Method for manufacturing mechatronic-thermo-aerodynamic-liquid integrated structure based on slm forming

Abstract

The application discloses a kind of based on SLM forming's machine-electric-thermal-gas-liquid integrated structure manufacturing method, comprising: constructing the three-dimensional model of machine-electric-thermal-gas-liquid integrated structure;SLM forming is carried out based on the three-dimensional model of machine-electric-thermal-gas-liquid integrated structure using Ti-6Al-4V titanium alloy powder as forming material;After SLM forming, the structure obtained is post-processed and cable embedding is completed, to obtain based on SLM forming's machine-electric-thermal-gas-liquid integrated structure.The application can realize the integrated design and efficient manufacturing of spacecraft machine, electricity, heat, gas, liquid multi-element function, solve the core pain point of traditional process, and improve the comprehensive performance of spacecraft.

Description

Technical Field

[0001] This invention relates to an integrated mechanical-electrical-thermal-gas-liquid structure and additive manufacturing method based on SLM forming, belonging to the field of multifunctional integrated structure and manufacturing technology for spacecraft. Background Technology

[0002] The new generation of spacecraft is developing towards multi-functional integration, extreme lightweighting and overall design. As the complexity of spacecraft on-orbit missions increases, their structures need to simultaneously bear multiple functions such as mechanical support, electrical (signal transmission), thermal (temperature control), gas (gas transmission), and liquid (liquid transport), and exhibit the core characteristic of cross-scale distribution of macroscopic and microscopic features. On a macroscopic level, it needs to meet the overall load-bearing stiffness and size constraints of the spacecraft, and on a microscopic level, it needs to achieve the precise layout of precision components such as fine thermal control structures and micro-pipelines.

[0003] Additive manufacturing (also known as 3D printing) is based on the core principle of layered manufacturing and layer-by-layer stacking. It can break through the manufacturing limitations of traditional cutting and casting processes on complex internal cavities and irregular structures. It can achieve integrated forming of complex structures without molds. It is an effective technical means to solve the manufacturing problems of multifunctional integrated structures for next-generation spacecraft. Among them, selective laser melting (SLM) process has become the preferred technical path for manufacturing complex structures of spacecraft due to its advantages such as high forming accuracy, high density and compatibility with lightweight and high-strength metal materials.

[0004] Currently, the multi-functional composite structures of traditional satellites and other spacecraft still adopt the traditional model of "single-function decoupled independent design + multi-module combination and integration." Functional modules such as structure, thermal control, power supply, information transmission, and gas-liquid transmission are designed and manufactured independently, and then combined into a whole through multiple assembly processes. Specifically, the basic load-bearing structural plate must first be manufactured, and then heat pipes are embedded into the structural plate through pre-embedding or post-embedding processes to achieve thermal control functions. Gas-liquid transmission pipelines are assembled through welding, bolting, etc., and electrical signal transmission is achieved by attaching cable networks to the structural surface through snap-fitting, binding, etc. The entire manufacturing process involves dozens of processes including design, processing, assembly, and testing. This not only results in a design cycle of 6-12 months and low manufacturing efficiency, but also has many core defects: First, the structural redundancy is serious. The independent design of each functional module requires reserving additional assembly space and connection structures, resulting in an overall weight redundancy rate of 20%-30% for the spacecraft, directly increasing launch costs (spacecraft weight redundancy). First, launch costs are positively correlated with weight; each additional kilogram of weight requires an additional hundreds of thousands of yuan in launch costs. Second, reliability is insufficient; there are hundreds of assembly interfaces between multiple modules, and gaps and loosening are prone to occur at these interfaces. Under the complex vibration and high and low temperature cycling environment of spacecraft in orbit, failures such as heat pipe detachment, pipeline leakage, and cable wear are likely to occur, which seriously affect the reliability of spacecraft in orbit. Third, performance improvement is limited; assembly interfaces increase thermal conduction impedance, signal transmission loss, and gas-liquid transmission pressure drop, resulting in a 15%-25% reduction in heat exchange efficiency and a decrease in signal transmission stability, which cannot meet the requirements of high-power heat dissipation and high-precision signal transmission of the new generation of spacecraft.

