Static test device and method for combined main load-bearing structure of satellite

Abstract

The invention discloses a static test device for a satellite combined type main load-bearing structure. A top loading tool is mounted on a top structural plate mounting interface of the satellite combined type main load-bearing structure, and a storage box loading tool is mounted on a storage box mounting interface on a combined type load-bearing cylinder; the loading ring and the partition simulation plate are mounted outside the combined main load-bearing structure; the loading ring is used for loading transverse and longitudinal loads; the number, the installation positions and the structural rigidity of the partition plate simulation plates are the same as those of the partition plates, and the partition plate simulation plates penetrate through and are connected with the loading rings in the axial direction to load longitudinal loads. The invention further discloses a static test method for the satellite combined type main load-bearing structure. The static test method comprises the following steps: simultaneously applying a transverse load and a longitudinal load to the top plate, the storage box loading tool and the loading ring; and applying a longitudinal load to the partition simulation plate. The invention provides a static test method which not only can ensure reasonable and sufficient examination and verification, but also can save development time and economic cost for a large combined satellite, and has important guiding significance for the structural design of a spacecraft.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft structure technology, specifically relating to a static test method that can be used for strength assessment of the main load-bearing structure of a composite satellite. Background Technology

[0002] With the continuous development of structural technology, spacecraft are becoming larger, more complex, and more modular. For the main load-bearing structures of large, modular satellites currently under development, traditional static strength testing methods are based on conducting static tests on the entire spacecraft structure. However, spacecraft structures consist of multiple modules and numerous components, resulting in complex assembly, long design and production cycles, and complex tooling and testing procedures for static tests. Therefore, it is necessary to consider a static testing method with fewer components, simpler implementation, and a shorter cycle time. Summary of the Invention

[0003] The purpose of this invention is to overcome the aforementioned shortcomings and provide a static testing device and method based on the main load-bearing structure of a modular satellite. This solves the technical problems of spacecraft structures having multiple sections, numerous components, complex assembly, long design and production cycles, and complex tooling and testing procedures for static testing. This invention proposes a static testing method for large modular satellites that ensures reasonable and sufficient evaluation and verification while saving development time and economic costs, and has significant guiding significance for the structural design of spacecraft.

[0004] To achieve the above-mentioned objectives, the present invention provides the following technical solution: A static test device for a satellite-type combined main load-bearing structure includes a top loading fixture, a loading ring, and a partition simulation plate; The top loading fixture is installed on top of the combined main load-bearing structure to apply overload to the spacecraft's top equipment; the loading rings and partition simulation plates are installed on the outside of the combined main load-bearing structure; the number and position of the loading rings are the same as those of the horizontal structural plates, and they are used to load lateral and longitudinal loads; the number, position, and structural stiffness of the partition simulation plates are the same as those of the partitions, and the partition simulation plates pass through the axial direction of the combined main load-bearing structure and are fixedly connected to each loading ring to load longitudinal loads.

[0005] Furthermore, it also includes a tank loading fixture, which is installed at the tank interface and used to apply overload loads to the tank.

[0006] Furthermore, the top loading fixture is a conical structure. The bottom of the conical structure is connected to the top of the main load-bearing structure and the partition simulation plate. The height of the conical structure is determined by the position of the total center of mass of the top effective load. A concentrated force is applied to the top of the top loading fixture to simulate the load of the effective load on the main structure.

[0007] Furthermore, corner strips are used to connect the loading ring and the partition simulation plate.

[0008] Furthermore, the loading ring includes an annular region and several angular regions extending outward from the outer side of the annular region, with the angular regions serving as concentrated force loading points; Two angular areas are set at the connection between the loading ring and the partition plate simulation plate to apply lateral and longitudinal loads to the loading surface; the remaining angular areas are only used to apply longitudinal loads; the annular area serves as the connection surface between the loading ring and the combined main load-bearing structure, and is connected to the combined main load-bearing structure by a ring of screws, transferring the combined lateral and longitudinal loads applied by the angular areas to the combined main load-bearing structure. An arc-shaped groove is provided between the angular region and the annular region.

