A large and medium-sized multi-layer space experimental device with a high payload mass ratio and an installation method

Abstract

The present invention belongs to the technical field of the structural design of space experimental devices. Aiming at the technical problems existing in the design of existing space science payloads, the present invention discloses a medium and large-sized multi-layer space experimental device with a high payload mass ratio and an installation method. The front vertical plate and the bottom plate are connected through the bottom to form an L-shaped structure. The lower frame, the middle layer plate and the upper frame are connected into one body from bottom to top. The lower frame is connected to the bottom plate, and the front end of the upper frame is connected to the inner side of the front vertical plate. The bottom of the front ventilation structure is installed at the front end of the bottom plate, and the upper part of the front ventilation structure is connected to the outer side of the front vertical plate. The notched skin is connected to the front vertical plate, the upper part of the bottom plate, the lower frame and the upper frame in a surrounding form. The upper cover plate is connected to the notched skin, the front vertical plate and the upper frame from above. It realizes diversified functions and the overall and compact design of the structure, and is a multi-layer space experimental device with a high load structure mass ratio, a compact modular partition, easy assembly and debugging, reliable strength, rapid iteration and low cost.

Description

Technical Field

[0001] The present invention belongs to the technical field of the structural design of space experimental devices, and particularly relates to a large and medium-sized multi-layer space experimental device with a high effective payload mass ratio and an installation method therefor. Background Art

[0002] The booming development of space activities will surely give rise to a large number of opportunities for space science / technology experiments, and consequently, a large number of development tasks for space science payloads will follow. Currently, national space experiment requirements are becoming more and more engineering-oriented, with smaller margins for power consumption, machinery, etc., and shorter development cycles. Under the task requirements of high safety, high reliability, and rapid iteration, modular design needs to be carried out. By decomposing a space payload into several independent functional modules, each module is physically and functionally independent, and standard mechanical, electrical, thermal, and data interfaces are used to connect the modules to achieve the overall function of the space payload. The modular space payload structure should be a more compact and lightweight structure, which is faster in assembly, integration, and testing, and the existing design is convenient for reuse.

[0003] The mechanical structure is an important part and the foundation of a space payload, undertaking functions such as withstanding internal and external loads, providing internal and external installation interfaces for the payload, and providing configuration. It is required to maintain a certain stiffness and dimensional stability under the action of various force and thermal environments in the mission profile, not only being able to withstand the extreme launch environment without damage and harmful deformation, but also having the required position and pointing accuracy during on-orbit operation to ensure that the effective payload on it can work properly according to the indicators.

[0004] For the structure of a space payload, its main performance indicators include mass, stiffness, and accuracy. With the development of China's space exploration and space science and other fields, higher requirements are put forward for high-load, lightweight, and high-precision structures. Currently, the typical spacecraft structure forms used in China include shell structures, plate structures, frame structures, support structures, connection structures, and deployable structures, which have relatively mature applications in spacecraft. However, in the structural design of space payloads, especially scientific payloads, due to the monomeric design, mainly in the form of external thick plates with ribs cut and then spliced, and internal local supports, the monomeric piecing-together trace is heavy, the ratio of the structural weight to the effective payload mass is very large, increasing the launch cost; moreover, the internal load integration is relatively poor, and it is not easy to keep the structure deformed uniformly, resulting in an increase in relative error; in addition, the non-modular design is also a luxury for separate debugging by multiple research and development units; finally, some structures are directly installed on the outer plate, resulting in insufficient openness of the space during debugging, small operating space, and thus being not conducive to local modification and correction.

[0005] In the development of existing space science payloads, there is basically no precedent that takes into account both technicality and economy. Therefore, if a beneficial exploration of the structure design and installation of a scientific payload with a compact structure, high payload-to-structure mass ratio, modular partitioning, easy debugging, reliable strength, rapid iteration, and low cost is carried out, it has important practical significance for the future space science payload structure design. Summary of the Invention

[0006] Aiming at the technical problems existing in the design of existing space science payloads, the purpose of the present invention is to develop a multi-layer space experimental device with a high effective payload mass ratio, specifically a multi-layer space experimental device and installation method with a high payload-to-structure mass ratio, compact modular partitioning, easy assembly and debugging, reliable strength, rapid iteration, and low cost.

