Modular integrated vacuum high-temperature sintering forming device adaptive to multi-gravity field environment

Abstract

The invention discloses a modular integrated vacuum high-temperature sintering forming device adaptive to a multi-gravity field environment. The modular integrated vacuum high-temperature sintering forming device comprises a metal sealing experiment box body and an axis heating assembly integrated in the metal sealing experiment box body, the axis heating assembly adopts a high-temperature-resistant vacuum sealing pipe end face sealing structure and is combined with a loose fastening mechanism, so that quick plugging and electrical / mechanical dual locking of a sample unit are realized, and the problems of connection failure and floating under a dynamic load are solved; the heating unit adopts a tubular silicon nitride heat transfer matrix matched with an external zirconium oxide and aerogel multi-layer heat insulation structure, high-temperature sintering in a wide temperature zone of 1100 DEG C to 1600 DEG C is realized under low power consumption, and the temperature rise of the surface of the box body is effectively controlled; the rotary acceleration assembly is connected through the mechanical interface, a variable gravity experiment environment is constructed by using centrifugal force, and the device is small in overall size and high in shock resistance and meets the harsh requirements of space station operation and ground supergravity simulation.

Description

Technical Field

[0001] This invention relates to the field of vacuum high-temperature sintering equipment technology, specifically a modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments. Background Technology

[0002] With the leaps in deep space exploration technology and the in-depth development of space materials science, studying the melting, sintering, and solidification of materials under different gravitational fields (such as 1 / 6g on the Moon, 1 / 3g on Mars, or >1g on Earth) using variable gravity scientific experimental cabinets on space stations or ground-based hypergravity centrifuges has become a current scientific frontier. Such experiments typically rely on rotating acceleration disk components to generate a stable centrifugal force field to simulate the target's gravitational environment.

[0003] However, adapting high-temperature vacuum experimental equipment to such variable gravity platforms presents a dual challenge: the significant differences between the Earth and space environments and the adaptability to dynamic loads. Firstly, existing vacuum tube furnace technology is primarily designed for static ground-based laboratories, generally characterized by its large size, high thermal inertia, and reliance on kilowatt-level power supplies. While Earth's energy resources are relatively abundant, such energy-intensive equipment typically requires complex water-cooling systems to maintain low external temperatures. Direct application to a rotating centrifuge platform would significantly increase the counterweight load on the rotating arm. Furthermore, in a space station setting, the platform imposes extremely stringent "entry requirements" on the load, typically demanding that single-channel power consumption be strictly controlled below 200W and that the equipment's external surface temperature be maintained below 60°C to ensure astronaut safety.

[0004] Furthermore, unlike conventional static experiments, variable gravity experimental devices must withstand continuous centrifugal overload and vibration environments for extended periods while rotating at high speeds with the turntable. Electrical connections and mechanical fasteners in traditional high-temperature furnaces are highly susceptible to poor contact or structural loosening under such dynamic conditions. Particularly relevant to space station applications, sample replacement or equipment maintenance in microgravity environments poses a significant risk. Without specialized anti-detachment designs in the fastening structures, disassembled screws and other small components can easily float, posing a serious threat to the operational stability of cabin equipment and the safety of astronauts.

[0005] Furthermore, existing high-temperature experimental equipment is largely limited by material properties, making it difficult to simultaneously meet the requirements of transparent observation (low temperature) and ultra-high temperature sintering (above 1600℃) in a single structure. Traditional sealed tubes are prone to softening and deformation above 1200℃, which limits the research on high-melting-point materials.

[0006] In summary, there is an urgent need to develop a modular vacuum high-temperature sintering device that combines high-efficiency heat insulation and low power consumption, easy maintenance with end-face sealing, resistance to centrifugal force and floating, and can adapt to a wide temperature range from 1100℃ to 1600℃. Summary of the Invention

[0007] The purpose of this invention is to provide a modular integrated vacuum high-temperature sintering forming device that is adapted to multiple force field environments in order to solve the above-mentioned problems.