[0005] In summary, traditional satellite multifunctional composite structures and their manufacturing processes, limited by the "decoupled design + assembly integration" model, cannot simultaneously meet the three core requirements of functional integration, payload-to-weight ratio (the ratio of payload weight to structural weight), and production and development cycle. This makes them ill-suited to the development trends of next-generation spacecraft that emphasize multifunctionality, lightweight design, and high reliability. Therefore, developing a mechanical-electrical-thermal-gas-liquid integrated structure and additive manufacturing method based on SLM forming to overcome the bottlenecks of traditional manufacturing technologies and achieve integrated and efficient manufacturing of multiple functions in spacecraft has become a critical technical problem urgently needing to be solved in the field of next-generation spacecraft structure development. It is also an effective way to promote the upgrading of spacecraft manufacturing technology towards high-end and intelligent manufacturing. Summary of the Invention

[0006] The purpose of this invention is to overcome the aforementioned shortcomings and provide a manufacturing method for an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming. This method solves the technical problems of existing spacecraft multifunctional composite structures, such as long design cycles, cumbersome manufacturing processes, severe structural and weight redundancy, low reliability, and insufficient functional integration. These structures cannot simultaneously achieve optimal functional integration, mass-to-weight ratio, and production development cycle, making them unsuitable for the development needs of next-generation spacecraft. This invention enables the integrated design and efficient manufacturing of multiple mechanical, electrical, thermal, gas, and liquid functions in spacecraft, addressing the core pain points of traditional processes and improving the overall performance of spacecraft.

[0007] To achieve the above-mentioned objectives, the present invention provides the following technical solution: A method for manufacturing an integrated mechatronic-thermal-gas-liquid structure based on SLM forming, comprising: S1 constructs a three-dimensional model of an integrated mechanical-electrical-thermal-gas-liquid structure; S2 uses Ti-6Al-4V titanium alloy powder as the forming material and performs SLM forming based on a three-dimensional model of an integrated mechanical-electrical-thermal-gas-liquid structure. S3 performs post-processing on the structure obtained after SLM forming and completes cable embedding to obtain an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming.

[0008] Furthermore, step S1 includes: Construct an initial model including skin and internal padding based on the target satellite payload layout; With minimizing structural weight as the objective function and bearing stiffness and heat dissipation efficiency as constraints, topology optimization is performed on the initial model to obtain the optimized model; Based on gas-liquid transmission parameters (such as pipeline pressure and pipeline flow rate) and electrical transmission parameters (such as power supply), gas-liquid transmission pipelines and electrical transmission pipelines are reserved in the optimization model. The functional interfaces were added to the obtained model, and then the three-dimensional model of the integrated mechanical-electrical-thermal-gas-liquid structure was completed.

[0009] Furthermore, when performing topology optimization on the initial model, Ti-6Al-4V was selected as the material; Topology optimization of the initial model includes topology optimization of the lightweight load-bearing structure and topology optimization of the fine thermal control structure. Topology optimization of the lightweight load-bearing structure includes designing the internal filling lattice as BCC or BCC-Z, with a cell size of 5-10mm, and a structural plate thickness of 1 / N (i.e., the structural plate thickness is an integer multiple of the cell size) to ensure the integrity of the lattice. The lattice rod diameter is 0.5mm~0.8mm, and the structural skin thickness is 0.6mm~1.2mm. Topology optimization of the fine thermal control structure includes adopting a microchannel heat pipe structure. The microchannel heat pipe is a microstructure printed to achieve thermal control through capillary action. The microchannel heat pipe spacing is s=30~35mm, and a channel heat pipe is used to adapt to the total heat dissipation power requirement (channel heat pipe is a conventional technology). The channel heat pipe type is Ω or T-type.

[0010] Furthermore, when reserving gas-liquid transmission pipelines and electrical transmission pipelines in the optimization model, the pipeline routing avoids the load installation position and the microchannel heat pipes and channel heat pipes of thermal control, and the pipeline spacing is ≥8mm.