[0009] Furthermore, the number of loaded annular regions is set to n; n is an even number ≥ 4; To ensure that the concentrated force in the angular region is evenly transmitted to the main load-bearing structure, the angular region must be evenly distributed on the ring, and each angular region must be symmetrically provided with an arc groove around its center line, with the circumferential angle of the arc groove set to 120° / n.

[0010] A static testing method for a satellite-mounted composite main load-bearing structure, implemented using the aforementioned static testing device for a satellite-mounted composite main load-bearing structure, includes: S1 applies transverse and longitudinal loads to the loading ring; S2 applies a longitudinal load to the partition simulated plate; S3 test strain and stress at typical locations of combined main load-bearing structures.

[0011] Furthermore, when applying a lateral load to the loading ring, two loading points are set for each loading ring. The positions of the loading points are selected from quadrant lines and are symmetrical about the axis of the combined main load-bearing structure.

[0012] Furthermore, when applying longitudinal loads to the loading ring, the loads are applied to all loading points of the loading ring, and each loading point is evenly distributed along the axis of the load-bearing cylinder; when applying transverse loads to the loading ring, the loads are applied only to the two angular loading points connected to the partition plate simulation plate.

[0013] Furthermore, when applying longitudinal loads to the partition simulation plate, the loads are applied through the loading points of the partition simulation plate.

[0014] This invention discloses a static testing device for a combined main load-bearing structure of a hexahedral plate-box satellite centered on a load-bearing cylinder. The combined main load-bearing structure includes a central load-bearing cylinder and a grid cylinder, excluding the peripheral horizontal structural plates, partitions, and side plates. A top loading fixture is installed at the top structural plate mounting interface of the satellite's combined main load-bearing structure, and a tank loading fixture is installed at the tank mounting interface on the combined load-bearing cylinder. Loading rings and partition simulation plates are installed on the outside of the combined main load-bearing structure. The number and installation position of the loading rings are the same as those of the satellite's horizontal structural plates, and they are used to load transverse and longitudinal loads. The number, installation position, and structural stiffness of the partition simulation plates are the same as those of the partitions. The partition simulation plates pass through and are fixedly connected to each loading ring along the axial direction of the combined main load-bearing structure, and are used to load longitudinal loads. This invention also discloses a static testing method based on the combined satellite main load-bearing structure, including simultaneously applying transverse and longitudinal loads to the top plate, tank loading fixture, and loading rings; and applying a longitudinal load to the partition simulation plates. This invention proposes a static testing method for large combined satellites that can ensure reasonable and sufficient evaluation and verification while saving development time and economic costs, and has important guiding significance for the structural design of spacecraft.

[0015] Compared with the prior art, the present invention has at least one of the following advantages: (1) The present invention uses a partition plate to simulate the plate to share part of the longitudinal load, reasonably simplifies the force transmission path, and more accurately simulates the actual load-bearing state of the combined main load-bearing structure; (2) The present invention utilizes a specially designed loading ring to ensure uniform load on each loading surface and avoid local over-testing; (3) The test piece tested in this invention is only a combined main load-bearing structure, and the tooling design is simple and easy to process and realize. It can replace the static test of the entire satellite of the combined main load-bearing structure, which saves time and costs and has significant economic benefits. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the static testing fixture design scheme of the present invention; Figure 2 This is a schematic diagram of the loading ring of the present invention; Figure 3 This is a schematic diagram of the loading fixture for the internal storage tank of the combined main load-bearing structure of the present invention, wherein (a) is the front view and (b) is the top view. Detailed Implementation

[0017] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0018] 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.