[0008] The present invention achieves the above objectives through the following technical solutions: A modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments includes an experimental chamber, the outer shell of which is made of metal and has a power socket and a vacuum interface on its surface; the interior of the experimental chamber is provided with a reference surface and a high-strength mechanical interface for mounting the device on a rotating acceleration disk assembly to support the internal components under rotation conditions. A core heating assembly is integrated inside the experimental chamber as a core unit; one or more independent core heating assemblies are arranged side by side inside the experimental chamber; each core heating assembly includes a high-temperature resistant vacuum sealing tube for constructing a vacuum sintering environment, the front end of the high-temperature resistant vacuum sealing tube is provided with an end face sealing structure, the rear end is provided with an auxiliary plug-in handle and is connected to an external power supply through a power supply connector. The sample heating unit is located inside the high-temperature resistant vacuum-sealed tube of the axial heating assembly and is a replaceable modular structure. It includes a tubular silicon nitride heat transfer substrate and a heating element wrapped around the outer surface of the tubular silicon nitride heat transfer substrate, and is provided with a graphite crucible for supporting the sample. A multi-layer thermal insulation structure is filled between the sample heating unit and the high-temperature resistant vacuum sealing tube, including a zirconia ceramic isolation tube and a nano-aerogel insulation layer, to reduce heat loss and control the temperature rise of the outer surface of the chamber.

[0009] A further technical solution is that the surface temperature of the metal shell of the experimental chamber is maintained within a safe range of no more than 60°C, and power sockets are distributed on one side of the experimental chamber. Multiple sets of experimental chambers are installed at each fan-shaped mounting position on the rotating acceleration disk assembly, which serves as a high-temperature heating experiment with multiple force fields, and is used for simulating microgravity of 0.01g to 1.5g in space and hypergravity of 1g to 10g on the ground.

[0010] In a further technical solution, the tubular silicon nitride heat transfer substrate is not limited to a single tubular structure shape, and the tubular silicon nitride heat transfer substrate is disposed inside a zirconia sleeve, the zirconia sleeve is fixedly connected to one side of the heated sample holder, and a second nano-aerogel insulation layer is distributed around the tubular silicon nitride heat transfer substrate.

[0011] In a further technical solution, the edge of one side of the heating sample holder is fixedly connected to the opening of the ceramic cover by screws. The middle part of the heating sample holder and the middle part of the ceramic cover are both channel structures, which are used to insert the temperature sensing end of the thermocouple and to expel air in the gap during vacuuming.

[0012] A further technical solution is that the tube walls in the multi-layer heat insulation structure are filled with a first nano-aerogel heat insulation layer. The multi-layer heat insulation structure is specifically composed of the high-temperature resistant vacuum sealing tube, the zirconia ceramic isolation tube and the metal tube arranged sequentially from the inside to the outside. The front port of the high-temperature resistant vacuum sealing tube is bolted to the external flange structure of the power supply plug in the external structural component through the end face sealing structure. The power supply plug is electrically connected to the power supply plug socket.

[0013] A further technical solution is that the zirconia ceramic isolation tube, the first nano-aerogel insulation layer, and the second nano-aerogel insulation layer are used to reduce heat loss and control the temperature rise of the outer surface of the experimental chamber, as well as to ensure that the sample temperature reaches 1600℃ under vacuum high-temperature sintering environment.

[0014] In a further technical solution, the end face sealing structure is configured as a detachable structure. When changing samples, only the end face sealing structure needs to be unloaded to insert or remove the internal sample heating unit, while the high-temperature resistant vacuum sealing tube remains fixed without disassembling the entire high-temperature resistant vacuum sealing tube, thus ensuring the stability of the vacuum sealing system.

[0015] In a further technical solution, the external structural component also includes the auxiliary plug-in handle and the vacuum interface. Another part of the vacuum interface is located at the rear end of the multi-layer heat insulation structure. The vacuum interface part located at the rear end of the high-temperature resistant vacuum sealing tube is in contact with one end of the ceramic cover. The auxiliary plug-in handle is set on the power supply connector.