[0011] Furthermore, the Ti-6Al-4V titanium alloy powder has a particle size D_50=28μm, a particle size distribution of 18μm~50μm, a powder sphericity ≥0.9, a loose packing density ρ_b=1.38g / cm^3, a tap density ρ_t=1.58g / cm^3, an oxygen content ≤0.12wt%, and a nitrogen content ≤0.05wt%. Before SLM forming, the Ti-6Al-4V titanium alloy powder is pretreated, including: placing the Ti-6Al-4V titanium alloy powder in a vacuum drying oven and drying it at 115℃±5℃ for 2.2h±0.1h to remove surface adsorbed moisture and impurities; after drying, it is transferred to the powder chamber of the SLM forming equipment under the protection of argon gas with a purity ≥99.999% to prevent powder oxidation.

[0012] Furthermore, after SLM forming is completed, the part is naturally cooled to room temperature under an argon atmosphere; the part is separated from the substrate by wire cutting at a speed of 4.8 mm / min ± 0.5 mm / min, and the surface roughness R_a is ≤ 3.2 μm; the inside of the gas-liquid transmission pipeline and the electrical transmission pipeline and the surface of the part are purged with argon to remove residual powder; burrs and excess supports are removed by sanding, and the surface roughness R_a after sanding is ≤ 1.6 μm; the inner diameter of the gas-liquid transmission pipeline and the electrical transmission pipeline is quantitatively removed by abrasive flow, and the wall thickness error of the part is ≤ ± 0.02 mm.

[0013] Furthermore, step S3 includes: A three-step process of high-pressure rinsing, ultrasonic fine cleaning, and drying is used to remove excess pipe material from the structure obtained after SLM forming. Helium mass spectrometry leak detection method is used to test the leak rate of the sealed pipelines, microchannel heat pipes, channel heat pipe interfaces and vacuum sealant sealing joints in the structure obtained after SLM forming (generally, if the test passes, proceed to the next step; if the test fails, the structure is scrapped directly). Microchannel heat pipes and channel heat pipes are filled with ammonia working fluid. The heat pipe volume is calculated based on the actual filling amount and theoretical model to verify whether the heat pipe heat dissipation performance meets the standard (test pieces are printed before the product is formed to verify in advance. Basically, the performance can meet the standard. If it does not meet the standard, it is scrapped directly). The mechanical interface is removed by machining to meet the requirements of high-precision interface installation.

[0014] Compared with the prior art, the present invention has at least one of the following advantages: (1) This invention integrates a lightweight load-bearing structure with a fine thermal control structure, completely eliminating the assembly interface in traditional processes, effectively reducing thermal conduction resistance, and improving heat exchange efficiency by 15%-25%. It can efficiently solve the core contradiction between miniaturization and high-power heat dissipation in the new generation of spacecraft, and ensure that the load operating temperature is stable within the design range. (2) By reserving cable conduits inside the structure, this invention replaces the traditional external cable hanging and binding mode, effectively saving a lot of space occupied by external cables, reducing the workload of cable fixing by more than 60%, and reducing the overall weight of the spacecraft by 5%-10%, avoiding signal transmission failures caused by on-orbit vibration and wear of cables, and improving the reliability of the electrical system. (3) The gas-liquid transmission pipeline of the present invention is formed synchronously with the supporting structure, eliminating the need for subsequent welding and assembly processes, significantly reducing the welding workload by more than 70%, avoiding the leakage risk caused by welding interfaces, maximizing the use of internal space, increasing space utilization by more than 30%, reducing gas-liquid transmission pressure drop, and improving transmission stability. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming of the present invention. Detailed Implementation

[0016] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0017] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.

[0018] The integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming precisely meets the development needs of next-generation spacecraft. It fully leverages the core advantages of SLM technology—"integrated forming, high precision, and high density"—to simultaneously design and form multiple functional structures, including lightweight load-bearing structures, sophisticated thermal control structures (such as microchannel heat pipes and heat dissipation fins), complex internal gas-liquid transmission pipelines, and pre-reserved cable channels. This completely breaks away from the traditional "split manufacturing - multi-stage assembly" production model. Compared to traditional processes, this technology significantly simplifies production processes, reducing manufacturing steps by more than 60% and shortening the design and manufacturing cycle to 3-6 months. It also eliminates assembly interfaces between multiple modules, improving the connection integrity between different functional components, increasing overall structural stiffness by 30%-40%, and significantly improving structural reliability, effectively avoiding interface failures during on-orbit operation. Furthermore, integrated forming maximizes the use of internal structural space, reducing redundant structural design and lowering spacecraft structural weight by 20%-30%, significantly saving installation space and launch costs. It also improves heat exchange efficiency, signal transmission stability, and gas-liquid transmission smoothness, comprehensively optimizing the overall performance of the spacecraft.