[0007] The technical solution adopted by the present invention is as follows:

[0008] A multi-layer space experimental device with a high effective payload mass ratio, including a front vertical plate, a bottom plate, a middle layer plate, an upper frame, a lower frame, a notched skin, a front ventilation structure, and an upper cover plate.

[0009] The front vertical plate and the bottom plate are connected through the bottom to form an L-shaped structure. The lower frame, the middle layer plate, and the upper frame are connected into one body from bottom to top, and are divided into upper, middle, and lower three-layer layouts in space. The lower frame is connected to the bottom plate, the front end of the upper frame is connected to the inner side of the front vertical plate, the bottom of the front ventilation structure is installed at the front end of the bottom plate, and the upper part of the front ventilation structure is connected to the outer side of the front vertical plate. The notched skin is connected to the front vertical plate, the upper part of the bottom plate, the lower frame, and the upper frame in a surrounding form, and the upper cover plate is connected to the notched skin, the front vertical plate, and the upper frame from above, thus forming a multi-layer space experimental device with different functional layers in the upper, middle, and lower parts and an external space.

[0010] Further, the bottom plate and the front vertical plate are set as the main support bodies to maintain the strength of the overall structure. The bottom plate and the front vertical plate have a certain thickness and adopt the processing method of structural ribbing, which is used not only for installing the experimental devices arranged thereon but also for structural weight reduction design.

[0011] Further, the middle layer plate has a certain thickness and adopts the processing method of structural ribbing, which is used not only for installing the experimental devices arranged thereon but also for structural weight reduction design. The middle layer plate is connected to the lower frame through through bolts.

[0012] Further, an electrical connector installation hole is processed above the front vertical plate, and installation legs arranged at equal intervals are provided below. The front vertical plate is connected to the bottom plate through the installation legs, and the outer periphery of the front vertical plate is set as a stepped edge, and is connected to the notched skin and the upper cover plate through the stepped edge.

[0013] Further, the bottom plate is arranged in a semi-box structure, with skirts of a certain height around it. The bottom plate is connected to the notch-shaped skin through the skirts; a certain number of mounting lugs are arranged on the outer edge of the bottom plate, and the bottom plate is connected to the aircraft through the lugs.

[0014] Further, the lower frame is arranged as a semi-closed rectangular frame structure composed of horizontal aluminum profiles, vertical aluminum profiles and connecting angle pieces. The bottom and front parts of the lower frame are respectively connected to the bottom plate and the front vertical plate through the connecting angle pieces.

[0015] Further, the upper frame is arranged as a semi-closed rectangular frame structure composed of horizontal aluminum profiles, vertical aluminum profiles and connecting angle pieces. The bottom and front parts of the upper frame are respectively connected to the lower frame and the front vertical plate through the connecting angle pieces. The top of the upper frame can be used for hanging and installing experimental devices.

[0016] Further, the notch-shaped skin is made of a thin plate bent into a notch-shaped thin plate. Riveting strips are respectively installed on its upper part and its lower part. The notch-shaped skin is connected to the left and right sides of the front vertical plate, the outer edge of the bottom plate and the upper cover plate through the riveting strips respectively; groove strips are installed inside all the outer profiles of the upper frame and the lower frame. The upper conductive sealing strip a and the lower conductive sealing strip b are installed through the groove strips, and the notch-shaped thin plate, the upper frame and the lower frame are connected through the conductive sealing strips respectively, which can also ensure the lap joint of the overall structure.

[0017] Further, a first protrusion extends upward at the upper end of the upper riveting strip a, and a second protrusion extends outward at the left end of the upper riveting strip a. The upper side where the first protrusion and the second protrusion are connected forms a first groove; a third protrusion extends downward at the lower end of the upper riveting strip a. The left side where the second protrusion and the third protrusion are connected forms a second groove, and the right side where the third protrusion and the body of the upper riveting strip a are connected forms a third groove 30;

[0018] The upper conductive sealing strip a is horizontally embedded in the first groove, and the top end of the thin skin is vertically embedded in the second groove;

[0019] At the upper end of the lower riveting strip b, an upper protrusion extends upward, and at the lower end of the lower riveting strip b, a lower protrusion extends outward. The intersection of the upper protrusion and the lower protrusion is connected by a horizontal connecting part to form a side "Z" - shaped structure. The upper side where the upper protrusion and the horizontal connecting part are connected forms a fourth groove, and the lower side where the horizontal connecting part and the lower protrusion are connected forms a fifth groove;

[0020] The lower end of the thin skin is connected to the outside of the upper protrusion of the lower riveting strip b, and the lower conductive sealing strip b is vertically embedded in the fifth groove;

[0021] The adjacent two edges of the first groove, the second groove, the third groove, the fourth groove, and the fifth groove are distributed at right angles. The third groove and the fourth groove correspond to each other and have the same recess depth, and the connecting line of their outer edges is on the same horizontal line.