[0019] The modular satellite mentioned in this invention is a hexahedral plate-box structure with a central load-bearing tube and a grid tube assembly as the main load-bearing structure. It mainly consists of the modular main load-bearing structure, horizontal structural plates, partitions, and side plates. The root of the modular main load-bearing structure is the satellite-rocket docking interface. The load transfer of the modular load-bearing structure has three paths: 1) horizontal structural plate – modular main load-bearing structure – satellite-rocket docking interface; 2) side plate – partition – modular main load-bearing structure – satellite-rocket docking interface; 3) storage tank – modular main load-bearing structure – satellite-rocket docking interface. Through force path analysis, it can be seen that the modular main load-bearing structure is the key load-bearing component of this type of spacecraft. Therefore, the static load test of the entire satellite can be replaced by a reasonably designed static load test of the modular main load-bearing structure. The structural plates other than the modular main load-bearing structure can be tested for strength through simple local tests.

[0020] like Figure 1 This invention provides a test load loading fixture, which employs a storage tank loading fixture ( Figure 3 The system comprises a top loading fixture 7, a top loading fixture 6, a first loading ring 2, a second loading ring 3, a third loading ring 4, and a partition simulation plate 5. The tank loading fixture 7, top loading fixture 6, first loading ring 2, second loading ring 3, and third loading ring are all connected to the combined main load-bearing structure 1 via a single ring of screws. The simulated partition is connected to the combined main load-bearing structure via double rows of corner strips. The first loading ring 2, second loading ring 3, third loading ring 4 and the partition simulation plate 5 are connected via double rows of corner strips. The partition simulation plate 5 is manufactured using the same design parameters as the satellite partition, ensuring that the load transfer method of the partition simulation plate 5 is the same as that of the actual satellite partition. This shares some of the longitudinal load with the first loading ring 2, second loading ring 3, and third loading ring 4, preventing severe overload of the loading ring cross-section.

[0021] The loading ring applies load to each loading section through n concentrated force loading points (n≥4). The loading fixture must possess sufficient structural rigidity while ensuring uniform stress distribution across all loading sections. Through optimized design, slots are required at the concentrated force loading points (corner regions) and between the loading points and the connection to the composite main load-bearing structure to prevent direct force transfer to the composite main load-bearing structure. Specific details regarding the slotting method for the fixture are provided below. Figure 2 .

[0022] During the static test, loads were applied through loading points set at the tank loading fixture, the top of the top loading fixture, the loading ring, and the diaphragm simulation plate to simulate overload of equipment installed in different locations. The top loading fixture and the loading ring applied both transverse and longitudinal combined loads, while the diaphragm simulation plate applied only longitudinal loads. The load values ​​for each loading surface were obtained from the actual load distribution on the satellite.

[0023] This invention successfully completed static testing of a large-scale composite main load-bearing structure weighing 6 tons and with a center of gravity 2 meters high. Compared with the actual load-bearing state of a spacecraft, the stress distribution deviation on the composite main load-bearing structure during the static test did not exceed 5%.

[0024] Example: The following is combined Figures 1-3 The test method provided by the present invention will be described in further detail.

[0025] During the test, the tank loading fixture and the top loading fixture applied lateral and longitudinal loads through their loading points. Lateral and longitudinal loads were applied to each loading ring, with two loading points set for the lateral load on each ring, the loading points being selected at the corner areas where the loading ring connects to the partition simulated plate. Longitudinal loads were applied at concentrated loading points in all corner areas of the loading rings. Only longitudinal loads were applied to the partition simulated plate 5; to ensure uniform load distribution on the partition simulated plate 5, multiple loading points could be set for each partition simulated plate. The application of loads at various points simulated the load conditions of the combined main load-bearing structure under the quasi-static design loads of the satellite.

[0026] The loads at each loading surface can be connected through a lever system, and the lever arm of each lever is determined by the magnitude of the two forces to be combined; ultimately, the lateral and longitudinal loads are combined into one or more points (the number of loading points is determined according to the actual number and capacity of the loading equipment).