[0019] Based on the core advantages of SLM additive manufacturing process, this invention combines the layout of spacecraft payloads and the requirements of multiple functions. Through the whole process technical solution of "integrated design-integrated forming", the efficient development of mechanical-electrical-thermal-gas-liquid integrated structure is realized. The specific steps are as follows: (1) Integrated structure design: Taking the layout of spacecraft payloads as the core, the overall design of mechanical-electrical-thermal-gas-liquid integrated structure is carried out by comprehensively considering the load heat dissipation power, gas-liquid transmission parameters, electrical signal transmission requirements and the specifications of each functional interface. The topology of lightweight load-bearing structure and fine thermal control structure is optimized at the same time. Gas-liquid transmission pipelines and cable pipelines are reserved in the structure. The three-dimensional model design is completed and the processing files adapted to SLM process are exported to ensure that there is no interference between each functional structure and the dimensional accuracy meets the standards, while taking into account the requirements of load-bearing stiffness and lightweight. (2) Integrated forming of SLM process: The SLM selective laser melting additive manufacturing process is adopted. Lightweight and high-strength metal materials suitable for spacecraft use are selected. The core process parameters such as laser power, scanning speed and layer thickness are set to match the materials and structure. The integrated forming of lightweight load-bearing structure and fine thermal control structure is completed in one go under a protective atmosphere. The pre-forming of gas-liquid transmission pipeline and cable pipeline is realized simultaneously to ensure the sealing, straightness and dimensional accuracy of pipeline channels. (3) Post-processing and testing of pipeline and heat pipe: The gas-liquid transmission pipeline and fine thermal control heat pipe after forming are subjected to full-process post-processing and performance testing. The internal cleaning of pipeline, leakage rate testing, interface assembly and working fluid filling are completed in sequence to ensure that the pipeline sealing and cleanliness meet the standards, the heat dissipation performance of heat pipe meets the design requirements, and there is no leakage or performance defect. (4) Internal cable handling and testing: Insert the aerospace-grade cable of the appropriate specification into the reserved cable conduit, complete the cable installation and fixation, and use methods such as continuity test, insulation resistance test, and signal transmission performance test to ensure that the cable is fixed reliably and the transmission is stable, and is suitable for the vibration environment of the spacecraft in orbit.

[0020] This invention has the following advantages: (1) Advantages of integrated structure-thermal control: The lightweight load-bearing structure and the fine thermal control structure are integrated into one, completely eliminating the assembly interface in the traditional process, effectively reducing the thermal conduction impedance, and improving the heat exchange efficiency by 15%-25%. This can efficiently solve the core contradiction between the miniaturization of the new generation of spacecraft and the heat dissipation of high power, and ensure that the working temperature of the payload is stable within the design range. (2) Advantages of integrated structure-electrical system: By reserving cable pipelines inside the structure, the traditional external cable hanging and binding mode is replaced, which effectively saves a lot of space occupied by external cables, reduces the workload of cable fixing by more than 60%, and reduces the overall weight of the spacecraft by 5%-10%. This avoids signal transmission failure caused by cable vibration and wear in orbit and improves the reliability of the electrical system. (3) Advantages of integrated structure-gas-liquid pipeline: The gas-liquid transmission pipeline is formed synchronously with the load-bearing structure, eliminating the need for subsequent welding and assembly processes. This significantly reduces the welding workload by more than 70%, avoids the leakage risk caused by welding interfaces, maximizes the use of the internal space of the structure, improves the space utilization rate by more than 30%, reduces the pressure drop of gas-liquid transmission, and improves the transmission stability.

[0021] Furthermore, through integrated design and molding throughout the entire process, this invention can shorten the design and manufacturing cycle of multifunctional spacecraft structures by more than 50%, reduce structural weight by 20%-30%, increase overall structural stiffness by 30%-40%, significantly reduce development and launch costs, and comprehensively enhance the overall performance and market competitiveness of spacecraft.