[0022] Further, the front ventilation structure is respectively provided with an upper bracket and a lower bracket from top to bottom. The ventilation equipment is installed through the upper bracket and the lower bracket. The ventilation equipment includes a ventilation heat exchanger and a fan. The ventilation equipment is covered with a metal mesh, which is used for fan ventilation and can also ensure the electromagnetic shielding effect inside and outside the ventilation equipment. The top of the upper bracket is set as an arch-shaped structure, and a ventilation screen is arranged thereon. Installation lugs are arranged on the outer side of the upper bracket and are connected and fixed to the front vertical plate through the installation lugs.

[0023] Further, the upper cover plate is set as a thin plate structure, and the upper cover plate is directly connected to the installation groove bar in the upper frame through a conductive sealing strip.

[0024] An installation method for a large and medium-sized multi-layer space experiment device with a high effective payload mass ratio, characterized in that it specifically includes the following steps:

[0025] (1) Install in the order from component level to module level, that is, first install the scientific experiment instruments on the bottom plate, the middle layer plate and the upper frame respectively and debug them separately;

[0026] (2) Then, connect the front vertical plate to the bottom plate and connect the external ventilation structure to the front vertical plate;

[0027] (3) Then connect the bottom plate, the lower frame, the middle layer plate and the upper frame to each other in sequence, and then connect the necessary electrical, gas and liquid links between each functional module;

[0028] (4) Finally, install the notched skin and the upper cover plate in sequence;

[0029] (5) When it is necessary to debug and adjust the functional module, disassemble it in the reverse order of the above steps.

[0030] The beneficial effects of the present invention are:

[0031] The present invention aims at the mission profile of space science payloads and the special requirements in the development process. It not only fully considers the complex mechanical environment conditions during the launch process and the technical requirements of space volume and device weight (such as weight reduction requirements, rapid iteration, compact structure, and convenient debugging) during the development of payload devices, but also reduces the development cost of scientific devices and shortens the development cycle as much as possible to achieve the feasibility of the comprehensive technology of payload development, the comprehensive balance between reliability and scientific research output, time nodes and economy, and the optimization of benefits. A new technology for the design and installation method of experimental device structure with compact structure, high load structure mass ratio, modular partition, reliable strength and low cost for multi-layer functional partition space suitable for space science experimental payloads is proposed. This technology is suitable for the design of large and medium-sized complex space science payload structures that work in spacecraft, contain multiple functional units, have a short development cycle, and have a small project budget. The space environment applicability, versatility and advantages of its payload structure are mainly reflected in the following aspects:

[0032] (1) High structural strength: The support beam, frame and skin are connected in combination, similar to the design concept of the keel and thin skin combination in current large bridges and large buildings. The front vertical plate and the bottom plate are used as the main support beams. They are connected with the external air duct structure and the frame to support each other and increase the strength. The skins are connected, reinforced, interlocked or inlaid. The skins are connected to the frame through the support plate nut to increase the structural strength of the entire device. Through dynamic design and modal analysis, the first-order natural frequency of the experimental device is greater than 100Hz, and the maximum stress under external mechanical loads such as vibration and impact is less than the yield strength under safe conditions. The structural strength meets the requirements of the mechanical vibration environment conditions of spacecraft launch.

[0033] (2) Multifunctional modular partitioning: The experimental device uses the bottom plate, middle plate and upper frame to divide the space, integrate the scattered components, and use the limited space to strengthen the overall structural rigidity. At the same time, it successfully realizes the installation layout combination of three-layer different experimental systems, which is conducive to dividing the experimental device into more integrated functional modules according to the spatial layout, and is conducive to the integrated and compact design of functions and structures.

