Expansion support for vibration test of flat satellite
By designing an extended support for the vibration test of flat-plate satellites, the problems of large volume, complex structure, and high cost of vibration test fixtures for large aerospace products were solved, enabling effective vibration testing under limited testing environments and tight schedules.
Patent Information
- Application Number
- CN202423320442.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-31
- Publication Date
- 2026-02-24
- Estimated Expiration
- 2034-12-31
AI Technical Summary
Existing vibration testing fixtures for large aerospace products are large in size, complex in structure, difficult to manufacture, and costly, making it difficult to conduct effective vibration tests under limited testing environments and tight schedules.
Design a plate satellite vibration test extension support, including a base, a support surface and a support part, which are connected by support ribs to form a basin-shaped structure to expand the load-bearing capacity of the vibration test bench. The support part is used to install and fix the satellite to be tested, and the base part is fixed to the vibration test bench.
Under limited testing environment and tight schedule, it can effectively expand the load-bearing capacity of vibration test bench, realize vibration testing of large aerospace products, and reduce manufacturing difficulty and cost.
Smart Images
Figure CN223940489U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of vibration testing technology, and in particular to an extended support for vibration testing of flat-plate satellites. Background Technology
[0002] Currently, the test fixtures used for vibration testing of large aerospace products, such as rockets and satellites, are mostly large forgings. To meet rigidity and weight requirements, these large test fixtures are generally bulky, complex in structure, difficult to form during manufacturing, have long manufacturing cycles, and extremely high overall costs. Therefore, conducting vibration tests under the premise of limited test environment area and tight schedule is an urgent problem to be solved in this field. Summary of the Invention
[0003] This utility model provides an extended support for a flat-plate satellite vibration test, which includes a base, a support surface, support ribs, and a support portion. The support surface extends obliquely upward from the edge of the base, and several support surfaces and the base form a basin shape. The support ribs connect the base and the support surface, and the base and the support portion. The support portion is located above the base and is used to install and fix the satellite to be tested. The base is used to assemble with a vibration test bench.
[0004] Furthermore, the chassis includes a chassis body, a first bottom edge beam, a second bottom edge beam, and a third bottom edge beam. The first bottom edge beam, the second bottom edge beam, and the third bottom edge beam are respectively located on the edge of the chassis body and are fixedly connected to the chassis body. The first bottom edge beam, the second bottom edge beam, and the third bottom edge beam form a triangle. The chassis body is used for relative installation and fixation with the vibration test bench.
[0005] Furthermore, the supporting surface includes a first facade, a second facade, and a third facade. The first facade is formed by extending obliquely upward from the first bottom edge beam. The second facade is formed by extending obliquely upward from the second bottom edge beam. The third facade is formed by extending obliquely upward from the third bottom edge beam. The left and right ends of the first facade are connected to the second facade and the third facade, respectively. The left and right ends of the second facade are connected to the first facade and the third facade, respectively. The left and right ends of the third facade are connected to the first facade and the second facade, respectively.
[0006] Furthermore, it also includes a first top edge beam, a second top edge beam, and a third top edge beam. The first top edge beam is located at the top of the first facade and is fixedly connected to the first facade. The second top edge beam is located at the top of the second facade and is fixedly connected to the second facade. The third top edge beam is located at the top of the third facade and is fixedly connected to the third facade. The first top edge beam, the second top edge beam, and the third top edge beam form a triangle.
[0007] Furthermore, the first top edge beam is arranged parallel to the first bottom edge beam, the second top edge beam is arranged parallel to the second bottom edge beam, and the third top edge beam is arranged parallel to the third bottom edge beam.
[0008] Furthermore, it also includes a first reinforcing plate and a second reinforcing plate, the two ends of the first reinforcing plate being integrally connected to the first top edge beam and the third top edge beam, respectively, and the two ends of the second reinforcing plate being integrally connected to the second top edge beam and the third top edge beam, respectively.