[0022] The multi-functional integrated structure of this machine (electric, heat, gas, and liquid) mainly consists of a satellite main structure plate 5, a fine-structured microchannel and channel heat pipe 1, a gas-liquid transmission pipeline 2, an electrical transmission pipeline 3, and a functional load 4, etc., and the overall structure is as follows: Figure 1 As shown, the fine structure microchannel and channel heat pipe 1, gas-liquid transmission pipeline 2, electrical transmission pipeline 3, and functional payload 4 are all installed on the satellite main structure plate 5. The fine structure microchannel and channel heat pipe 1 is used for heat dissipation of the structure plate, the gas-liquid transmission pipeline 2 is used for transmitting propellant of the propulsion system, the electrical transmission pipeline 3 is used for embedding the cable network, and the functional payload 4 is selected according to the purpose of the satellite.

[0023] Traditional satellite structural panels are designed as separate units, meaning heat pipes, gas-liquid transmission lines, and electrical transmission lines are manufactured and processed separately, and then assembled to the satellite's load-bearing structural panel via surface mounting or pre- / post-embedding. This invention, using SLM (Surface Mount Technology) process, achieves integrated manufacturing of heat pipes, gas-liquid transmission lines, electrical transmission lines, and the load-bearing structural panel. It overcomes the limitations of traditional spacecraft subsystems being designed independently, achieving a high degree of electrical system integration. Electronic devices and cables are assembled into a structure with thermal control and electromagnetic shielding functions. Thermal control of electronic components is achieved through a high thermal conductivity structural panel, radiators, and heat pipes, giving the structure its own thermal control function. By eliminating the need for enclosures and cables, the overall satellite weight is significantly reduced, and the effective space within the satellite is greatly increased. Furthermore, it significantly reduces assembly steps, achieving structural lightweighting and weight reduction, and improving the overall rigidity of the structural panel. This is an innovative manufacturing method for satellite structural panels that achieves both structural lightweighting and functional integration.

[0024] Example: This invention relates to a manufacturing method for an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming, comprising: Step 1: Based on the load layout, conduct structural design that takes into account heat dissipation and interfaces.

[0025] (1) Taking the target satellite payload layout as the core, and taking into account heat dissipation requirements, specifications of various functional interfaces, lightweight structure, and load-bearing requirements, complete the overall design and three-dimensional modeling of the integrated mechanical-electrical-thermal-gas-liquid structure. Determine the payload layout and confirm the core parameters, including the number, weight, and heat dissipation power of functional payload modules; determine the gas-liquid transmission requirements: transmission medium, transmission flow rate, and working pressure; confirm the electrical transmission requirements: rated voltage, rated current, and cross-sectional dimensions of flat cables; and confirm the structural load-bearing requirements: overall structural stiffness, load-to-mass ratio, and operating temperature range.

[0026] (2) Integrated structural topology optimization design: Ti-6Al-4V material was selected. ANSYS topology optimization software was used, with minimizing structural weight as the objective function and bearing stiffness and heat dissipation efficiency as constraints, to perform topology optimization of the lightweight load-bearing structure and the fine thermal control structure. The internal filling lattice design is BCC, BCC-Z, etc., with cell size of 1 / N of the multi-functional plate thickness, lattice rod diameter of 0.5mm~0.8mm, and structural skin thickness of 0.6mm~1.2mm to ensure both lightweight and load-bearing performance; the fine thermal control structure adopts a microchannel heat pipe design, with heat pipe spacing s=32mm, using channel heat pipes to adapt to the total heat dissipation power requirements, and the pipe type is Ω or T-type.

[0027] (3) Pipeline channel design: Based on the gas-liquid transmission and electrical transmission parameters, calculate and reserve the corresponding pipeline channels: gas-liquid transmission pipeline inner diameter d=7mm, wall thickness δ=0.9mm (calculated from the thin-walled cylinder strength formula δ≥Pd / 2[σ], Ti-6Al-4V allowable stress[σ]=800MPa); flat cable pipeline thickness). 8~1mm (reserving 1.2 times the cable diameter assembly allowance), pipeline routing avoids load installation positions and thermal control heat pipes, pipeline spacing ≥8mm, to prevent functional interference, thermal effects, and signal interference.