[0016] In a further technical solution, the positive and negative terminals of the heating element are electrically connected to plug-in electrodes, and the plug-in electrodes are inserted and positioned together with the power supply plug-in socket by a locking mechanism. A thermocouple is encapsulated in the zirconia ceramic part located in the middle of the power supply plug-in socket, and the temperature sensing end of the thermocouple is exposed and in contact with the outer wall of the graphite crucible. Two thermocouples are provided to realize synchronous temperature measurement, so as to evaluate the temperature uniformity of the heating area and maintain redundant backup of temperature monitoring when a single thermocouple fails.

[0017] In a further technical solution, the heating element is made of platinum-rhodium alloy wire or tungsten-molybdenum alloy material, which is used in conjunction with a thermocouple to achieve automatic temperature control, and the temperature value is controllable.

[0018] The beneficial effects of this invention are: 1. High connection reliability: It realizes the quick insertion and removal of sample units and electrical / mechanical dual locking, which completely solves the problems of connection failure and component floating under dynamic load (centrifugation / microgravity); 2. Excellent thermal insulation performance: The heating unit is equipped with a multi-layer thermal insulation structure of zirconium oxide and aerogel, which achieves high-temperature sintering in a wide temperature range of 1100℃ to 1600℃ with low power consumption, and effectively controls the temperature rise of the cabinet surface, meeting the ergonomic and safety standards. 3. High adaptability: The overall size is small and the shock resistance is strong. It connects to the rotation acceleration component through the mechanical interface and uses centrifugal force to build a variable gravity experimental environment. The core sealing tube can be flexibly selected according to temperature requirements (quartz / corundum), which takes into account both observation and ultra-high temperature experimental needs. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0021] Figure 1 The schematic diagram of the overall layout of the device of the present invention installed on the rotating acceleration disk assembly shows its installation position on the centrifuge sector station and the method of constructing multiple force fields.

[0022] Figure 2 The overall appearance and structure diagram of the experimental chamber shows the high-density integrated design of a single chamber with dual channels (dual axes), as well as the layout of the power connectors and vacuum interfaces on the panel.

[0023] Figure 3 The diagram shows the external structure of the axial heating assembly (core unit), including the auxiliary handle for modular plugging and unplugging, the rear power supply interface, and the inflation / deflation test port.

[0024] Figure 4 The internal longitudinal cross-sectional view of the axial heating assembly shows in detail the sealing structure of the high-temperature resistant vacuum sealing tube end face, the zirconia ceramic isolation tube, and the distribution of the nano-aerogel insulation layer filling the gap.

[0025] Figure 5 The exploded view of the power supply plug-in base and the sample heating unit highlights the non-detachable fastening mechanism to counteract centrifugal overload, the electrode plug-in fit relationship, and the blind insertion guide structure.

[0026] Figure 6 The diagram shows the internal structure of the sample heating unit, illustrating the layout of the heating element and the encapsulation and contact temperature measurement of the two thermocouples in the zirconia ceramic component.

[0027] The attached figures are labeled as follows: 1. Axial heating assembly; 110. Multi-layer thermal insulation structure; 111. Metal tube; 112. First nano-aerogel insulation layer; 113. Zirconia ceramic isolation tube; 114. High-temperature resistant vacuum sealing tube; 120. Sample heating unit; 121. Insertable electrode; 122. Heated sample holder; 123. Ceramic cover; 124. Zirconia sleeve; 125. Heating element; 126. Tubular silicon nitride heat transfer substrate; 127. Thermocouple; 130. Graphite crucible; 140. Second nano-aerogel insulation layer; 2. External structural components; 210. Power supply socket; 211. Power supply connector; 212. Non-detachable fastening mechanism; 220. Auxiliary plug-in handle; 230. Vacuum interface; 3. Experimental enclosure: 310. Power connector; 4. Rotation acceleration disk assembly; 5. Lunar soil samples. Detailed Implementation

[0028] Example 1: Construction of a high-density integrated device structure adaptable to multiple force fields This embodiment demonstrates a modular integrated vacuum high-temperature sintering forming apparatus reference suitable for multi-force field environments. Figures 1-5 The device is designed as a high-density integrated single-box dual-channel system. Two completely independent axial heating components (1) are integrated side by side within a metal-shielded experimental box (3) that conforms to the standard experimental cabinet envelope size of 260mm×144mm×270mm.