[0009] Furthermore, the support portion includes a first support, a second support, and a third support. The first support is located at the connection between the first facade and the second facade, the second support is located at the connection between the second facade and the third facade, and the third support is located at the connection between the third facade and the first facade. The first support, the second support, and the third support are respectively provided with inverted conical supports for mounting and fixing the satellite under test.
[0010] Furthermore, the inverted cone support includes an inverted cone top surface, an inverted cone bottom surface, an inverted cone reinforcing rib, and an inverted cone body. The inverted cone top surface is used to connect with the satellite under test and is located at the top of the inverted cone support. The inverted cone bottom surface is used to connect with the support portion and is located at the bottom of the inverted cone support. The inverted cone reinforcing rib is connected between the inverted cone top surface and the inverted cone bottom surface. The inverted cone body is connected between the inverted cone top surface, the inverted cone bottom surface, and the inverted cone reinforcing rib.
[0011] Furthermore, the supporting rib includes a cylindrical portion, a first rib, a second rib, and a third rib. The first rib, the second rib, and the third rib are radially arranged around the periphery of the cylindrical portion. One end of the first rib is connected to the cylindrical portion, and the other end of the first rib is connected to the first vertical surface. One end of the second rib is connected to the cylindrical portion, and the other end of the second rib is connected to the second vertical surface. One end of the third rib is connected to the cylindrical portion, and the other end of the first rib is connected to the first vertical surface.
[0012] Furthermore, the supporting ribs also include a fourth rib, a fifth rib, and a sixth rib. The fourth rib, the fifth rib, and the sixth rib are arranged radially around the periphery of the cylindrical portion. One end of the fourth rib is connected to the cylindrical portion, and the other end of the fourth rib is connected to the first support. One end of the fifth rib is connected to the cylindrical portion, and the other end of the fifth rib is connected to the second support. One end of the sixth rib is connected to the cylindrical portion, and the other end of the sixth rib is connected to the third support.
[0013] The flat-plate satellite vibration test extension support provided by this utility model is made into an extension tooling with rigidity and weight that meets the test requirements by forming a basin-shaped support surface and a base, and a support rib connecting the base and the support surface. For test environments where the vibration test bench itself is small and the test environment area is limited, placing the flat-plate satellite vibration test extension support of this utility model on the vibration test bench can effectively expand the size of the satellite to be tested that the vibration test bench can support, thereby realizing vibration testing of large aerospace products under the premise of limited test environment area and tight schedule. Attached Figure Description
[0014] Figure 1 A top view of the extended support for the vibration test of a flat satellite provided by this utility model.
[0015] Figure 2 This is a bottom view of the extended support for the flat-plate satellite vibration test in this utility model.
[0016] Figure 3 This is a side view of the extended support for the flat-plate satellite vibration test in this utility model.
[0017] Figure 4 This is a schematic diagram of the chassis, support, support surface, and support ribs in this utility model.
[0018] Figure 5 This is a schematic diagram of the inverted cone support in this utility model. Detailed Implementation
[0019] To further illustrate the technical means and effects adopted by this utility model in order to achieve the intended purpose of the invention, the present utility model will be described in detail below with reference to the accompanying drawings and preferred embodiments.
[0020] It should be noted that the terms "first," "second," "third," "fourth," etc., in the specification and claims of this utility model are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence.
