Satellite simulator structure applied to satellite ground test

Abstract

The utility model relates to a satellite simulator structure applied to a satellite ground test. The satellite simulator structure comprises a top plate, a bottom plate, a front panel, a rear panel, side plates, an upper heat conduction block and a lower heat conduction block, a left edge opening and a right edge opening of the bottom plate are vertically connected with the side plates, and a front edge opening and a rear edge opening of the bottom plate are vertically connected with the front panel and the rear panel respectively; the three upper heat conduction blocks are connected to the inner face of the side plate in parallel at intervals, and the lower heat conduction blocks are further connected between the adjacent upper heat conduction blocks. And the top plate covers the upper ends of the front panel, the rear panel and the side plates. The device has the advantages that the size can be effectively reduced, and the requirements of light weight and portability are met; each single machine module is independently mounted, and each single machine can be independently dismounted, so that the requirements of testability and maintainability are met; the heat conduction block design is adopted, and heat balance can be achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite single-machine ground simulation structure, and more specifically to a satellite simulator structure applied to satellite ground testing. Background Art

[0002] With the advancement of technology, the growth of market demand and the improvement of commercialization, the application fields of satellites are constantly expanding, playing an important role in communications, meteorology, remote sensing, broadcasting, navigation and other fields. It has also driven the growth rate of satellite services and ground equipment manufacturing industries to significantly exceed that of satellite manufacturing and launch services, and their proportion in the entire satellite industry chain continues to rise.

[0003] The existing satellite ground test tooling design concept is single, all designed for a single unit, and the structural design is mostly flat, with poor integration, large size, poor heat dissipation performance and other disadvantages. Therefore, designing a structure for ground testing has become a problem that needs to be solved in the industry.

[0004] The preceding description is intended to provide general background information and does not necessarily constitute prior art. Utility Model Content

[0005] The utility model aims to provide a satellite simulator structure applied to satellite ground testing, which can effectively reduce the volume and meet the requirements of lightness and portability.

[0006] The utility model provides a satellite simulator structure applied to satellite ground testing, comprising a top plate, a bottom plate, a front panel, a rear panel, a side plate, an upper heat-conducting block and a lower heat-conducting block; the side plates are vertically connected to the left and right openings of the bottom plate, and the front and rear openings of the bottom plate are respectively vertically connected to the front panel and the rear panel; three upper heat-conducting blocks are connected in parallel and at intervals on the inner surface of the side plate, and the lower heat-conducting block is also connected between adjacent upper heat-conducting blocks; the top plate is provided on the upper end covers of the front panel, the rear panel and the side plates.

[0007] Furthermore, thermal conductive silicone grease is coated on the upper surface of the bottom plate.

[0008] Furthermore, thermal conductive silicone grease is coated on the lower surface of the top plate.

[0009] Furthermore, two installation corners are connected to the bottom outside the side plate, and heat dissipation fins are installed on the installation corners.

[0010] Furthermore, outer surfaces of the top plate, the bottom plate, the front panel, the rear panel and the side panels are subjected to black anodizing treatment.

[0011] Furthermore, a circle of support beams is provided on the periphery of the inner surface of the rear panel, and a plurality of support columns are also provided on the inner surface of the rear panel, and threaded holes are opened on the support columns.

[0012] Furthermore, the front panel and the rear panel are both provided with a plurality of connector openings for connecting test cables.

[0013] The utility model discloses a satellite simulator structure for ground testing of satellites, which adopts a stacking mode with a power distribution module at the bottom, a satellite service module in the middle and a measurement and control module at the top; specifically, two ends of the power distribution module, the satellite service module and the measurement and control module are correspondingly connected to the upper heat conduction blocks on the inner surfaces of the two side panels; the locking strips in the traditional solution are replaced, and the satellite is connected to the single machine through screws, and then connected to the front panel, the rear panel and the side panels through screws; the screw connection can make each surface completely contact, so that the heat of the measurement and control, power distribution and satellite service single machine modules is transferred to the satellite simulator structure, and the reliability of the connection is also increased; the measurement and control, power distribution and satellite service single machine modules are connected in the satellite simulator structure in a stacking mode through the upper heat conduction block and the lower heat conduction block; the volume can be effectively reduced to meet the requirements of lightweight and portability; each single machine module is independently installed, and each single machine can be disassembled separately to meet the requirements of testability and maintainability; the heat conduction block design can achieve thermal balance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The present invention is a schematic structural diagram of a satellite simulator structure for use in satellite ground testing provided by an embodiment of the present invention.

[0015] Figure 2 for Figure 1 A structural schematic diagram of another perspective of the satellite simulator structure used for satellite ground testing.

[0016] Figure 3 for Figure 1 Schematic diagram of the structure of the base plate of the satellite simulator structure used for satellite ground testing.

[0017] Figure 4 for Figure 1 Schematic diagram of the structure of the side panel of the satellite simulator used for satellite ground testing.

[0018] Figure 5 for Figure 1 Schematic diagram of the structure of the rear panel of the satellite simulator used for satellite ground testing.

[0019] Figure 6 for Figure 1 Schematic diagram of the structure of the satellite simulator printed circuit board of the satellite simulator structure used for satellite ground testing.

[0020] Figure 7 for Figure 1 A structural schematic diagram of another perspective of the satellite simulator printed board of the satellite simulator structure used for satellite ground testing.