[0034] (3) Convenient assembly and debugging: The modular partition and integrated layout facilitate the integrated installation and maintenance of the internal experimental load device, and are also convenient for disassembly and assembly. Convenient debugging is mainly reflected in two levels. First, the modular layout facilitates the separate debugging and disassembly of each functional module; second, once the outer mouth skin and upper cover are disassembled, the entire experimental device is basically exposed, and there is enough operating space from all directions to repair or adjust local components.

[0035] (4) High load-bearing structure mass ratio: The profile itself is a relatively lightweight material, and in addition, the skin within the new type of this experiment is a very thin sheet, which significantly reduces the pure structural weight of the entire device, thereby achieving a high load-bearing structure mass ratio. That is, under the limitation of the total weight, more scientific experimental instruments can be arranged, thus maximizing the scientific experimental function.

[0036] (5) Excellent economy: The structural materials adopt commercial (general model) frame aluminum profiles and aluminum thin sheets, which significantly reduce the structural material and processing costs.

[0037] In summary, the present invention is a main structure design and its installation method applicable to large and medium-sized, complex systems, and large-volume space experimental devices, which can be generally applied to the structural design of relatively complex scientific research and technical test devices on experimental platforms such as space satellites, spacecraft, and space stations, and can also be used for ground-based experimental devices.

[0038] The structural design and load installation integration method of this experimental device have been successfully applied to the design of the space evaporation and condensation scientific experimental device of China's cargo spacecraft, and successfully realized a high-strength experimental device box assembly structure of the combination of support beams, plates, and skins with an effective scientific experimental load mass greater than 76% (40 Kg load mass / 52 Kg total device mass). More experimental systems and scientific instrument loads are integrated and placed under the limitations of limited space scale and weight. On the premise that the structural weight well meets the lightweight requirement, the high stiffness and strength design of its structure itself has withstood the mechanical environment of the spacecraft's launch into orbit, and successfully completed various on-orbit scientific experiments in space. Brief Description of the Drawings

[0039] Figure 1 It is a schematic diagram of the overall internal structure of the present invention.

[0040] Figure 2 It is a schematic diagram of the overall external structure of the present invention.

[0041] Figure 3 It is a schematic diagram of the structure of the lower frame of the present invention.

[0042] Figure 4 It is a partial structural schematic diagram of the notch-shaped skin of the present invention.

[0043] Figure 5 It is a structural schematic diagram of the front ventilation structure of the present invention.

[0044] Figure 6 It is a schematic diagram of the mechanical simulation model of the experimental device of the present invention.

[0045] Figure 7 It is a schematic diagram of the vibration simulation result of the experimental device of the present invention.

[0046] Among them, 1. front vertical plate; 2. bottom plate; 3. middle layer plate; 4. upper frame; 5. lower frame; 6. notch-shaped skin; 7. front ventilation structure; 8. upper cover plate; 9. aluminum alloy profile; 10. connecting angle piece; 11. groove strip; 12. vibration isolation pad; 13. thin skin of the skin; 14. upper riveting strip a; 15. lower riveting strip b; 16. upper conductive sealing strip a; 17. lower conductive sealing strip b; 18. upper bracket; 19. mounting lug; 20. lower bracket; 21. ventilation screen; 22. first protrusion; 23. second protrusion; 24. third protrusion; 25. upper protrusion; 26. lower protrusion; 27. horizontal connecting part; 28. first groove; 29. first groove; 30. second groove; 31. third groove; 32. fourth groove; 33. fifth groove. Detailed implementation mode

[0047] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention. It should be noted that in this article, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Terms such as "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Terms such as "include" and "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent in such process, method, article or device. Without further limitation, elements defined by the statement "including..." do not exclude the existence of additional identical elements in the process, method, article or device including the said elements.

[0048] Embodiment 1:

[0049] As Figure 1 and Figure 2As shown, a large and medium-sized multi-layer space experimental device with a high effective load mass ratio is composed of a front vertical plate 1, a bottom plate 2, a middle plate 3, an upper frame 4, a lower frame 5, a notch-shaped skin 6, a front ventilation structure 7 and an upper cover plate 8. The front vertical plate 1 and the bottom plate 2 are connected to form an L-shaped structure through the bottom, and the lower frame 5, the middle plate 3 and the upper frame 4 are connected from bottom to top as a whole. When the experimental device is installed, the lower frame 5 is connected to the bottom plate 2, and the front end of the upper frame 4 is connected to the inner side of the front vertical plate 1. When the front ventilation structure 7 is installed, the bottom is installed at the front end of the bottom plate 2, and the upper part is connected to the outer side of the front vertical plate 1. The notch-shaped skin 6 is connected to the front vertical plate 1, the upper part of the bottom plate 2, the lower frame 5, and the upper frame 4 in a semi-enclosed form. The upper cover plate 8 is connected to the notch-shaped skin 6, the front vertical plate 1, and the upper frame 4 from above, thereby forming a multi-functional module partition and integrated layout multi-layer space experimental device structure.

