A satellite general mass simulator

Abstract

The present invention relates to a satellite general mass simulation component, which includes a cross bar, a longitudinal bar and a disc. There are two cross bars. Two groups of longitudinal long holes are provided on the longitudinal bar. A first threaded hole is also provided at the middle position of the longitudinal bar. A second threaded hole is provided at the center of the disc. The disc is arranged at the middle position of the longitudinal bar and is connected by a first screw passing through the correspondingly arranged first threaded hole and the second threaded hole. The two groups of longitudinal long holes are respectively arranged on both sides of the first threaded hole. A third threaded hole is provided on the cross bar. The two cross bars are arranged in parallel at intervals. The longitudinal bar is arranged on the two cross bars and is respectively connected by a second screw passing through the correspondingly arranged longitudinal long hole and the third threaded hole. The present invention adopts the scheme of cooperation between the longitudinal bar and the cross bar. The cross bar can be arranged at the corresponding position of the satellite cabin panel, the longitudinal bar is installed on the cross bar, and then the disc is arranged on the longitudinal bar. The longitudinal installation distance of the mass simulation component can be adjusted by adjusting the distance between the two cross bars, and the versatility is strong.

Description

Technical Field

[0001] The present invention relates to the technical field related to satellite simulation tests, and particularly relates to a general satellite mass simulation component. Background Art

[0002] With the increasing demand for existing satellites, the rapid manufacture of low-cost microsatellites has become a key development direction in the current aerospace field. Each microsatellite needs to undergo vibration tests. Before the vibration test of the flight model satellite, generally, the vibration test of the structural model satellite is carried out. The single-machine equipment used in this test is generally replaced by mass simulation components. Many mass simulation components with different size specifications are required for each satellite.

[0003] Most of the existing microsatellites produce a set of mass simulation components for each satellite. On the one hand, the development cost is relatively high, and on the other hand, it also causes waste of resources.

[0004] As the types of microsatellite development increase, it is uneconomical to design and process a set of mass simulation components for each satellite. The existing technology is to design and process special mass simulation components for each piece of equipment. Its main disadvantages are as follows: (1) High input costs, including input of manpower, material resources, and financial resources; (2) High maintenance costs. As the number of product models increases, more and more mass simulation components are produced, which will occupy more and more storage space in the warehouse and also require warehouse management personnel for daily management. Therefore, it is necessary to design a set of general mass simulation components to meet the test requirements of most satellites. Summary of the Invention

[0005] In order to solve one or several of the technical problems existing in the prior art, the present invention provides a general satellite mass simulation component.

[0006] The technical solution for the present invention to solve the above technical problems is as follows: A general satellite mass simulation component includes a cross bar, a longitudinal bar, and a disc. There are two cross bars. Two groups of longitudinal long holes are provided on the longitudinal bar. A first threaded hole is also provided at the middle position of the longitudinal bar. A second threaded hole is provided at the center of the disc. The disc is arranged at the middle position of the longitudinal bar and is connected by a first screw passing through the corresponding first threaded hole and second threaded hole; the two groups of longitudinal long holes are respectively arranged on both sides of the first threaded hole. A third threaded hole is provided on the cross bar. The two cross bars are arranged in parallel at intervals. The longitudinal bar is arranged on the two cross bars and is respectively connected by a second screw passing through the corresponding longitudinal long hole and third threaded hole.

[0007] The beneficial effects of the present invention are as follows: The present invention adopts a scheme of combining vertical rods and horizontal rods. The horizontal rods can be arranged at corresponding positions on the satellite cabin board, the vertical rods are installed on the horizontal rods, and then the discs are arranged on the vertical rods. By adjusting the distance between the two horizontal rods, the longitudinal installation distance of the mass simulation parts can be adjusted to adapt to different shapes, structures and distances of single equipment on the satellite cabin board, enhancing the versatility of the mass simulation parts. Moreover, by arranging discs at the middle position of the vertical rods, the mass simulation parts can be weighted to match the weight of the corresponding equipment. The universal satellite mass simulation parts of the present invention are applicable to microsatellites, with a simple structure and convenient operation, and can meet the vibration test requirements of the vast majority of microsatellites.