[0021] Please see Figures 1 to 3The extended support for the vibration test of a flat-plate satellite provided by this utility model includes a base 1, a support surface 2, support ribs 3, and a support portion 4. The support surface 2 extends upward and outward from the edge of the base 1, forming a basin shape with a smaller bottom and a larger top with several support surfaces 2 and the base 1. The support ribs 3 connect the base 1 and the support surface 2, and the base 1 and the support portion 4. The support portion 4 is located above the base 1 and is used to install and fix the satellite under test. The base 1 is used for assembly with the vibration test bench. Specifically, in this embodiment, the base 1 is provided with connecting holes for relative installation and fixing with the vibration test bench. The extended support for the vibration test of the flat-plate satellite can be installed and fixed on the vibration test bench through the base 1 and corresponding bolts. The support portion 4 is provided with connecting holes for relative installation and fixing with the satellite under test. The extended support for the vibration test of the flat-plate satellite can be installed and fixed with the satellite under test through the support portion 4 and corresponding bolts. The satellite under test is a flat-plate stacked satellite. The vibration test bench is a Hill 20T vibration table. The flat-plate satellite vibration test extension support of this utility model can be applied to vibration test fixtures used for large aerospace products. In actual use, the base part 1 is fixed relative to the vibration test stand, and the support part 4 is fixed relative to the satellite under test, thus completing the relative fixation between the satellite under test and the vibration test stand. For test environments where the vibration test stand itself is small and the test area is limited, placing the flat-plate satellite vibration test extension support of this utility model on the vibration test stand can effectively expand the size of the satellite under test that the vibration test stand can support, thereby enabling vibration testing of large aerospace products under the premise of limited test area and tight schedule.
[0022] Furthermore, the chassis part 1 in this utility model includes a chassis body 11, a first bottom edge beam 1a, a second bottom edge beam 1b, and a third bottom edge beam 1c. The first bottom edge beam 1a, the second bottom edge beam 1b, and the third bottom edge beam 1c are located at the edge of the chassis body 11 and are fixedly connected to the chassis body 11. The first bottom edge beam 1a, the second bottom edge beam 1b, and the third bottom edge beam 1c form a triangle. The support surface 2 is obtained by extending upward and outward from the first bottom edge beam 1a, the second bottom edge beam 1b, and the third bottom edge beam 1c respectively. The chassis body 11 is used for relative installation and fixation with the vibration test bench. Specifically, in this embodiment, the first bottom beam 1a, the second bottom beam 1b, and the third bottom beam 1c are connected sequentially to form an isosceles triangle. The first bottom beam 1a and the second bottom beam 1b are the legs, and the third bottom beam 1c is the base. The first bottom beam 1a, the second bottom beam 1b, and the third bottom beam 1c are also the three sides of the chassis body 11, meaning the chassis body 11 is also an isosceles triangle. In particular, when manufacturing the flat-plate satellite vibration test extension support of this utility model, the first bottom beam 1a, the second bottom beam 1b, and the third bottom beam 1c are all embedded as keels in the casting mold. This arrangement allows the keels to ensure that the bottom of the flat-plate satellite vibration test extension support of this utility model possesses both structural strength and casting convenience during casting.
[0023] Furthermore, the support surface 2 in this utility model includes a first elevation 2a, a second elevation 2b, and a third elevation 2c. The first elevation 2a is formed by extending obliquely upward from the first bottom edge beam 1a, the second elevation 2b is formed by extending obliquely upward from the second bottom edge beam 1b, and the third elevation 2c is formed by extending obliquely upward from the third bottom edge beam 1c. The left and right ends of the first elevation 2a are connected to the second elevation 2b and the third elevation 2c, respectively. The left and right ends of the second elevation 2b are connected to the first elevation 2a and the third elevation 2c, respectively. The left and right ends of the third elevation 2c are connected to the first elevation 2a and the second elevation 2b, respectively. Specifically, in this embodiment, the first elevation 2a, the second elevation 2b, and the third elevation 2c are located on the same side of the chassis body 11, and the included angles formed between them and the chassis body 11 are all obtuse angles. That is to say, the first elevation 2a, the second elevation 2b, the third elevation 2c, and the chassis body 11 form a basin-shaped groove with an upward opening, a smaller bottom, and a larger top. The top and bottom edges of the first facade 2a, the second facade 2b, and the third facade 2c are all isosceles triangles. Several weight-reducing holes are provided on each of the three facades to reduce weight. This utility model's flat-plate satellite vibration test extension support utilizes a basin-shaped groove structure with an upward-facing opening, a smaller bottom, and a larger top to respond to and amplify vibrations generated by existing vibration test benches. This allows for vibration testing of larger satellites using a smaller vibration test bench, resulting in good economic benefits.