[0050] The front vertical plate 1 and the bottom plate 2 are used as the main supporting beams, and are connected with the notch-shaped skin 6, the upper frame 4, and the lower frame 5. They are connected with the external air duct structure and the frame to support each other and increase the strength. The notch-shaped skin 6 is connected, reinforced, bitten or inlaid. The notch-shaped skin 6 is connected with the upper frame 4 and the lower frame 5 to increase the structural strength of the entire device. The bottom plate 2, the middle plate 3, and the upper frame 4 are used to divide the space, strengthen the overall structural rigidity, and successfully realize the installation of different experimental systems on the three internal layers and the combination of external equipment layout, realize diversified functions and structural integration and compact design, thus forming a multi-functional module partition, overall layout of the structural beam and skin combination multi-layer space experimental device structure.

[0051] In another embodiment of the present invention, the interior of the space experiment device is structurally divided into a three-layer layout of upper, middle and lower layers and a space for placing external equipment. The interior is installed as an integral assembly structure of a frame plus a skin outer panel, so that the space experiment device is divided into three relatively integrated functional modules according to the spatial layout, realizing an integrated and compact design of function and structure. The bottom plate 2 and the front vertical plate 1 serve as the main supporting bodies to maintain the strength of the overall structure, and are connected to the external air duct structure 7, the upper frame 4 and the lower frame 5 to support each other and increase strength. The bottom plate 2 and the front vertical plate 1 have a certain thickness and are processed by structural ribs, which are used for installing the experimental devices arranged thereon and also as a structural weight reduction design.

[0052] In another embodiment of the present invention, an electrical connector mounting hole is processed on the front vertical plate 1 for installing a through-board electrical connector to realize electrical connection inside and outside the experimental device. Below the front vertical plate 1 are three mounting legs at equal intervals for connection with the bottom plate 2. The outer periphery of the front vertical plate 1 is a stepped edge for connection with the notched skin 6 and the upper cover plate 8. Such a stepped edge is a stop design, which is conducive to ensuring the electromagnetic shielding performance of the entire experimental device.

[0053] In another embodiment of the present invention, the bottom plate 2 adopts a semi-box design. Its bottom is used to install scientific experiment modules. There are skirts with a certain height around the bottom plate 2, and these skirts are also stepped edges, which are used to connect with the notch-shaped skin 6. The rabbet design is beneficial to ensuring the electromagnetic shielding performance of the entire experimental device. The outermost edge at the bottom of the bottom plate 2 has a certain number of mounting lugs for connecting with the aircraft.

[0054] In another embodiment of the present invention, as Figure 3 shown, the lower frame 5 is composed of horizontal aluminum profiles 9, vertical aluminum profiles 9 and connecting angle pieces 10 to form a semi-closed rectangular frame structure. The bottom and the front part of the lower frame 5 are respectively connected to the bottom plate 2 and the front vertical plate 1 through connecting angle pieces. The height of the lower frame 5 is mainly designed according to the maximum height and operability of the scientific function modules to be installed.

[0055] Similar to the lower frame 5, the upper frame 4 is composed of horizontal aluminum profiles, vertical aluminum profiles and connecting angle pieces to form a semi-closed rectangular frame structure. The bottom and the front part of the upper frame 4 are respectively connected to the lower frame 5 and the front vertical plate 1 through connecting angle pieces. The top of the upper frame 5 can be used for hanging and installing the experimental device and the internal cable routing space of the experimental device.

[0056] Installation groove strips 11 are installed inside all the outer profiles 9 of the upper frame 4 and the lower frame 5, and conductive sealing strips are installed on the groove strips, which are used for connecting the notch-shaped skin 6 with the upper frame 4 and the lower frame 5, and can also ensure the lap joint of the overall structure.

