manual transmission errors. For example, cable length table and bracket processing code can be directly used, shortening the production preparation period. The output data is clearly marked (such as installation coordinates and bending radius control points), ensuring that the assembly and production links are executed according to unified standards, and improving the production quality and reliability of the electrical system.

[0073] Example 1 Taking the electrical arrangement design of a small launch vehicle first stage instrument cabin as an example; A method for generating an electrical instrument arrangement drawing of a launch vehicle, comprising: Step 21, preset rule base construction: Obtain arrangement specifications: Collect arrangement specifications through three channels: refer to aerospace industry public standards, such as standards related to equipment installation spacing, industry documents regulating electromagnetic compatibility requirements, and clearly define the safe distance required between sensitive electronic equipment and high-power equipment; extract enterprise internal technical documents, including the requirements for cable laying bending degree in 《Launch Vehicle Electrical Instrument Layout Process Manual》and the mechanical performance constraints in 《Equipment Installation Bracket Design Specification》; analyze historical design verification data, such as records of signal interference caused by the proximity between telemetry equipment and power modules in previous rockets of the same type, and qualified case constraint conditions of assembly delay caused by insufficient instrument cabin operation space, and finally form a complete set of arrangement specifications covering electromagnetism, mechanics and operation and maintenance; Arrange the specifications into preset rules: Decompose and quantify the collected specifications: For the electromagnetic compatibility specification, it is clear that sensitive devices (such as inertial measurement units IMU) and interference source devices (such as power modules above 200W) need to maintain a distance. Combined with engineering verification data, it is set that the distance needs to be greater than 500mm, which is defined as the distance rule, and the rule identifier is RULE001; For the cable laying specification, considering the physical properties of cables of different materials, it is determined that the bending radius of all cable bundles when laid needs to be greater than 5 times the diameter of the cable itself, which is defined as the bending radius rule, and the identifier is RULE002; For the support mechanical specification, combined with the vibration environment of the rocket during flight, it is required that the first-order natural frequency of all device installation supports needs to be greater than 100Hz, which is defined as the frequency rule, and the identifier is RULE003; For the operation and maintenance specification, in order to ensure the convenience of later maintenance of the device, it is stipulated that the operation space around the device maintenance interface needs to be greater than 300mm, which is defined as the operation space rule, and the identifier is RULE004; Pre-set rule storage: In the pre-set rule library built in the PDM system, the above rules are stored in categories: in the rule basic information table, the rule identifiers RULE001 to RULE004, rule types (such as distance rule, frequency rule) and rule descriptions (such as sensitive device and interference source distance requirement) are entered; In the applicable scenario association table, it is clear that each rule corresponds to an application scenario, such as RULE001 associated with IMU and high-power power supply, all cabin sections, RULE003 associated with all device installation supports; In the parameter threshold table, the specific numerical requirements of each rule are recorded, such as 500mm for RULE001 and 100Hz for RULE003, and the numerical units are marked to ensure that the rule data can be accurately called by the system during subsequent design checking; Step 22, feature parameter acquisition and digital instrument determination: Acquire feature parameters: For the IMU (model IMU-300) required for the first stage instrument cabin of the rocket, it is clear from the overall design task book of the launch vehicle that its function is to provide flight attitude measurement, and it belongs to sensitive electronic equipment; Then extract the feature parameters of this IMU from the enterprise electrical equipment attribute database: the size is 250mm×200mm×160mm, the weight is 4.2kg, the interface type includes 2 RS422 signal interfaces and 1 DC power supply interface, the power consumption is 15W, and the electromagnetic compatibility level is the first sensitive device, which can resist strong electromagnetic interference; Determine digital electrical instruments: The preset electrical equipment standard library stores the parameterized three-dimensional model corresponding to the IMU-300. The attribute label of the model completely matches the extracted characteristic parameters: the size label is 250 mm x 200 mm x 160 mm, the weight attribute is 4.2 kg, the interface type and power consumption information are consistent, and the electromagnetic compatibility level is clearly marked as a first-level sensitive device; the acquired characteristic parameters of the IMU-300 are compared with the model attribute labels in the library one by one, and it is confirmed that there is no difference in the five core parameters, and finally it is determined that the parameterized three-dimensional model is the digital electrical instrument corresponding to the IMU-300; Step 23, electrical instrument layout generation: Form a preliminary device layout: The preset digital carrier rocket foundation is the three-dimensional digital prototype of the first-stage instrument cabin of the small carrier rocket. The prototype includes cabin shell, internal stringer structure, 3 groups of device mounting support interfaces, and the range of 80 mm at both ends of the cabin is marked as a forbidden installation area, and