[0024] Furthermore, the extended support for the vibration test of the flat satellite in this utility model also includes a first top edge beam 5a, a second top edge beam 5b, and a third top edge beam 5c. The first top edge beam 5a is located at the top of the first facade 2a and is fixedly connected to the first facade 2a. The second top edge beam 5b is located at the top of the second facade 2b and is fixedly connected to the second facade 2b. The third top edge beam 5c is located at the top of the third facade 2c and is fixedly connected to the third facade 2c. The first top edge beam 5a, the second top edge beam 5b, and the third top edge beam 5c form a triangle. Specifically, in this embodiment, the first top edge beam 5a, the second top edge beam 5b, and the third top edge beam 5c are connected in sequence to form an isosceles triangle, with the first top edge beam 5a and the second top edge beam 5b as the legs and the third top edge beam 5c as the base. This isosceles triangle is similar to the isosceles triangle formed by the first bottom edge beam 1a, the second bottom edge beam 1b, and the third bottom edge beam 1c. Therefore, the first top edge beam 5a is parallel to the first bottom edge beam 1a, the second top edge beam 5b is parallel to the second bottom edge beam 1b, and the third top edge beam 5c is parallel to the third bottom edge beam 1c. Furthermore, since the first facade 2a, the second facade 2b, the third facade 2c, and the chassis body 11 form a basin-shaped groove structure with a smaller bottom and a larger top, the length of the first top edge beam 5a is greater than the length of the first bottom edge beam 1a, the length of the second top edge beam 5b is greater than the length of the second bottom edge beam 1b, and the length of the third top edge beam 5c is greater than the length of the third bottom edge beam 1c. The shapes of the first facade 2a, the second facade 2b, and the third facade 2c are all trapezoidal. Specifically, in manufacturing the flat satellite vibration test extension support of this utility model, the first top edge beam 5a, the second top edge beam 5b, and the third top edge beam 5c are also embedded as keels within the casting mold. This arrangement allows the keels to ensure that the top of the flat satellite vibration test extension support of this utility model possesses both structural strength and casting convenience during casting.
[0025] Furthermore, the support portion 4 in this utility model includes a first support 4a, a second support 4b, and a third support 4c. The first support 4a is located at the connection between the first facade 2a and the second facade 2b, the second support 4b is located at the connection between the second facade 2b and the third facade 2c, and the third support 4c is located at the connection between the third facade 2c and the first facade 2a. The first support 4a, the second support 4b, and the third support 4c are respectively provided with inverted conical supports 7 for mounting and fixing the satellite to be tested. Specifically, in this embodiment, the first support 4a is located between the connection between the first facade 2a and the second facade 2b, and between the connection between the first bottom beam 1a and the second bottom beam 1b and the connection between the first top beam 5a and the second top beam 5b. The second support 4b is located between the connection between the second facade 2b and the third facade 2c, and between the connection between the second bottom beam 1b and the third bottom beam 1c and the connection between the second top beam 5b and the third top beam 5c. The third support 4c is located between the connection between the third facade 2c and the first facade 2a, and between the connection between the third bottom beam 1c and the first bottom beam 1a and the connection between the third top beam 5c and the first top beam 5a. It is easily understood that since the first top beam 5a, the second top beam 5b, and the third top beam 5c form an isosceles triangle, and the first top beam 5a, the second top beam 5b, and the third top beam 5c also form an isosceles triangle, the second support 4b and the third support 4c are symmetrically arranged at both ends of the third facade 2c. Furthermore, such as Figure 4 As shown, the support part 4 includes a support top surface 41 located at its top and a support ramp surface located on the side facing the basin-shaped groove structure. The support top surface 41 is provided with a connecting hole for installing the inverted cone support 7. The left and right ends of the support ramp surface 42 are respectively fixedly connected to the adjacent support surface 2. In this embodiment, the left and right ends of the support ramp surface 42 of the first support 4a are respectively connected to the first vertical surface 2a and the second vertical surface 2b, the left and right ends of the support ramp surface 42 of the second support 4b are respectively connected to the second vertical surface 2b and the third vertical surface 2c, and the left and right ends of the support ramp surface 42 of the third support 4c are respectively connected to the third vertical surface 2c and the first vertical surface 2a. The support top surfaces 41 of the first support 4a, the second support 4b and the third support 4c can all be used to install the inverted cone support 7. Therefore, the installation and number of inverted cone supports 7 can be adjusted according to the actual situation of the satellite under test. In particular, when manufacturing the flat satellite vibration test extension support of this utility model, the support part 4 is cast by lost foam casting process. Based on the first bottom edge beam 1a, the second bottom edge beam 1b, the third bottom edge beam 1c, the first top edge beam 5a, the second top edge beam 5b and the third top edge beam 5c pre-embedded as the keel, the support part 4 cast by lost foam casting process can be produced with lower cost and faster construction period, while enabling the flat satellite vibration test extension support of this utility model to have the stiffness and weight to meet the test requirements.