[0027] In order to bring out the lateral loading fixture of the storage tank from inside the load-bearing cylinder, loading holes need to be set at the corresponding positions during the development of the combined main load-bearing structure.

[0028] 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.

[0029] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A static testing device for a satellite-type combined main load-bearing structure, characterized in that, Includes top loading fixture (6), loading ring and partition simulation plate (5); The top loading fixture (6) is installed on the top of the combined main load-bearing structure to apply overload to the spacecraft's top equipment; the loading ring and the partition simulation plate (5) are installed on the outside of the combined main load-bearing structure; The loading rings are the same in number and position as the horizontal structural plates, and are used to load transverse and longitudinal loads; the partition simulation plate (5) is the same in number, position and structural stiffness as the partition. The partition simulation plate (5) passes through and is fixedly connected to each loading ring along the axial direction of the combined main load-bearing structure, and is used to load longitudinal loads.

2. The static test device for a satellite-type combined main load-bearing structure according to claim 1, characterized in that, The top loading fixture (6) is a conical structure. The bottom of the conical structure is connected to the top of the main load-bearing structure and the partition simulation plate (5). The height of the conical structure is determined by the position of the total center of mass of the top effective load. The top loading fixture (6) applies a concentrated force to simulate the load of the effective load on the main structure.

3. The satellite-type combined main load-bearing structure static test device according to claim 1, characterized in that, An angle bar is used to connect the loading ring and the partition simulation plate (5).

4. The static testing device for a satellite-type combined main load-bearing structure according to claim 1, characterized in that, The loading ring includes an annular region and several angular regions extending outward from the outer side of the annular region, with the angular regions serving as concentrated force loading points; Two angular areas are set at the connection between the loading ring and the partition plate simulation plate to apply lateral and longitudinal loads to the loading surface; the remaining angular areas are only used to apply longitudinal loads; the annular area serves as the connection surface between the loading ring and the combined main load-bearing structure, and is connected to the combined main load-bearing structure by a ring of screws, transferring the combined lateral and longitudinal loads applied by the angular areas to the combined main load-bearing structure. An arc-shaped groove is provided between the angular region and the annular region.

5. The static testing device for a satellite-type combined main load-bearing structure according to claim 1, characterized in that, The number of loaded annular regions is set to n; n is an even number ≥ 4; The angular regions are evenly distributed on the ring, and each angular region is symmetrically arranged with an arc groove about the center line. The circumferential angle of the arc groove is set to 120° / n.

6. The static testing device for a satellite-type combined main load-bearing structure according to claim 1, characterized in that, It also includes a tank loading fixture, which is installed at the tank interface and is used to apply overload loads to the tank.

7. A static test method for a satellite-type combined main load-bearing structure, characterized in that, The static test device for a satellite-type combined main load-bearing structure as described in any one of claims 1-6 is used, comprising: S1 applies transverse and longitudinal loads to the loading ring; S2 applies a longitudinal load to the partition simulation plate (5); S3 test strain and stress at typical locations of combined main load-bearing structures.

8. The static test method for a satellite-type combined main load-bearing structure according to claim 7, characterized in that, When applying a transverse load to the loading ring, two loading points are set for each loading ring. The positions of the loading points are selected from the quadrant lines and are symmetrical about the axis of the combined main load-bearing structure.

9. The static test method for a satellite-type combined main load-bearing structure according to claim 7, characterized in that, When applying longitudinal load to the loading ring, the load is applied to all loading points of the loading ring, and each loading point is evenly distributed along the axis of the load-bearing cylinder; When applying a lateral load to the loading ring, the load is applied only to the two angular loading points connected to the partition simulation plate.

10. A static test method for a satellite-type combined main load-bearing structure according to claim 7, characterized in that, When applying longitudinal load to the partition simulation plate (5), the load is applied through the loading point of the partition simulation plate.

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