[0008] Based on the above technical solutions, the present invention can be further improved as follows.

[0009] Further, the disc includes a plurality of discs with different diameters. The plurality of discs with different diameters are stacked on the vertical rod and connected to the vertical rod through the first screws.

[0010] The beneficial effect of adopting the above further scheme is: By setting a plurality of discs with different diameters, it is convenient to adapt to mass simulation parts of different weights. For example, single equipment with a large weight requires more or heavier large-diameter discs.

[0011] Further, the diameters of the plurality of discs with different diameters gradually increase or decrease from bottom to top.

[0012] The beneficial effect of adopting the above further scheme is: By gradually increasing the diameters of the plurality of discs from bottom to top, the center of gravity of each disc can be adjusted to make the center lower, making the whole equipment more stable.

[0013] Further, the disc includes at least one first disc and at least one second disc. The diameter of the first disc is smaller than that of the second disc. The first disc is arranged adjacent to the vertical rod, and the second disc is stacked above or below the first disc.

[0014] Further, inclined surfaces are respectively provided at both sides of the upper end of the vertical rod corresponding to the positions of two groups of longitudinal long holes, and a plane is provided at the position corresponding to the first threaded hole between the two inclined surfaces.

[0015] The beneficial effect of adopting the above further scheme is: By setting the inclined surfaces, it is beneficial to weight reduction and also convenient for assembling the discs. By setting the plane, it is also convenient for installing and supporting the discs.

[0016] Further, each group of longitudinal long holes is at least two, and at least two longitudinal long holes in each group are arranged side by side in parallel at intervals; third threaded holes are respectively provided at the positions corresponding to each longitudinal long hole on the horizontal rod.

[0017] The beneficial effects of adopting the above further scheme are as follows: Each group of longitudinal long holes includes at least two longitudinal long holes, which is beneficial to the stable connection and fixation between the longitudinal rod and the cross rod.

[0018] Furthermore, the two groups of longitudinal long holes are arranged in one-to-one correspondence.

[0019] The beneficial effects of adopting the above further scheme are as follows: By arranging the two groups of longitudinal long holes in one-to-one correspondence, the connection between the longitudinal rod and the cross rod is made more stable.

[0020] Furthermore, longitudinal stepped grooves are provided at positions corresponding to each longitudinal long hole on the longitudinal rod, and the screw head of the second screw is hidden in the longitudinal stepped groove and limited on the step of the longitudinal stepped groove.

[0021] The beneficial effects of adopting the above further scheme are as follows: By providing the longitudinal stepped grooves, it is convenient to hide the screw head of the second screw and also convenient to support the screw head of the second screw.

[0022] Furthermore, transverse long holes are also provided on the cross rod.

[0023] The beneficial effects of adopting the above further scheme are as follows: By providing the transverse long holes, it is used to adjust the transverse installation spacing of the single equipment on the satellite cabin panel.

[0024] Furthermore, two transverse long holes are respectively provided on each cross rod, and the two transverse long holes are symmetrically arranged on both sides of the third threaded hole.

[0025] The beneficial effects of adopting the above further scheme are as follows: By providing two transverse long holes, the installation between the cross rod and the satellite cabin panel is made more stable and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a three-dimensional structural schematic diagram of the cross rod of the present invention;

[0027] Figure 2 is a three-dimensional structural schematic diagram of the longitudinal rod of the present invention;

[0028] Figure 3 is a front view structural schematic diagram of the satellite general mass simulation part of the present invention;

[0029] Figure 4 is a top view structural schematic diagram of the satellite general mass simulation part of the present invention;

[0030] Figure 5 is a three-dimensional structural schematic diagram of the satellite general mass simulation part of the present invention.