[0026] Furthermore, such as Figure 5 As shown, in a preferred embodiment of this utility model, an inverted cone support 7 is also provided on the support part 4, and the satellite to be tested is assembled with the flat plate satellite vibration test extension support through the inverted cone support 7. Specifically, the inverted cone support 7 in this utility model is an inverted cone structure with a larger top and a smaller bottom. It includes an inverted cone top surface 71 at the top, an inverted cone bottom surface 72 at the bottom, an inverted cone reinforcing rib 73 connecting the inverted cone top surface 71 and the inverted cone bottom surface 72, and an inverted cone body 74 connecting the inverted cone reinforcing rib 73, the inverted cone top surface 71 and the inverted cone bottom surface 72. The inverted cone top surface 71 and the inverted cone bottom surface 72 are both annular structures and are concentrically arranged. The outer diameter of the inverted cone top surface 71 is larger than the outer diameter of the inverted cone bottom surface 72. Several inverted cone reinforcing ribs 73 are inclinedly arranged between the inverted cone top surface 71 and the inverted cone bottom surface 72. Therefore, the inverted cone support 7 has an inverted cone structure with a larger top and a smaller bottom. The inverted cone top surface 71 is provided with a connecting hole for relative installation and fixing with the satellite under test, and the inverted cone bottom surface 72 is provided with a connecting hole for relative installation and fixing with the support part 4. The inverted cone support 7, the support part 4 and the satellite under test can be connected by bolts. In this embodiment, a total of three inverted cone supports 7 are respectively disposed on the first support 4a, the second support 4b and the third support 4c.
[0027] For further information, please refer to [link / reference]. Figure 4The supporting rib 3 in this utility model includes a cylindrical portion 31, a first rib 3a, a second rib 3b, a third rib 3c, a fourth rib 3d, a fifth rib 3e, and a sixth rib 3f. Specifically, the bottom ends of the cylindrical portion 31, the first rib 3a, the second rib 3b, and the third rib 3c are respectively fixedly connected to the chassis body 11. The first rib 3a, the second rib 3b, and the third rib 3c are radially arranged around the periphery of the cylindrical portion 31. One end of the first rib 3a is connected to the cylindrical portion 31, and the other end of the first rib 3a is connected to the first vertical surface 2a. One end of the second rib 3b is connected to the cylindrical portion 31, and the other end of the second rib 3b is connected to the second vertical surface 2b. One end of the third rib 3c is connected to the cylindrical portion 3a. 1. The other end of the first rib 3a is connected to the first vertical surface 2a. The bottom ends of the fourth rib 3d, the fifth rib 3e, and the sixth rib 3f are respectively fixed to the chassis body 11. The fourth rib 3d, the fifth rib 3e, and the sixth rib 3f are arranged radially around the periphery of the cylindrical part 31. One end of the fourth rib 3d is connected to the cylindrical part 31, and the other end of the fourth rib 3d is connected to the support slope surface 42 of the first support 4a. One end of the fifth rib 3e is connected to the cylindrical part 31, and the other end of the fifth rib 3e is connected to the support slope surface 42 of the second support 4b. One end of the sixth rib 3f is connected to the cylindrical part 31, and the other end of the sixth rib 3f is connected to the support slope surface 42 of the third support 4c. In this embodiment, the first rib 3a, the second rib 3b, the third rib 3c, the fourth rib 3d, the fifth rib 3e, and the sixth rib 3f are respectively provided with weight-reducing holes for reducing weight. In particular, when manufacturing the flat satellite vibration test extension support of this utility model, the support rib 3 is cast by lost foam casting. Based on the first bottom edge beam 1a, the second bottom edge beam 1b, the third bottom edge beam 1c, the first top edge beam 5a, the second top edge beam 5b, and the third top edge beam 5c pre-embedded as the keel, the support rib 3 cast by lost foam casting can be produced at a lower cost and in a faster time, while enabling the flat satellite vibration test extension support of this utility model to have the stiffness and weight that meet the test requirements.