[0029] 1. Wide-temperature-range adaptable sealing tube selection design To address the challenge of traditional devices simultaneously supporting both light transmission observation and ultra-high temperature experiments at 1600℃, this invention employs a modular, replaceable high-temperature resistant vacuum sealing tube (114) design: Mode A: Transparent Observation Mode. For routine experiments below 1200℃, a high-purity quartz tube (114) is selected for the high-temperature resistant vacuum sealing tube. Its excellent light transmittance allows an external high-speed camera to penetrate the observation window of the heat insulation layer, if reserved, to capture the melting and solidification process of the sample in real time.

[0030] Mode B: Ultra-high temperature sintering mode: For experiments on high melting point materials ranging from 1200℃ to 1600℃, the high-temperature resistant vacuum sealing tube (114) is upgraded to a high-purity corundum tube. Corundum material can still maintain extremely high mechanical strength and airtightness at 1600℃, and can effectively block ion diffusion at high temperatures to ensure ultimate vacuum.

[0031] Improved sealing structure: Regardless of whether quartz or corundum is used, the high-temperature vacuum sealing tube (114) is fixed by an end-face compression sealing structure. The internal heating unit can be pulled out entirely by simply removing the metal flange on the front end and using the auxiliary insertion and removal handle (220). This design allows operators to change samples or switch between the two modes without disassembling the furnace tube body.

[0032] 2. Core heating unit and thermal protection The internal heating unit has been specifically optimized to adapt to operating conditions of 1600℃: Heat transfer substrate: A tubular silicon nitride heat transfer substrate (126) is used. Silicon nitride material has excellent high-temperature thermal conductivity and thermal shock resistance. As a heat exchange medium between the heating element and the graphite crucible, it can prevent the heating wire from overheating and melting, and ensure heating uniformity.

[0033] Heat source: The heating element (125) wound on the surface of the substrate is made of platinum-rhodium alloy wire suitable for oxidizing atmosphere or below 1600℃, or tungsten-molybdenum alloy wire suitable for vacuum / reducing atmosphere and higher temperature.

[0034] Tiered insulation: A multi-layer composite insulation structure is filled between the silicon nitride substrate and the outer sealed tube, including an inner zirconia ceramic insulating tube (113) and nano-aerogel insulation layers (112, 140) filling the gaps. This "sandwich" structure effectively blocks heat radiation from the core area, ensuring that even if the internal temperature reaches 1600℃, the surface temperature of the external metal experimental chamber can still be controlled within a safe range.

[0035] 3. Anti-centrifugal and anti-floating design To address the centrifugal overload (up to 10g) caused by rotation and the microgravity environment, the internal sample heating unit (120) and power supply socket (210) employ a captive fastener mechanism (212). Once the sample heating unit is inserted, the captive screw mechanically locks both components in place. This design prevents poor contact of the electrodes due to centrifugal force during rotation and completely eliminates the risk of foreign object debris (FOD) from the screw floating inside the chamber after disassembly under microgravity conditions.

[0036] Example 2: Performance Verification This embodiment demonstrates an application scenario where the aforementioned device is used in a ground-based laboratory environment to simulate the vacuum boundary conditions of a space station experiment and to form typical high-melting-point powder materials under limited power consumption. This embodiment aims to serve as a benchmark before variable gravity experiments, focusing on verifying the device's ability to maintain ultimate vacuum, its low-power thermal field construction capabilities, and the safety of human-computer interaction.

[0037] Experimental subjects: simulated lunar soil powder or high melting point ceramic powder were loaded into a graphite crucible (130) with a sample size of Φ10mm×20mm.