[0031] In the drawings, the list of components represented by each reference numeral is as follows:

[0032] 1. Cross bar; 11. Third threaded hole; 12. Horizontal long hole;

[0033] 2. Vertical bar; 21. First threaded hole; 22. Vertical long hole; 23. Vertical step groove; 24. Inclined plane; 25. Plane;

[0034] 3. First disk; 4. Second disk; 5. First screw; 6. Second screw. Specific implementation mode

[0035] The principles and features of the present invention will be described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0036] As Figures 1 to 5 shown, a satellite general mass simulation component of this embodiment includes a cross bar 1, a vertical bar 2 and disks. There are two cross bars 1. Two groups of vertical long holes 22 are provided on the vertical bar 2. A first threaded hole 21 is also provided at the middle position of the vertical bar 2. A second threaded hole is provided at the center of the disk. The disk is arranged at the middle position of the vertical bar 2 and is connected by a first screw 5 passing through the corresponding first threaded hole 21 and the second threaded hole; the two groups of vertical long holes 22 are respectively arranged on both sides of the first threaded hole 21. A third threaded hole 11 is provided on the cross bar 1. The two cross bars 1 are arranged in parallel at intervals. The vertical bar 2 is arranged on the two cross bars 1 and is respectively connected by a second screw 6 passing through the corresponding vertical long hole 22 and the third threaded hole 11.

[0037] The satellite general mass simulation component of this embodiment is mainly used to simulate various different single-unit devices (any electronic device) on the satellite. The simulation component of this embodiment has the same installation points, the same weight, and the same center of gravity as the single-unit device to be simulated. In this way, when doing mechanical tests, it is closer to the single-unit device being simulated. The general mass simulation component of this embodiment is mainly used to simulate single-unit devices with square installation points.

[0038] Specifically, the cross bar of this embodiment is mainly used to adjust the horizontal installation spacing of the satellite general mass simulation component. Generally, the cross bar is made of aluminum alloy. The vertical bar is mainly used to adjust the vertical installation spacing of the mass simulation component according to the adjustment of the cross bar. Generally, the vertical bar is made of aluminum alloy.

[0039] As Figures 3 to 5 shown, the disks of this embodiment include disks with different diameters. The disks with different diameters are stacked on the vertical bar 2 and are connected to the vertical bar 2 by the first screw 5. By setting disks with different diameters, it is convenient to adapt to mass simulation components with different weights. For example, single-unit devices with large weights require more or heavier large-diameter disks.

[0040] AsFigure 3 As shown, the diameters of multiple disks with different diameters gradually increase or decrease from bottom to top. By gradually increasing or decreasing the diameters of the multiple disks from bottom to top, the center of gravity position after the superposition of each disk can be adjusted to simulate single-machine equipment with different centers of gravity.

[0041] As Figures 3 to 5 shown, the disk in this embodiment includes at least one first disk 3 and at least one second disk 4. The diameter of the first disk 3 is smaller than that of the second disk 4. The first disk 3 is arranged adjacent to the vertical rod 2, and the second disk 4 is stacked above or below the first disk 3. Specifically, the first disk 3 is mainly used to adjust the center of gravity of the mass simulation part and is generally made of aluminum alloy by machining. The second disk 4 is mainly used for the counterweight of the mass simulation part to match the weight of the corresponding equipment. The second disk 4 is generally made of metal materials with relatively large densities such as copper and stainless steel.

[0042] As Figure 2 、 Figure 3 and Figure 5 shown, on both sides of the upper end of the vertical rod 2 in this embodiment, inclined surfaces 24 are respectively provided at positions corresponding to two groups of longitudinal long holes 22, and a flat surface 25 is provided at the position corresponding to the first threaded hole 21 between the two inclined surfaces 24. By setting the inclined surfaces, it is beneficial for weight reduction and also convenient for assembling the disks. By setting the flat surface, it is also convenient for installing and supporting the disks. By providing the inclined surfaces 24 and the flat surface 25 on the vertical rod 2, the vertical rod 2 is integrally formed into an isosceles trapezoid structure, which more conforms to the force characteristics of the actual product and can reduce the weight of the vertical rod.