[0028] Furthermore, the extended support for the flat-plate satellite vibration test in this invention also includes a first reinforcing plate 6a and a second reinforcing plate 6b. Specifically, the first reinforcing plate 6a is located above the first facade 2a and the third facade 2c, and its two ends are integrally connected to the first top edge beam 5a and the third top edge beam 5c, respectively. The second reinforcing plate 6b is located above the second facade 2b and the third facade 2c, and its two ends are integrally connected to the second top edge beam 5b and the third top edge beam 5c, respectively. In this embodiment, the first reinforcing plate 6a is also screwed integrally with the sixth rib 3f below it, and the second reinforcing plate 6b is also screwed integrally with the fifth rib 3e below it. This invention strengthens the fundamental frequency and stiffness of the extended support for the flat-plate satellite vibration test through the first reinforcing plate 6a and the second reinforcing plate 6b.
[0029] In summary, the flat-plate satellite vibration test extension support of this utility model, through the basin-shaped support surface and the base, and the support ribs connecting the base and the support surface, creates an extension tooling that meets the rigidity and weight requirements of the test. For test environments where the vibration test bench itself is small and the test environment area is limited, placing the flat-plate satellite vibration test extension support of this utility model on the vibration test bench can effectively expand the size of the satellite to be tested that the vibration test bench can support, thereby enabling vibration testing of large aerospace products under the premise of limited test environment area and tight schedule.
[0030] The above are merely specific embodiments of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.
Claims
1. A plate satellite vibration test extension support, characterized in that: It includes a chassis (1), a support surface (2), a support rib (3), and a support portion (4). The support surface (2) extends obliquely upward from the edge of the chassis (1). Several support surfaces (2) and the chassis (1) form a basin shape. The support rib (3) connects the chassis (1) and the support surface (2), and the chassis (1) and the support portion (4). The support portion (4) is located above the chassis (1) and is used to install and fix the satellite to be tested. The chassis (1) is used to assemble with the vibration test bench.
2. The extended support for flat-plate satellite vibration testing as described in claim 1, characterized in that: The chassis (1) includes a chassis body (11), a first bottom edge beam (1a), a second bottom edge beam (1b), and a third bottom edge beam (1c). The first bottom edge beam (1a), the second bottom edge beam (1b), and the third bottom edge beam (1c) are located on the edge of the chassis body (11) and are fixedly connected to the chassis body (11). The first bottom edge beam (1a), the second bottom edge beam (1b), and the third bottom edge beam (1c) form a triangle. The chassis body (11) is used for relative installation and fixation with the vibration test bench.
3. The extended support for flat-plate satellite vibration testing as described in claim 2, characterized in that: The supporting surface (2) includes a first facade (2a), a second facade (2b), and a third facade (2c). The first facade (2a) is formed by extending obliquely upward from the first bottom edge beam (1a). The second facade (2b) is formed by extending obliquely upward from the second bottom edge beam (1b). The third facade (2c) is formed by extending obliquely upward from the third bottom edge beam (1c). The left and right ends of the first facade (2a) are connected to the second facade (2b) and the third facade (2c), respectively. The left and right ends of the second facade (2b) are connected to the first facade (2a) and the third facade (2c), respectively. The left and right ends of the third facade (2c) are connected to the first facade (2a) and the second facade (2b), respectively.