the middle area is a preferred installation area. The preset layout template selects the first-stage instrument cabin sensitive device layout template. The template is for IMU type sensitive devices, and the preset installation position is the No. 2 support interface in the middle preferred installation area. The digital electrical instrument of the IMU-300 is placed in the three-dimensional digital prototype according to the preset position of the template, and the system detects the matching of the device mounting interface and the support interface in real time. It is confirmed that the four mounting holes at the bottom of the IMU and the hole diameter of the No. 2 support are both 5 mm, and they can be fixed by bolts without interface conflict. Finally, a preliminary device layout containing the IMU-300 is formed. The connection relationship of the IMU-300 is imported from the electrical schematic diagram, which needs to be connected with the flight control computer (model FCU-500) and the 24V DC power supply module (model PS-240, power 220W). The flight control computer is located 120 mm to the right of the IMU-300, and the power supply module is located 30 mm outside the forbidden installation area on the right side of the cabin. Based on the three-dimensional space data of the preliminary device layout, the system automatically generates a cable recommended path: starting from the signal interface of the IMU-300, along the horizontal direction to the signal interface of the flight control computer, then turning to the right to extend to the output interface of the power supply module, avoiding the stringer structure and other devices in the cabin. The designer views the path through the three-dimensional view and finds that the cable needs to bypass a stringer near the power supply module. The designer manually drags the path point to adjust the direction, moves the path point bypassing the stringer 15 mm away from the stringer. During the optimization process, the system displays the cable length in real time as 1.1 m, and the bending radius at the bending part meets the requirements. After determining the final cable path, the system automatically adds the device position number for the IMU-300, the flight control computer and the power supply module, and adds the label CAB-IMU-001 for the cable. The device layout and the cable path are integrated to generate a complete electrical instrument layout of the first-stage instrument cabin. Step 24, electrical instrument layout inspection: Full model batch inspection: A full model batch check is performed on the generated primary instrument cabin electrical instrument layout: in terms of interference condition checking, a three-dimensional collision detection algorithm is called to calculate the minimum spatial distance between IMU-300 and the surrounding stringers, cables and other structures. The results show that the distance between IMU and stringers is 12mm, and the distance between cable and stringer is 8mm, both of which are greater than the preset safety threshold of 5mm, and there is no interference problem; in terms of electrical instrument layout spacing checking, the three-dimensional coordinates of IMU-300 and the three-dimensional coordinates of the power module are obtained, and the straight-line distance between the two is calculated. The result is 420mm, which is less than the requirement of 500mm in the preset rule, and the spacing is not up to standard; in terms of cable bending radius checking, three adjacent path points on the cable path are selected, the distance and angle between the two adjacent points are calculated, and then the bending radius is determined. The results show that the radius of all bending parts is 35mm, the cable diameter is 7mm, and 35mm is greater than 5 times the cable diameter (35mm), which meets the requirements; in terms of support natural frequency checking, the material elastic modulus, cross-sectional moment of inertia, mass and support length of the IMU installation support are obtained, and the first-order natural frequency of the support is calculated to be 92Hz, which is less than the preset threshold of 100Hz, and is determined to be not up to standard; in terms of operation space checking, the 300mm range around the IMU-300 maintenance interface is checked, and it is found that there is no obstruction in front of the interface, the cable on the side is 50mm away from the interface, and no object occupies the operation space, which is determined to be up to standard; finally, the inspection results are summarized, and two items are not up to standard: the distance between IMU and power module is insufficient, and the natural frequency of IMU installation support is insufficient; Step 25, target rule determination: Determine the target rule: Determination of target rules according to characteristic parameters of IMU-300: analysis of size (250mmx200mmx160mm, all less than 500mm), determination of small equipment, matching of space layout rule from preset rule library; small sensitive equipment needs to keep a distance of at least 150mm from non-sensitive equipment; according to weight (4.2kg, less than 10kg), matching of structure adaptation rule; equipment with weight less than 10kg can be installed on a standard support, and the bearing capacity of the support needs to be greater than 1.2 times the weight of the equipment; according to the interface type (containing multiple signal and power interfaces), matching of interface layout rule; multiple interface equipment needs to reserve 100mm of operating space around the interface; according to power consumption (15W, less than 50W), determination of low-power equipment, matching of thermal environment adaptability rule; low-power equipment does not need to reserve additional heat dissipation spacing; according to the electromagnetic compatibility level (first-level sensitive equipment), matching of electromagnetic compatibility rule; the distance between first-level sensitive equipment and interference source equipment with power greater than 200W needs to be greater than 500mm, and shielded cable needs to be used for connection