[0043] As Figure 2 、 Figure 4 and Figure 5 shown, each group of longitudinal long holes 22 has at least two, and at least two longitudinal long holes 22 in each group are arranged side by side in parallel at intervals; corresponding to each longitudinal long hole 22 on the cross bar 1, third threaded holes 11 are respectively provided. Each group of longitudinal long holes includes at least two longitudinal long holes, which is beneficial for the stable connection and fixation between the vertical rod and the cross bar.

[0044] As Figure 2 、 Figure 4 and Figure 5 shown, a preferred solution in this embodiment is that the two groups of longitudinal long holes 22 are arranged in one-to-one correspondence. By arranging the two groups of longitudinal long holes in one-to-one correspondence, the connection between the vertical rod and the cross bar is made more stable.

[0045] As Figure 2 、 Figure 4 and Figure 5As shown in the figure, a preferred solution of this embodiment is that longitudinal step grooves 23 are provided at positions corresponding to each longitudinal long hole 22 on the longitudinal rod 2, and the screw head of the second screw 6 is hidden in the longitudinal step groove 23 and is limited on the step of the longitudinal step groove 23. By providing the longitudinal step grooves, it is convenient to hide the screw head of the second screw and also convenient to support the screw head of the second screw.

[0046] As Figure 1 , Figure 4 and Figure 5 shown, a transverse long hole 12 is further provided on the cross bar 1 of this embodiment. By providing the transverse long hole, it is used to adjust the transverse installation spacing of the single-unit equipment on the satellite cabin panel.

[0047] As Figure 1 , Figure 4 and Figure 5 shown, a preferred solution of this embodiment is that two transverse long holes 12 are respectively provided on each cross bar 1, and the two transverse long holes 12 are symmetrically arranged on both sides of the third threaded hole 11. By providing two transverse long holes, the installation between the cross bar and the satellite cabin panel is more stable and reliable.

[0048] A satellite general mass simulator of this embodiment adopts a H-shaped structure and can replace any single-unit equipment mass simulator, as long as it meets the following requirements: the installation holes of the single-unit equipment are rectangular four-point type, and the longitudinal and transverse spacings of the installation holes are between 50 and 100 mm (more installation hole spacing requirements can also be met through expansion and alternative solutions), and the weight of the single-unit equipment is between 0.2 kg and 5 kg.

[0049] In a satellite general mass simulator of this embodiment, the maximum spacing of the third threaded holes of the cross bar can be 100 mm, or 200 mm, 300 mm, etc. The maximum spacing of the first threaded holes of the longitudinal rod can be 100 mm, or 200 mm, 300 mm, etc. The maximum weight of the satellite general mass simulator can be 5 kg, or 10 kg, 15 kg, etc.; the satellite general mass simulator can be made into a series. For example, the sizes of the cross bar or the longitudinal rod can be 100 mm, 200 mm, 300 mm, 400 mm, 500 mm, etc. in multiple series.

[0050] During the use of a satellite general mass simulator according to this embodiment, first, two cross bars are installed at corresponding positions on the satellite cabin panel through horizontal long holes, and then the longitudinal bar is fixed to the cross bars by second screws. Then, each disc is placed in sequence, and is fastened by first screws passing through the second threaded holes of each disc and the first threaded hole of the longitudinal bar. The satellite general mass simulator of this embodiment is applicable to the mass simulation of single-machine equipment and is used for the vibration test of satellites. A set of satellite general mass simulators can be applicable to single-machine equipment of various size specifications, which can greatly save the design and processing costs; this satellite general mass simulator is convenient to install, the center of mass can be adjusted in three directions, and the weight can be arbitrarily adjusted within a certain range.