[0028] (4) Interface design and 3D modeling: Design the interfaces for each function, including load installation interface, gas-liquid pipeline interface and cable lead-out interface; use SolidWorks software to complete the integrated structural 3D model design to ensure that there is no interference between each functional structure, pipeline channel and interface; use ANSYS software to perform stiffness, strength, heat conduction and flow field simulation verification, export STL format processing files to adapt to the import requirements of SLM forming equipment, and generate design drawings to clarify the dimensions, tolerances and technical requirements of each part.

[0029] Step 2: Manufacturing the integrated mechanical-electrical-thermal-gas-hydraulic structure using SLM technology. (1) Ti-6Al-4V titanium alloy powder was selected as the forming material. The material parameters were: powder particle size D_50=28μm, particle size distribution 18μm~50μm, powder sphericity ≥0.9, loose density ρ_b=1.38g / cm^3, tap density ρ_t=1.58g / cm^3, oxygen content ≤0.12wt%, and nitrogen content ≤0.05wt%. Powder pretreatment: the titanium alloy powder was placed in a vacuum drying oven and dried at 115℃±5℃ for 2.2h±0.1h to remove surface adsorbed moisture and impurities. After drying, it was protected with argon gas with a purity ≥99.999% and transferred to the powder chamber of the SLM forming equipment to prevent powder oxidation.

[0030] (2) Selective laser melting forming equipment is selected with a positioning accuracy of ±0.01mm; the core process parameters are set as shown in Table 1 below to ensure that the forming accuracy and density meet the standards and adapt to the forming requirements of integrated structure and reserved pipeline.

[0031] Table 1 SLM Core Process Parameters

[0032] (3) After the forming is completed, keep the argon atmosphere and cool naturally to room temperature (cooling time ≥ 4.5h) to prevent oxidation and deformation; wire cut to separate the formed part from the substrate, cutting speed 4.8mm / min ± 0.5mm / min, cutting surface roughness R_a ≤ 3.2μm; high pressure argon gas blows the inside of the pipeline and the surface of the structure to remove residual powder, sandpaper polishes to remove burrs and excess support, after polishing the outer surface roughness R_a ≤ 1.6μm; abrasive flow is used to quantitatively remove excess material from the inner diameter of the pipeline, wall thickness error ≤ ± 0.02mm.

[0033] Step 3: Leakage detection, interface assembly, internal cleaning, and working fluid filling of gas-liquid pipelines and heat pipes. (1) Use the three-step method of "high pressure flushing - ultrasonic fine cleaning - drying" to remove excess material from the pipe.

[0034] (2) Use helium mass spectrometry to detect leaks in sealed pipelines, heat pipe interfaces, and vacuum sealant connections.

[0035] (3) The heat pipe is filled with ammonia working fluid (suitable for low temperature environment), and the filling amount and heat pipe volume are verified to ensure that the heat dissipation performance of the heat pipe meets the standards.

[0036] (4) The mechanical interface is removed by mechanical processing to meet the high-precision interface installation requirements.

[0037] Step 4: Install, secure, and inspect the internal cables. Select aerospace-grade cables of appropriate specifications, complete the installation, fixation and full performance testing to ensure stable transmission, reliable fixation and adaptability to on-orbit vibration environment.

[0038] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0039] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for manufacturing an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming, characterized in that, include: S1 constructs a three-dimensional model of an integrated mechanical-electrical-thermal-gas-liquid structure; S2 uses Ti-6Al-4V titanium alloy powder as the forming material and performs SLM forming based on a three-dimensional model of an integrated mechanical-electrical-thermal-gas-liquid structure. S3 performs post-processing on the structure obtained after SLM forming and completes cable embedding to obtain an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming.

2. The manufacturing method of an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming according to claim 1, characterized in that, Step S1 includes: Construct an initial model including skin and internal padding based on the target satellite payload layout; With minimizing structural weight as the objective function and bearing stiffness and heat dissipation efficiency as constraints, topology optimization is performed on the initial model to obtain the optimized model; Based on the gas-liquid transmission parameters and electrical transmission parameters, gas-liquid transmission pipelines and electrical transmission pipelines are reserved in the optimization model; The functional interfaces were added to the obtained model, and then the three-dimensional model of the integrated mechanical-electrical-thermal-gas-liquid structure was completed.