cable; de-duplication and priority sorting of matched rules; there is a conflict between the 150mm spacing in the space layout rule and the 500mm spacing in the electromagnetic compatibility rule, and the more stringent 500mm spacing requirement is used; electromagnetic compatibility rule and structure adaptation rule are marked as high priority, and other rules are marked as ordinary priority; finally, a target rule list containing 4 rules is formed, which clearly indicates the identification, parameter threshold and priority of each rule; Step 26, adjustment of electrical instrument layout diagram: For the two items that do not meet the requirements, the system generates a visual alarm in the three-dimensional view: the IMU and power module spacing does not meet the requirements, which is marked with a yellow dashed line box, and the pop-up window displays the violation of the target rule (electromagnetic compatibility rule), the current spacing is 420mm, the required spacing is greater than 500mm, and the problem location coordinates are X =850mm, Y =0mm, Z =0mm; the support inherent frequency does not meet the requirements, which is marked with a red dashed line box in the support area, and the pop-up window displays the violation of the target rule (structure adaptation rule), the current frequency is 92Hz, the required frequency is greater than 100Hz, and the problem location coordinates are X =800mm, Y =0mm, Z =0mm, the designer can click the pop-up window to directly jump to the problem area; Processing of spacing not meeting the requirements: from the preset electrical equipment standard library, it is known that IMU-300 and flight computer are first-level priority, power module is second-level priority, and auxiliary sensor is third-level priority; the position of the second-level priority power module is adjusted first, which is moved 100mm to the right of the cabin section, the spacing between IMU and power module is recalculated to be 520mm, which is greater than the target rule requirement of 500mm, and the spacing problem is solved; The problem of the bracket inherent frequency not meeting the standard is solved by adjusting the bracket structure parameters, adding 1 piece of 2mm-thick rib plate on both sides of the bracket to enhance the stiffness of the bracket and improve the sectional moment of inertia. The newly calculated inherent frequency of the bracket is 108Hz, which is greater than the requirement of 100Hz. After the adjustment, the adjusted electrical instrument layout is imported into the full model batch checking process again to perform interference, spacing, bending radius, inherent frequency, and operation space checking. Meanwhile, the design and assembly personnel are organized to conduct VR review to check the convenience of equipment installation and maintenance. The new checking report shows that all items meet the target rules, and there is no objection in the VR review and no new rule violation items. The electrical instrument layout that passes the inspection is finally confirmed. The equipment installation interface model, cable connection relationship, and overall design task book requirements are checked to be consistent. The layout is marked as the target version V1.0 in the PDM system, and the design data is frozen to prevent arbitrary modification. At the same time, the key parameters in the adjustment process are recorded, including the coordinates before and after the power module adjustment, the inherent frequency values before and after the addition of the bracket rib plate, and the design traceability document is formed to finally determine the layout as the target electrical instrument layout. Step 27, output the target electrical instrument layout: Based on the target electrical instrument layout of the primary instrument cabin, two types of output results are generated: design documents, automatically generate equipment installation drawings, which detail the installation position number IMU-300#1, installation method, fastener model M5x10 internal hexagonal bolt, installation coordinates X =750mm, Y =0mm, Z =0mm, and the same installation information of the flight control computer and the power module. Generate a cable laying diagram, label the cable CAB-IMU-001, the path is from IMU to flight control computer to power module, and the location and radius value of the 3 bending radius control points. Generate a device specification table containing device label, device name, quantity, size, weight, and other characteristic parameters, and specify IMU-300, flight control computer, and power module each 1 unit. In terms of production data, all path point coordinates of CAB-IMU-001 are extracted from the three-dimensional cable model, the actual length of the cable is calculated as 1.2 m by accumulating the distance between adjacent path points, a cable length table is generated, which contains the cable label, diameter 7 mm, length 1.2 m, and the type of device interface connected at both ends; the three-dimensional model processing data of the IMU mounting bracket is exported in STL format, and the processing code suitable for the numerical control milling machine is generated, which contains the size of the bracket, the position of the rib plate, and the processing parameters of the mounting hole; a general assembly process guide is generated, which clearly defines the equipment installation sequence as installing the bracket first, then fixing the IMU, installing the flight control computer, installing the power module, and laying the cable. It is emphasized that the bending radius needs to be maintained during cable laying, and the inspection points include key items such as equipment spacing and bracket frequency; all output results are stored in the production data module of the PDM system according to the archiving requirements of the launch vehicle type - first stage instrument cabin - 2024 version, and are pushed to the general assembly workshop, cable production workshop, and bracket processing workshop through the system, ensuring that design data is directly used for production links without the need for manual secondary conversion.