[0051] This embodiment adopts a scheme of cooperating the longitudinal bar and the cross bars. The cross bars can be set at corresponding positions on the satellite cabin panel, the longitudinal bar is installed on the cross bars, and then the discs are set on the longitudinal bar. The longitudinal installation spacing of the mass simulator can be adjusted by adjusting the spacing between the two cross bars to adapt to different shaped structures of the satellite cabin panel, which enhances the versatility of the mass simulator. Moreover, by setting discs at the middle position of the longitudinal bar, the mass simulator can be counterweighted to match the weight of the corresponding equipment. The satellite general mass simulator of this embodiment is applicable to small satellites, has a simple structure and is convenient to operate, and can meet the vibration test requirements of the vast majority of small satellites.

[0052] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation of the present invention.

[0053] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0054] In the present invention, unless otherwise clearly defined or limited, terms such as "installed", "connected", "joined", "fixed", etc. shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication between two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0055] In the present invention, unless otherwise clearly defined or limited, the first feature being "on" or "under" the second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature is at a higher level than the second feature in terms of horizontal height. The first feature being "under", "below" and "beneath" the second feature may mean that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature is at a lower level than the second feature in terms of horizontal height.

[0056] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0057] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A general satellite mass simulation component, characterized in that, It includes a cross bar, a longitudinal bar and a disc. There are two cross bars. Two groups of longitudinal long holes are formed on the longitudinal bar. A first threaded hole is also formed at the middle position of the longitudinal bar. A second threaded hole is formed at the center of the disc. The disc is arranged at the middle position of the longitudinal bar and is connected by a first screw passing through the correspondingly arranged first threaded hole and second threaded hole; the two groups of longitudinal long holes are respectively arranged on both sides of the first threaded hole. A third threaded hole is formed on the cross bar. The two cross bars are arranged in parallel at intervals. The longitudinal bar is arranged on the two cross bars and is respectively connected by a second screw passing through the correspondingly arranged longitudinal long hole and third threaded hole; On both sides of the upper end of the longitudinal bar, inclined surfaces are respectively provided at positions corresponding to the two groups of longitudinal long holes. The position corresponding to the first threaded hole between the two inclined surfaces is a flat surface; the two groups of longitudinal long holes are arranged in one-to-one correspondence.

2. The general satellite mass simulation component according to claim 1, characterized in that, The disc includes a plurality of discs with different diameters. The plurality of discs with different diameters are stacked on the longitudinal bar and are connected to the longitudinal bar by the first screw.

3. The general satellite mass simulation component according to claim 2, wherein, The diameters of the plurality of discs with different diameters gradually increase or decrease from bottom to top.

4. The general satellite mass simulation component according to claim 2, characterized in that, The disc includes at least one first disc and at least one second disc. The diameter of the first disc is smaller than that of the second disc. The first disc is arranged adjacent to the longitudinal bar. The second disc is stacked above or below the first disc.

5. A general satellite mass simulation component according to any one of claims 1 to 4, characterized in that Each group of longitudinal long holes is at least two. At least two longitudinal long holes in each group are arranged side by side in parallel at intervals; a third threaded hole is respectively provided at the position corresponding to each longitudinal long hole on the cross bar.

6. A general satellite mass simulation component according to any one of claims 1 to 4, characterized in that, A longitudinal stepped groove is formed at the position corresponding to each longitudinal long hole on the longitudinal bar. The screw head of the second screw is hidden in the longitudinal stepped groove and is limited on the step of the longitudinal stepped groove.

7. A general satellite mass simulation component according to any one of claims 1 to 4, characterized in that A transverse long hole is also formed on the cross bar.

8. The general satellite mass simulation component according to claim 7, characterized in that, Two transverse long holes are respectively provided on each cross bar. The two transverse long holes are symmetrically arranged on both sides of the third threaded hole.

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