[0038] Operating conditions settings: 1. Installation interface verification: Install the device on the fan-shaped workstation interface of the centrifugal turntable of the variable gravity cabinet. Keep the turntable in a stationary and locked state, such as the rotating acceleration disc assembly (4), and power supply through the power connector (310) ≤200W.

[0039] 2. Vacuum environment construction: The molecular pump unit is connected through the vacuum interface (230) to evacuate the multi-layer thermal insulation structure (110) and maintain it in a vacuum state of ≤100Pa to simulate the air pressure of the space environment.

[0040] Working process and equipment performance verification: 1. Start-up and heating: Start the heating program and the tubular silicon nitride heat transfer substrate (126) inside the device begins to work.

[0041] 2. Energy efficiency verification: Monitoring data shows that, thanks to the filled nano-aerogel insulation layer (112, 140), the device successfully drove the sample area to the target sintering temperature of 1100℃ with an input power of only 180W, which meets the space station's ≤200W limit. This proves that the device has the ability to build a high-temperature thermal field with low power consumption.

[0042] 3. Thermal safety verification: During the 60-minute heat preservation at 1100℃, the highest measured temperature on the outer surface of the experimental chamber (3) remained stable at around 48℃, which is better than the astronaut touch safety standard of 60℃, thus verifying the effectiveness of the multi-layer heat insulation structure.

[0043] 4. Structural reliability verification: After the experiment, it was found that the high temperature resistant vacuum sealing tube (114) end face sealing structure had no leakage after a complete thermal cycle from room temperature to 1100℃, and the sealing ring was intact; and the loose fastening mechanism (212) ensured that the power supply electrode always maintained a low impedance connection during thermal expansion and contraction, without any loosening, which verified the static stability and electrical reliability of the mechanical structure.

[0044] Experimental results: 1. Temperature control accuracy: Real-time monitoring data from two embedded armored K-type thermocouples (127) showed that the temperature fluctuation in the sample area was controlled within ±1%, and the data from the two channels were consistent, which verified the effectiveness of the redundant temperature measurement design.

[0045] 2. Forming effect: After natural cooling, the sample was taken out. Utilizing the self-consumption characteristics of the graphite crucible (130) in a high-temperature micro-oxidation environment, the sintered lunar soil ceramic body automatically separated from the mold without adhesion. The sample size shrinkage met expectations, verifying the feasibility of the vacuum sintering process in the device.

[0046] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0047] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments, comprising an experimental chamber (3), the outer shell of which is made of metal and has a power socket (310) and a vacuum interface (230) on its surface; the interior of the experimental chamber (3) is provided with a reference surface and a high-strength mechanical interface for mounting the device on a rotating acceleration disk assembly (4) to support the internal components under rotation conditions; characterized in that, Also includes: A core heating assembly (1) is integrated inside the experimental chamber (3) as a core unit; one or more independent core heating assemblies (1) are arranged side by side inside the experimental chamber (3). Each of the aforementioned axial heating components (1) includes a high-temperature resistant vacuum sealing tube (114) for constructing a vacuum sintering environment. The front end of the high-temperature resistant vacuum sealing tube (114) is provided with an end face sealing structure, and the rear end is provided with an auxiliary plug-in handle (220) and connected to an external power supply through a power supply connector (211). The sample heating unit (120) is located inside the high-temperature resistant vacuum sealing tube (114) and is a replaceable modular structure. It includes a tubular silicon nitride heat transfer substrate (126) and a heating element (125) wrapped around the outer surface of the tubular silicon nitride heat transfer substrate (126), and is provided with a graphite crucible (130) for carrying the sample. A multi-layer thermal insulation structure (110) is filled between the sample heating unit (120) and the high-temperature resistant vacuum sealing tube (114), including a zirconia ceramic isolation tube (113) and a nano aerogel insulation layer (112, 140), which is used to reduce heat loss and control the temperature rise of the outer surface of the chamber.