[0074] The present application combines multi-specialty parallel design with three-dimensional digital modeling, breaking the traditional serial limitations, avoiding problems such as insufficient space and interference in advance, reducing rework and coordination costs, and shortening the design cycle.

[0075] A preset rule library is constructed by combining public standards, internal documents, and historical data, which converts text specifications into structured quantitative rules, reduces dependence on personnel experience, and ensures design consistency and optimality.

[0076] In the design stage, full-dimensional batch checking driven by algorithms is used to detect problems such as spacing, bending radius, and natural frequency in advance, avoiding hidden dangers left to the manufacturing stage, and significantly reducing modification costs.

[0077] Based on the precise matching of target rules according to equipment feature parameters, the priority of the rule is adjusted in order, and the adjustment-reinspection closed-loop mechanism is used to ensure that the layout meets the core constraints and improve the reliability and safety of the electrical system.

[0078] The output results cover design files and production data, which can be directly connected to downstream production links, realizing seamless connection between design and production, and improving overall research and production efficiency.

[0079] As shown in Figure 2 The embodiment of the present application also provides a generation device 20 of an electrical instrument layout of a launch vehicle, which comprises: An acquisition module 21 is configured to acquire feature parameters of required electrical instruments of the launch vehicle. The processing module 22 is configured to: determine a digital electrical instrument corresponding to the required electrical instrument according to the characteristic parameter; generate an electrical instrument layout of the carrier rocket according to the digital electrical instrument and a preset digital carrier rocket base; obtain an inspection result of the electrical instrument layout according to the electrical instrument layout; determine a target rule from preset rules in a preset rule library according to the characteristic parameter; adjust the electrical instrument layout according to the target rule and the inspection result, so that the inspection result meets the target rule, to obtain a target electrical instrument layout; and output the target electrical instrument layout; wherein a construction process of the preset rule library comprises: obtaining an arrangement specification of electrical instruments of the carrier rocket; converting the arrangement specification into a preset rule; and storing the preset rule into the preset rule library.

[0080] Optionally, converting the arrangement specification into the preset rule comprises: converting the arrangement specification into the preset rule, wherein the preset rule comprises a rule type, an applicable scenario and a parameter threshold.

[0081] Optionally, determining the digital electrical instrument corresponding to the required electrical instrument according to the characteristic parameter comprises: matching a digital electrical instrument consistent with the characteristic parameter from a preset electrical equipment standard library, wherein the characteristic parameter comprises a size, a weight, an interface type, a power consumption and an electromagnetic compatibility level of the electrical instrument.

[0082] Optionally, generating the electrical instrument layout of the carrier rocket according to the digital electrical instrument and the preset digital carrier rocket base comprises: placing the digital electrical instrument in the preset digital carrier rocket base according to a preset arrangement template to form a preliminary device layout; forming a cable path on the preliminary device layout according to a connection relationship of the required electrical instrument to generate the electrical instrument layout of the carrier rocket.