[0057] In another embodiment of the present invention, the middle layer plate 3 has a certain thickness and adopts the processing method of structural ribbing, which is used for installing the experimental device arranged thereon and also serves as a structural weight reduction design. A vibration isolation pad 12 is placed below the middle layer plate 3 and is connected to the lower frame 5 through through bolts. The vibration isolation pad 12 is used for the overall shock absorption of the scientific instruments on the middle layer plate 3 to ensure the relative accuracy of the scientific instruments above remains consistent.

[0058] In another embodiment of the present invention, as Figure 4 shown, the notch-shaped skin 6 is formed by bending sheet metal into a notch-shaped thin plate 13. An upper riveting strip a14 and a lower riveting strip b15 are respectively installed on its upper part and its lower part. To ensure the overall electromagnetic shielding performance of the experimental device, conductive sealing strips a16 and conductive sealing strips b17 are arranged on the upper plane of the upper riveting strip a14 and the inner vertical surface of the lower riveting strip b15.

[0059] As Figure 4 shown, the specific installation structure of the notch-shaped skin:

[0060] The upper riveting strip a14 is arranged in a "Z" - shaped structure. At the upper end of the upper riveting strip a14, a first protrusion 22 extends upward. At the left end of the upper riveting strip a14, a second protrusion 23 extends outward. The upper side where the first protrusion 22 and the second protrusion 23 are connected forms a first groove 28;

[0061] At the lower end of the upper riveting strip a14, a third protrusion 24 extends downward. The left side where the second protrusion 23 and the third protrusion 24 are connected forms a second groove 29. The right side where the third protrusion 24 and the body of the upper riveting strip a14 are connected forms a third groove 30;

[0062] The upper conductive sealing strip a16 is horizontally embedded in the first groove 28. The top end of the thin skin panel 13 is vertically embedded in the second groove 29;

[0063] At the upper end of the lower riveting strip b15, an upper protrusion 25 extends upward. At the lower end of the lower riveting strip b15, a lower protrusion 26 extends outward. The junction of the upper protrusion 25 and the lower protrusion 26 is connected by a horizontal connecting part 27 to form a side "Z" - shaped structure. The upper side where the upper protrusion 25 and the horizontal connecting part 27 are connected forms a fourth groove 31. The lower side where the horizontal connecting part 27 and the lower protrusion 26 are connected forms a fifth groove 32;

[0064] The lower end of the thin skin panel 13 is connected to the outside of the upper protrusion 25 of the lower riveting strip b15. The lower conductive sealing strip b17 is vertically embedded in the fifth groove 32.

[0065] The first groove 28, the second groove 29, the third groove 30, the fourth groove 31, and the fifth groove 32 are all arranged in an "L" - shaped structure, and the adjacent two edges of each groove are at a right - angle distribution. The third groove 30 and the fourth groove 31 correspond to each other and have the same depression depth, and the connection line of their outer edges is on the same horizontal line.

[0066] The upper riveting strip a14 and the lower riveting strip b15 have two functions. Threaded holes can be arranged on the upper plane of the upper riveting strip a14 for connecting with the upper cover plate 8. Through - holes can be arranged on the outside of the lower riveting strip b15 for connecting with the bottom plate 2 and the front vertical plate 1; In addition, the rabbet design of the upper riveting strip a14 and the lower riveting strip b15 is beneficial to ensuring the electromagnetic shielding performance of the entire experimental device.

[0067] Another embodiment of the present invention, as Figure 5As shown in the figure, the front ventilation structure 7 is used to install ventilation equipment, and its structure consists of an upper bracket 18, mounting lugs 19, a lower bracket 20, and a ventilation screen 21. The upper bracket 18 and the lower bracket 20 serve as support keels. After installing the ventilation heat exchanger and the fan on the bracket, they are connected and fixed to the front vertical plate 1 through the mounting lugs 19 to ensure the structural strength of the entire front ventilation structure. The outer metal ventilation screen 21 is covered, and the thickness of the screen does not exceed 0.5 mm. It is used for fan ventilation, with air entering from the screen at the upper bracket and exiting from the screen at the upper bracket, dissipating the excess heat inside the experimental device to the outside of the box, and can also ensure the electromagnetic shielding effect inside and outside the ventilation equipment.