3. The manufacturing method of an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming according to claim 2, characterized in that, When performing topology optimization on the initial model, Ti-6Al-4V was selected as the material; Topology optimization of the initial model includes topology optimization of the lightweight load-bearing structure and topology optimization of the fine thermal control structure; topology optimization of the lightweight load-bearing structure includes internal filling lattice design as BCC or BCC-Z, cell size of 5-10mm, that is, the thickness of the integrated mechanical-electrical-thermal-gas-liquid structure plate is an integer multiple of the cell size to ensure the integrity of the lattice, the lattice rod diameter is 0.5mm~0.8mm, and the structural skin thickness is 0.6mm~1.2mm; The topology optimization of the fine thermal control structure includes the use of microchannel heat pipe structure, with microchannel heat pipe spacing s=30~35mm, and the use of channel heat pipes to adapt to the total heat dissipation power requirements. The channel heat pipe type is Ω or T.

4. The manufacturing method of an integrated mechatronics-thermal-gas-liquid structure based on SLM forming according to claim 2, characterized in that, When reserving gas-liquid transmission pipelines and electrical transmission pipelines in the optimization model, the pipeline routing should avoid the load installation position and the microchannel heat pipes and channel heat pipes of thermal control, and the pipeline spacing should be ≥8mm.

5. The manufacturing method of an integrated mechanical-electrical-thermal-gas-liquid structure based on SLM forming according to claim 1, characterized in that, The Ti-6Al-4V titanium alloy powder has a particle size D_50 = 28 μm, a particle size distribution of 18 μm to 50 μm, a sphericity ≥ 0.9, a loose packing density ρ_b = 1.38 g / cm^3, a tap density ρ_t = 1.58 g / cm^3, an oxygen content ≤ 0.12 wt%, and a nitrogen content ≤ 0.05 wt%. Before SLM forming, the Ti-6Al-4V titanium alloy powder is pretreated, including: placing the Ti-6Al-4V titanium alloy powder in a vacuum drying oven and drying it at 115℃±5℃ for 2.2h±0.1h to remove surface adsorbed moisture and impurities; after drying, it is transferred to the powder chamber of the SLM forming equipment under the protection of argon gas with a purity ≥99.999% to prevent powder oxidation.

6. The manufacturing method of an integrated mechatronics-thermal-gas-liquid structure based on SLM forming according to claim 1, characterized in that, The process parameters for SLM forming include: Laser power: 300-350W; Scanning speed: 1000-1300 mm / s; Filler line spacing: 0.1-0.15mm; Powder layer thickness: 40-60um.

7. A method for manufacturing an integrated mechatronic-thermal-gas-liquid structure based on SLM forming according to claim 1, characterized in that, After SLM forming is completed, the part is naturally cooled to room temperature under an argon atmosphere; the part is then separated from the substrate by wire cutting. The residual powder was removed by purging the inside of the gas-liquid transmission pipeline and the electrical transmission pipeline and the surface of the formed part with argon gas. The burrs and excess support were removed by sanding with sandpaper. After sanding, the surface roughness R_a ≤ 1.6μm. Abrasive flow is used to quantitatively remove excess material from the inner diameter of gas-liquid and electrical transmission pipelines, and the wall thickness error of the formed parts is ≤ ±0.02mm.

8. A method for manufacturing an integrated mechatronic-thermal-gas-liquid structure based on SLM forming according to claim 7, characterized in that, When separating the formed part from the substrate by wire EDM, the cutting speed is 4.8 mm / min ± 0.5 mm / min, and the surface roughness R_a is ≤ 3.2 μm.

9. A method for manufacturing an integrated mechatronic-thermal-gas-liquid structure based on SLM forming according to claim 1, characterized in that, Step S3 includes: A three-step process of high-pressure rinsing, ultrasonic fine cleaning, and drying is used to remove excess pipe material from the structure obtained after SLM forming. Helium mass spectrometry was used to detect leaks in the sealed pipes, microchannel heat pipes, channel heat pipe interfaces, and vacuum sealant connections in the structure obtained after SLM forming. Microchannel heat pipes and channel heat pipes are filled with ammonia working fluid. The heat pipe volume is calculated based on the actual filling amount and theoretical model to verify whether the heat dissipation performance of the heat pipes meets the standards. The mechanical interface is removed by machining to meet the requirements of high-precision interface installation.

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