[0083] Optionally, obtaining the inspection result of the electrical instrument layout according to the electrical instrument layout comprises: performing full-model batch inspection on the electrical instrument layout to obtain the inspection result of the electrical instrument layout, wherein the inspection result comprises interference conditions between devices, between a device and a structure, between a cable and other objects, and between electrical instrument layout spacings, cable bending radii, support inherent frequencies and operation spaces.

[0084] Optionally, determining the target rule from the preset rules in the preset rule library according to the characteristic parameter comprises: matching corresponding space layout rules and structure adaptation rules from the preset rules in the preset rule library according to the size, the weight and the interface type in the characteristic parameter. According to the power consumption and electromagnetic compatibility level in the characteristic parameters, a corresponding electromagnetic compatibility rule and thermal environment adaptability rule are matched from preset rules in a preset rule library; The space layout rule, structure adaptation rule, electromagnetic compatibility rule and thermal environment adaptability rule are taken as the target rule.

[0085] Optionally, according to the target rule and the check result, the electrical instrument layout is adjusted so that the check result meets the target rule, and a target electrical instrument layout is obtained, including: For an item in the check result that violates the target rule, a visual alarm is generated in the electrical instrument layout and a problem position is located; If there is a problem of non-compliance of the digital electrical instrument layout spacing, the placement position of a low-priority digital electrical instrument in a preset digital carrier rocket is adjusted first; if adjusting a single digital electrical instrument cannot meet the requirement, the layout of multiple digital electrical instruments in the region is re-planned until the spacing meets the target rule; If there is a problem of non-compliance of the cable bending radius, the cable bending curvature is increased first; if increasing the cable bending curvature cannot meet the requirement, the cable path in the region is re-planned to ensure that the cable bending radius meets the target rule; If there is a problem of non-compliance of the support natural frequency, the structure parameters of the support are adjusted or the support material is replaced, and the support natural frequency is re-calculated until it meets the target rule; If there is a problem of non-compliance of the operation space or interference, the installation position of the related equipment is adjusted, the cable path is optimized or the local structure is modified until the problem is solved; After the adjustment is completed, the check process is re-executed on the adjusted electrical instrument layout, and if there is still an item that violates the target rule, the above adjustment steps are repeated until all the check results meet the target rule; The electrical instrument layout in which all the check results meet the target rule is determined as the target electrical instrument layout.

[0086] It should be noted that the device corresponds to the above method, and all the implementation manners in the above method embodiments are applicable to this embodiment and can achieve the same technical effects.

[0087] Embodiments of the application also provide a computing device, including one or more processors; a storage device for storing one or more programs, when the one or more programs are executed by the one or more processors, so that the one or more processors implement the method as described above. All the implementation manners in the above method embodiments are applicable to this embodiment and can achieve the same technical effects.

[0088] The embodiment of the present application further provides a computer device readable storage medium, which stores instructions, and when the instructions are run on the computer device, the computer device executes the method as described above. All implementation manners in the above method embodiment are applicable to this embodiment, and the same technical effects can be achieved.

[0089] Those skilled in the art can clearly understand that the units and algorithm steps of the examples described in combination with the embodiments disclosed in the present application can be realized by electronic hardware or a combination of software and electronic hardware of a computing device. Whether the functions are realized 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 realize the described functions for each specific application, but such implementation should not be considered beyond the scope of the present application.

[0090] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the above-described system, device and unit can refer to the corresponding processes in the foregoing method embodiments, which will not be repeated here.

[0091] In the embodiments provided by the present application, it should be understood that the disclosed device and method can be implemented in other ways. For example, the device embodiments described above are only schematic. The division of the units is only a logical function division. There can be another division manner in actual implementation. For example, a plurality of units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed mutual couplings or direct couplings or communication connections between the units can be indirect couplings or communication connections through some interfaces, devices or units, and can be electrical, mechanical or in other forms.

[0092] The units described as separate components can or can not be physically separate, and the components displayed as units can or can not be physical units. That is, they can be located in one place, or can be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the embodiment.