[0068] In another embodiment of the present invention, the upper cover plate 8 is a thin plate structure and is directly connected to the mounting groove strip inside the upper frame through a conductive sealing strip a16.

[0069] The installation method of the large and medium-sized multi-layer space experimental device with a high effective payload mass ratio specifically includes the following steps:

[0070] (1) Install in the order from component level to module level, that is, first install the scientific experimental instruments on the bottom plate 2, the middle layer plate 3, and the upper frame 4 respectively and debug them separately;

[0071] (2) Then, connect the front vertical plate 1 to the bottom plate 2 and connect the external ventilation structure 7 to the front vertical plate 1;

[0072] (3) Then connect the bottom plate 2, the lower frame 5, the middle layer plate 3, and the upper frame 4 to each other in sequence, and then connect the necessary electrical, gas, and liquid links between the various functional modules;

[0073] (4) Finally, install the notched skin 6 and the upper cover plate 8 in sequence;

[0074] (5) When it is necessary to debug and adjust the functional modules, disassemble them in the reverse order of the above steps.

[0075] In summary, the mechanical structure of the space experimental device of the present invention, for space science payloads working inside a spacecraft, containing multiple functional units, with a short development cycle and a relatively small project budget, considering various aspects such as technical feasibility, reliability, scientific research output, time nodes, and economy, realizes a structural design and installation method of a multi-layer space experimental device with high structural strength, high payload-to-structure mass ratio, modular partitioning, facilitating debugging, and low cost.

[0076] As Figure 6 and Figure 7 shown, through the simulation analysis under the launch test conditions, the maximum stress values are all less than the yield strength of 212.5 MPa under the safety conditions, and the structural strength meets the design requirements.

[0077] Table 1. Maximum stress of the load device obtained from simulation analysis under various test conditions

[0078]

[0079] This technical solution has been successfully applied to the design of the space evaporation and condensation scientific experiment device of the first cargo spacecraft in China's manned space engineering, and successfully realized a high-strength experimental device box body composed of support beams, plates and skins with an effective scientific experiment payload mass greater than 76%. Under the premise of well meeting the lightweight requirement of the structural weight, the design of high structural stiffness and strength has withstood the mechanical environment of the spacecraft's launch into orbit and successfully completed various on-orbit scientific experiments in space.

[0080] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A large and medium-sized multi-layer space experimental device with a high payload mass ratio, Characterized in that, It includes a front vertical plate, a bottom plate, a middle layer plate, an upper frame, a lower frame, a notched skin, a front ventilation structure, and an upper cover plate. The front vertical plate and the bottom plate are connected by the bottom to form an L-shaped structure. The lower frame, the middle layer plate, and the upper frame are connected into one body from bottom to top, and are spatially divided into upper, middle, and lower three-layer layouts. The lower frame is connected to the bottom plate, the front end of the upper frame is connected to the inner side of the front vertical plate, the bottom of the front ventilation structure is installed at the front end of the bottom plate, and the upper part of the front ventilation structure is connected to the outer side of the front vertical plate. The notched skin is connected to the front vertical plate, the upper part of the bottom plate, the lower frame, and the upper frame in a surrounding form. The upper cover plate is connected to the notched skin, the front vertical plate, and the upper frame from above, thus forming a multi-layer space experimental device with different functional layers in the upper, middle, and lower parts and an external space.

2. The large and medium-sized multi-layer space experimental device with a high payload mass ratio according to claim 1, Characterized in that, An electrical connector installation hole is processed above the front vertical plate, and installation legs arranged at equal intervals are provided below. The front vertical plate is connected to the bottom plate through the installation legs. The outer periphery of the front vertical plate is provided with a stepped edge, and is connected to the notched skin and the upper cover plate through the stepped edge.

3. The large and medium-sized multi-layer space experimental device with a high payload mass ratio according to claim 1, Characterized in that, The bottom plate is set as a semi-box structure, and its periphery is provided with skirts with a certain height. The bottom plate is connected to the notched skin through the skirts; a certain number of installation lugs are arranged on the outer edge of the bottom plate and are connected to the aircraft through the lugs.

4. The large and medium-sized multi-layer space experimental device with a high payload mass ratio according to claim 1, Characterized in that, The lower frame is set as a semi-closed rectangular frame structure composed of horizontal aluminum profiles, vertical aluminum profiles, and connecting angle pieces. The bottom and the front of the lower frame are respectively connected to the bottom plate and the front vertical plate through the connecting angle pieces.