2. The modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 1, characterized in that: The surface temperature of the metal shell of the experimental chamber (3) is maintained within a safe range of no more than 60°C. Power sockets (310) are distributed on one side of the experimental chamber (3). Multiple sets of experimental chambers (3) are installed at each fan-shaped mounting position on the rotating acceleration disk assembly (4) to perform high-temperature heating experiments in multiple force fields, for simulating microgravity of 0.01g to 1.5g in space and hypergravity of 1g to 10g on the ground.

3. The modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 1, characterized in that: The tubular silicon nitride heat transfer substrate (126) is not limited to a single tubular structure shape, and the tubular silicon nitride heat transfer substrate (126) is disposed inside a zirconia sleeve (124). The zirconia sleeve (124) is fixedly connected to one side of the heated sample holder (122), and a second nano-aerogel insulation layer (140) is distributed around the tubular silicon nitride heat transfer substrate (126).

4. The modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 3, characterized in that: The edge of one side of the heated sample holder (122) is fixedly connected to the opening of the ceramic cover (123) by screws. The middle part of the heated sample holder (122) and the middle part of the ceramic cover (123) are both channel structures, which are used to insert the temperature sensing end of the thermocouple (127) and to discharge the air in the gap during vacuuming.

5. The modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 1, characterized in that: The specific material of the high-temperature resistant vacuum sealing tube (114) is configured according to the target sintering temperature: when the target sintering temperature is below 1200℃, the high-temperature resistant vacuum sealing tube (114) is made of high-purity quartz tube so as to take advantage of its light transmittance for internal observation. When the target sintering temperature is between 1200℃ and 1600℃, the high-temperature resistant vacuum sealing tube (114) is made of high-purity corundum tube or zirconia ceramic tube to ensure structural strength and airtightness under high-temperature conditions.

6. The modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 5, characterized in that: The tube walls of the multi-layer heat insulation structure (110) are filled with a first nano-aerogel heat insulation layer (112). The multi-layer heat insulation structure (110) is specifically composed of the high-temperature resistant vacuum sealing tube (114), the zirconia ceramic isolation tube (113) and the metal tube (111) arranged sequentially from the inside to the outside. The front port of the high-temperature resistant vacuum sealing tube (114) is bolted to the external flange structure of the power supply plug (211) located in the external structural component (2) through the end face sealing structure. The power supply plug (211) is electrically connected to the power supply plug socket (210).

7. A modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 6, characterized in that: The zirconia ceramic isolation tube (113), the first nano-aerogel insulation layer (112), and the second nano-aerogel insulation layer (140) are used to reduce heat loss and control the temperature rise of the outer surface of the experimental chamber (3) and to ensure that the sample temperature reaches 1600℃ in a vacuum high-temperature sintering environment.

8. A modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 6, characterized in that: The end face sealing structure is configured as a detachable structure. When changing samples, only the end face sealing structure needs to be unloaded to insert or remove the internal sample heating unit (120), while the high temperature resistant vacuum sealing tube (114) remains fixed without disassembling the entire tube body, thus ensuring the stability of the vacuum sealing system.

9. A modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 1, characterized in that: The positive and negative terminals of the heating element (125) are electrically connected to plug-in electrodes (121), and the plug-in electrodes (121) are inserted and positioned together with the power supply plug-in socket (210) by means of a locking mechanism (212). A thermocouple (127) is encapsulated in the zirconia ceramic part located in the middle of the power supply plug-in socket (210), and the temperature sensing end of the thermocouple (127) is exposed and in contact with the outer wall of the graphite crucible (130). Two thermocouples (127) are provided to realize synchronous temperature measurement, so as to evaluate the temperature uniformity of the heating area and maintain redundant backup of temperature monitoring when a single thermocouple (127) is abnormal.

10. A modular integrated vacuum high-temperature sintering forming device adapted to multiple force field environments according to claim 9, characterized in that: The heating element (125) is made of platinum-rhodium alloy wire or tungsten-molybdenum alloy material, and is used in conjunction with thermocouple (127) to achieve automatic temperature control, and the temperature value is controllable.

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