[0093] In addition, each functional unit in each embodiment of the present application can be integrated into a processing unit, or each unit can exist physically independently, or two or more units can be integrated into one unit.

[0094] If the functions are implemented in the form of software function units and sold or used as independent products, they can be stored in a storage medium readable by a computing device. Based on this understanding, the technical solutions of the present application or the parts that essentially contribute to the prior art or the parts of the technical solutions can be embodied in the form of software products. The computing device software product is stored in a storage medium and includes a plurality of instructions for causing a computing device (which can be a personal computing device, a server, or a network device, etc.) to execute all or part of the steps of the method described in the various embodiments of the present application. The aforementioned storage medium includes a U disk, a mobile hard disk, a ROM, a RAM, a magnetic disk or an optical disk, and various program code storage media.

[0095] In addition, it should be noted that in the device and method of the present application, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions of the present application. Moreover, the steps of performing the above series of processes can naturally be executed in time sequence according to the order of description, but do not necessarily have to be executed in time sequence. Some steps can be executed in parallel or independently of each other. It can be understood by those skilled in the art that all or any steps or components of the method and device of the present application can be implemented in hardware, firmware, software or a combination thereof in any computing device (including a processor, a storage medium, etc.) or a network of computing devices, which can be implemented by those skilled in the art with basic programming skills after reading the description of the present application.

[0096] Therefore, the object of the present application can also be achieved by running a program or a set of programs on any computing device. The computing device can be a commonly known general-purpose device. Therefore, the object of the present application can also be achieved by merely providing a program product containing program code for implementing the method or device. That is, such a program product also constitutes the present application, and a storage medium storing such a program product also constitutes the present application. Obviously, the storage medium can be any commonly known storage medium or any storage medium developed in the future. It should be noted that in the device and method of the present application, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions of the present application. Moreover, the steps of performing the above series of processes can naturally be executed in time sequence according to the order of description, but do not necessarily have to be executed in time sequence. Some steps can be executed in parallel or independently of each other.

[0097] The above is the preferred embodiment of the present application. It should be noted that for those skilled in the art, without departing from the principles of the present application, a number of improvements and refinements can be made, which should also be considered within the scope of protection of the present application.

Claims

1. A method for generating an electrical instrumentation layout diagram of a launch vehicle, characterized in that, include: Obtain the characteristic parameters of the electrical instruments required for the launch vehicle; Based on the aforementioned characteristic parameters, determine the digital electrical instrument corresponding to the required electrical instrument; Based on the digital electrical instruments and the preset digital launch vehicle foundation, generate the electrical instrument layout diagram of the launch vehicle; Based on the electrical instrument layout diagram, the inspection results of the electrical instrument layout diagram are obtained; Based on the aforementioned feature parameters, the target rule is determined from the preset rules in the preset rule base; Based on the target rules and inspection results, the electrical instrument layout diagram is adjusted so that the inspection results conform to the target rules, thus obtaining the target electrical instrument layout diagram; Output the layout diagram of the target electrical instruments; The process of constructing the preset rule base includes: obtaining the layout specifications of the electrical instruments of the launch vehicle; converting the layout specifications into preset rules; and storing the preset rules in the preset rule base.

2. The method for generating the electrical instrumentation diagram of a launch vehicle according to claim 1, characterized in that, Converting the layout specifications into preset rules includes: The layout specifications are converted into preset rules, which include: rule type, applicable scenario and parameter threshold.

3. The method for generating the electrical instrumentation diagram of a launch vehicle according to claim 1, characterized in that, Based on the aforementioned characteristic parameters, the digital electrical instruments corresponding to the required electrical instruments are determined, including: The system matches digital electrical instruments from a pre-defined electrical equipment standard library that match the specified characteristic parameters, including the instrument's size, weight, interface type, power consumption, and electromagnetic compatibility level.

4. The method for generating the electrical instrumentation diagram of a launch vehicle according to claim 1, characterized in that, Based on the aforementioned digital electrical instruments and the pre-defined digital launch vehicle foundation, an electrical instrument layout diagram for the launch vehicle is generated, including: The digital electrical instruments are arranged in a preset digital launch vehicle foundation according to a preset layout template to form a preliminary equipment layout. Based on the connection relationships of the required electrical instruments, cable paths are formed on the preliminary equipment layout to generate the electrical instrument layout diagram of the launch vehicle.