4. The extended support for flat-plate satellite vibration testing as described in claim 3, characterized in that: It also includes a first top edge beam (5a), a second top edge beam (5b), and a third top edge beam (5c). The first top edge beam (5a) is located at the top of the first facade (2a) and is fixedly connected to the first facade (2a). The second top edge beam (5b) is located at the top of the second facade (2b) and is fixedly connected to the second facade (2b). The third top edge beam (5c) is located at the top of the third facade (2c) and is fixedly connected to the third facade (2c). The first top edge beam (5a), the second top edge beam (5b), and the third top edge beam (5c) form a triangle.
5. The extended support for flat-plate satellite vibration testing as described in claim 4, characterized in that: The first top edge beam (5a) is arranged parallel to the first bottom edge beam (1a), the second top edge beam (5b) is arranged parallel to the second bottom edge beam (1b), and the third top edge beam (5c) is arranged parallel to the third bottom edge beam (1c).
6. The extended support for flat-plate satellite vibration testing as described in claim 4, characterized in that: It also includes a first reinforcing plate (6a) and a second reinforcing plate (6b). The two ends of the first reinforcing plate (6a) are connected to the first top edge beam (5a) and the third top edge beam (5c) respectively. The two ends of the second reinforcing plate (6b) are connected to the second top edge beam (5b) and the third top edge beam (5c) respectively.
7. The extended support for flat-plate satellite vibration testing as described in claim 3, characterized in that: The support portion (4) includes a first support (4a), a second support (4b) and a third support (4c). The first support (4a) is located at the connection between the first facade (2a) and the second facade (2b). The second support (4b) is located at the connection between the second facade (2b) and the third facade (2c). The third support (4c) is located at the connection between the third facade (2c) and the first facade (2a). The first support (4a), the second support (4b) and the third support (4c) are respectively provided with inverted conical supports (7) for installing and fixing the satellite under test.
8. The extended support for flat-plate satellite vibration testing as described in claim 7, characterized in that: The inverted cone support (7) includes an inverted cone top surface (71), an inverted cone bottom surface (72), an inverted cone reinforcing rib (73), and an inverted cone body (74). The inverted cone top surface (71) is used to connect with the satellite under test and is located at the top of the inverted cone support (7). The inverted cone bottom surface (72) is used to connect with the support part (4) and is located at the bottom of the inverted cone support (7). The inverted cone reinforcing rib (73) is connected between the inverted cone top surface (71) and the inverted cone bottom surface (72). The inverted cone body (74) is connected between the inverted cone top surface (71), the inverted cone bottom surface (72), and the inverted cone reinforcing rib (73).
9. The extended support for flat-plate satellite vibration testing as described in claim 7, characterized in that: The supporting rib (3) includes a cylindrical part (31), a first rib (3a), a second rib (3b), and a third rib (3c). The first rib (3a), the second rib (3b), and the third rib (3c) are arranged radially around the periphery of the cylindrical part (31). One end of the first rib (3a) is connected to the cylindrical part (31), and the other end of the first rib (3a) is connected to the first facade (2a). One end of the second rib (3b) is connected to the cylindrical part (31), and the other end of the second rib (3b) is connected to the second facade (2b). One end of the third rib (3c) is connected to the cylindrical part (31).
10. The extended support for flat-plate satellite vibration testing as described in claim 9, characterized in that: The supporting rib (3) further includes a fourth rib (3d), a fifth rib (3e), and a sixth rib (3f). The fourth rib (3d), the fifth rib (3e), and the sixth rib (3f) are arranged radially around the periphery of the cylindrical part (31). One end of the fourth rib (3d) is connected to the cylindrical part (31), and the other end of the fourth rib (3d) is connected to the first support (4a). One end of the fifth rib (3e) is connected to the cylindrical part (31), and the other end of the fifth rib (3e) is connected to the second support (4b). One end of the sixth rib (3f) is connected to the cylindrical part (31), and the other end of the sixth rib (3f) is connected to the third support (4c).