5. The large and medium-sized multi-layer space experimental device with a high payload mass ratio according to claim 1, Characterized in that, The upper frame is set as a semi-closed rectangular frame structure composed of horizontal aluminum profiles, vertical aluminum profiles, and connecting angle pieces. The bottom and the front of the upper frame are respectively connected to the lower frame and the front vertical plate through the connecting angle pieces.

6. The large and medium-sized multi-layer space experimental device with a high payload mass ratio according to claim 1 or 4 or 5, Characterized in that, The notched skin is made of a thin plate bent into a notched thin plate. An upper riveting strip a and a lower riveting strip b are respectively installed on its upper part and its lower part, and are connected to the left and right sides of the front vertical plate, the outer edge of the bottom plate, and the upper cover plate through the upper riveting strip a and the lower riveting strip b respectively; installation grooves are installed inside all the outer profiles of the upper frame and the lower frame, and an upper conductive sealing strip a and a lower conductive sealing strip b are installed through the grooves, and are connected to the notched thin plate, the upper frame, and the lower frame through the conductive sealing strips respectively.

7. The large and medium-sized multi-layer space experimental device with a high payload mass ratio according to claim 6, Characterized in that, The upper end of the upper riveting strip a extends upward to form a first protrusion, and the left end of the upper riveting strip a extends outward to form a second protrusion. The upper side portion where the first protrusion and the second protrusion are connected forms a first groove; the lower end of the upper riveting strip a extends downward to form a third protrusion. The left side portion where the second protrusion and the third protrusion are connected forms a second groove, and the right side portion where the third protrusion is connected to the body of the upper riveting strip a forms a third groove; The upper conductive sealing strip a is horizontally embedded in the first groove, and the top end of the thin skin plate is vertically embedded in the second groove; The upper end of the lower riveting strip b extends upward to form an upper protrusion, and the lower end of the lower riveting strip b extends outward to form a lower protrusion. The junction of the upper protrusion and the lower protrusion is connected by a horizontal connecting portion to form a side "Z" - shaped structure. The upper side portion where the upper protrusion is connected to the horizontal connecting portion forms a fourth groove, and the lower side portion where the horizontal connecting portion is connected to the lower protrusion forms a fifth groove; The lower end of the thin skin plate is connected to the outside of the upper protrusion of the lower riveting strip b, and the lower conductive sealing strip b is vertically embedded in the fifth groove; The adjacent two edges between the first groove, the second groove, the third groove, the fourth groove, and the fifth groove are distributed at right angles. The third groove and the fourth groove correspond to each other and have the same recess depth, and the connecting line of their outer edges is on the same horizontal line.

8. The large - medium - sized multi - layer space experimental device with a high payload mass ratio according to claim 1, wherein, The front ventilation structure is provided with an upper bracket and a lower bracket from top to bottom. Ventilation equipment is installed through the upper bracket and the lower bracket. The ventilation equipment includes a ventilation heat exchanger and a fan, and the ventilation equipment is covered with a metal mesh; the top of the upper bracket is set as an arch - shaped structure, and a ventilation screen is arranged thereon. Installation lugs are arranged on the outside of the upper bracket and are connected and fixed to the front vertical plate through the installation lugs.

9. The large - medium - sized multi - layer space experimental device with a high payload mass ratio according to claim 1, wherein, The upper cover plate is set as a thin plate structure, and the upper cover plate is directly connected to the installation groove strip in the upper frame through a conductive sealing strip.

10. An installation method for the large - medium - sized multi - layer space experimental device with a high payload mass ratio according to any one of claims 1 - 9, wherein, Specifically, it includes the following steps: (1) Install in the order from component - level to module - level, that is, first install the scientific experimental instruments on the bottom plate, the middle - layer plate, and the upper frame respectively and debug them respectively; (2) Then, connect the front vertical plate to the bottom plate and connect the external ventilation structure to the front vertical plate; (3) Then connect the bottom plate, the lower frame, the middle - layer plate, and the upper frame to each other in sequence, and then connect the necessary electrical, gas, and liquid links between each functional module; (4) Finally, install the notched skin and the upper cover plate in sequence; (5) When it is necessary to debug and adjust the functional module, disassemble it in the reverse order of the above steps.

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