5. The method for generating the electrical instrumentation diagram of a launch vehicle according to claim 1, characterized in that, Based on the electrical instrument layout diagram, the inspection results of the electrical instrument layout diagram are obtained, including: A full-model batch inspection is performed on the electrical instrument layout diagram to obtain the inspection results. The inspection results include: interference between equipment, between equipment and structure, between cables and other objects, as well as the spacing of electrical instruments, the bending radius of cables, the natural frequency of supports, and the operating space.

6. The method for generating the electrical instrumentation diagram of a launch vehicle according to claim 1, characterized in that, Based on the aforementioned feature parameters, the target rule is determined from preset rules in a preset rule base, including: Based on the size, weight, and interface type in the feature parameters, the corresponding spatial layout rules and structural adaptation rules are matched from the preset rules in the preset rule base; Based on the power consumption and electromagnetic compatibility level in the feature parameters, the corresponding electromagnetic compatibility rules and thermal environment adaptability rules are matched from the preset rules in the preset rule base; The spatial layout rules, structural adaptation rules, electromagnetic compatibility rules, and thermal environment adaptability rules are taken as the target rules.

7. The method for generating the electrical instrumentation diagram of a launch vehicle according to claim 1, characterized in that, Based on the target rules and inspection results, the electrical instrument layout diagram is adjusted to ensure that the inspection results conform to the target rules, resulting in the target electrical instrument layout diagram, including: For items that violate the target rules in the inspection results, generate visual alarms in the electrical instrument layout diagram and locate the problem location; If there is a problem with the spacing of digital electrical instruments not meeting the standards, the placement of low-priority digital electrical instruments in the pre-set digital launch vehicle foundation should be adjusted first; if adjusting a single digital electrical instrument cannot meet the requirements, the layout of multiple digital electrical instruments in the area should be replanned until the spacing meets the target rules. If there is a problem with the cable bending radius not meeting the standard, first increase the cable bending arc. If increasing the cable bending arc cannot meet the requirements, replan the cable route in the area to ensure that the cable bending radius meets the target rules. If the natural frequency of the support is not up to standard, adjust the structural parameters of the support or replace the support material, and recalculate the natural frequency of the support until it meets the target rules. If there are issues such as insufficient operating space or interference, adjust the installation location of the relevant equipment, optimize the cable path, or modify the local structure until the problem is resolved. After the adjustment is completed, the inspection process is repeated on the adjusted electrical instrument layout diagram. If there are still items that violate the target rules, the above adjustment steps are repeated until the inspection results all comply with the target rules. The electrical instrument layout diagram that fully meets the target rules is identified as the target electrical instrument layout diagram.

8. A device for generating an electrical instrumentation diagram for a launch vehicle, characterized in that, include: The acquisition module is used to acquire the characteristic parameters of the electrical instruments required for the launch vehicle; The processing module is used to determine the digital electrical instruments corresponding to the required electrical instruments based on the characteristic parameters; and to generate an electrical instrument layout diagram of the launch vehicle based on the digital electrical instruments and a preset digital launch vehicle foundation. Based on the electrical instrument layout diagram, an inspection result of the electrical instrument layout diagram is obtained; based on the feature parameters, a target rule is determined from the preset rules in the preset rule base; based on the target rule and the inspection result, the electrical instrument layout diagram is adjusted so that the inspection result conforms to the target rule, thereby obtaining the target electrical instrument layout diagram; Output the target electrical instrument layout diagram; wherein, the construction process of the preset rule base includes: obtaining the layout specifications of the launch vehicle's electrical instruments; converting the layout specifications into preset rules; and storing the preset rules in the preset rule base.

9. A computing device, characterized in that, include: One or more processors; A storage device for storing one or more programs, which, when executed by one or more processors, cause the one or more processors to implement the method as described in any one of claims 1 to 7.

10. A computing device readable storage medium, characterized in that, The computing device readable storage medium stores a program that, when executed by a processor, implements the method as described in any one of claims 1 to 7.

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