[0021] The reference numerals and components involved in the drawings are as follows:

[0022] 1. Top plate 2. Bottom plate 3. Front panel

[0023] 31. Connector opening 4. Rear panel 41. Support beam

[0024] 42, support column 43, threaded hole 5, side plate

[0025] 6. Upper heat conducting block 7. Lower heat conducting block 8. Installation angle

[0026] 9. Satellite simulator printed circuit board DETAILED DESCRIPTION

[0027] The following is a further detailed description of the specific implementation of the present invention in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0028] The terms "first", "second", "third", "fourth" and the like in the specification and claims of the present utility model are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence.

[0029] Example 1

[0030] Figure 1 A schematic diagram of the structure of a satellite simulator for satellite ground testing provided by an embodiment of the utility model, Figure 2 for Figure 1 A schematic diagram of another perspective of the satellite simulator structure used for satellite ground testing. Figure 3 for Figure 1 The schematic diagram of the bottom plate of the satellite simulator structure used for satellite ground testing. Figure 4 for Figure 1 The schematic diagram of the side panel of the satellite simulator structure used for satellite ground testing. Figure 1 , Figure 2 , Figure 3 , Figure 4The satellite simulator structure for satellite ground testing provided by the embodiment of the utility model includes a top plate 1, a bottom plate 2, a front panel 3, a rear panel 4, a side panel 5, an upper heat-conducting block 6 and a lower heat-conducting block 7; the side panels 5 are vertically connected to the left and right openings of the bottom plate 2, and the front panel 3 and the rear panel 4 are vertically connected to the front and rear openings of the bottom plate 2 respectively; three upper heat-conducting blocks 6 are connected in parallel and spaced apart on the inner surface of the side panel 5, and the lower heat-conducting block 7 is also connected between adjacent upper heat-conducting blocks 6; the top plate 1 is provided on the upper end covers of the front panel 3, the rear panel 4 and the side panels 5.

[0031] It should be noted that the satellite simulator includes measurement and control, power distribution and satellite service stand-alone modules. Considering the heat consumption of the three modules, the power distribution module heat consumption> measurement and control module heat consumption> satellite service module heat consumption, the power distribution module is stacked at the bottom, the satellite service module is in the middle, and the measurement and control module is stacked at the top.

[0032] Specifically, the two ends of the power distribution module, satellite service module and measurement and control module are correspondingly connected to the upper heat conduction blocks 6 on the inner surfaces of the two side panels 5; replacing the locking strip in the traditional solution, it is connected to the satellite unit through screws, and then connected to the front panel 3, rear panel 4 and side panel 5 through screws. The use of screw connection can make each surface fully contact, so that the heat of the measurement and control, power distribution and satellite service unit modules can be transferred to the satellite simulator structure, while also increasing the reliability of the connection.

[0033] The satellite simulator structure of the utility model is applied to satellite ground testing. The measurement and control, power distribution and satellite service stand-alone modules are connected in a stacked manner in the satellite simulator structure through an upper heat conductive block 6 and a lower heat conductive block 7. The volume can be effectively reduced to meet the requirements of lightness and portability. Each stand-alone module is installed independently, and each stand-alone module can be disassembled separately to meet the requirements of testability and maintainability. The heat conductive block design can achieve thermal balance.

[0034] Furthermore, thermal conductive silicone grease is coated on the upper surface of the bottom plate 2 ; and thermal conductive silicone grease is coated on the lower surface of the top plate 1 .

[0035] It should be noted that the thermal grease coated on the upper surface of the bottom plate 2 allows the lower surface of the lower frame of the power distribution module structure to be in contact with the upper surface of the bottom plate 2 through the thermal grease, and the heat of the power distribution module is transferred to the bottom plate 2 through heat conduction. The thermal grease on the lower surface of the top plate 1 allows the upper surface of the thermal block of the upper frame of the measurement and control module structure to be completely in contact with the lower surface of the top plate 1 through the thermal grease, and the heat is transferred to the top plate 1 through heat conduction.

[0036] Further references Figure 1 , Figure 2 In the utility model, two mounting angles 8 are connected to the bottom of the outside of the side plate 5 , and heat dissipation fins are installed on the mounting angles 8 .

[0037] It should be noted that the side panel 5 and the base plate 2 are connected by screws, and then the heat sink fins are installed through the mounting angle 8 so that the lower surface of the base plate 2 and the heat sink fins are in complete contact, and thermal grease is applied between the lower surface of the base plate 2 and the contact surface of the heat sink fins to transfer heat to the heat sink fins through heat conduction.

[0038] Furthermore, the outer surfaces of the top plate 1, the bottom plate 2, the front plate 3, the rear plate 4 and the side plate 5 are subjected to black anodizing treatment to achieve radiation heat dissipation.

[0039] Figure 5 for Figure 1 The schematic diagram of the rear panel of the satellite simulator structure used for satellite ground testing. Figure 6 for Figure 1 The schematic diagram of the structure of the satellite simulator printed circuit board used for satellite ground testing is shown in the figure. Figure 7 for Figure 1 Another perspective of the structure diagram of the satellite simulator printed circuit board used for satellite ground testing. Please refer to Figure 5 , Figure 6 , Figure 7 In the present invention, a circle of support beams 41 is disposed around the inner surface of the rear panel 4 , and a plurality of support columns 42 are also disposed on the inner surface of the rear panel 4 , wherein threaded holes 43 are formed on the support columns 42 .

[0040] It should be noted that the support beam 41 and the support column 42 are used to support the satellite simulator printed circuit board 9, and play a supporting role when each module is plugged in separately to protect the printed circuit board; the support column 42 has a threaded hole 43 for fixing the printed circuit board on the rear panel 4.

[0041] Furthermore, the front panel 3 and the rear panel 4 are both provided with a plurality of connector openings 31 for connecting test cables.

[0042] Based on the above description, it can be seen that the advantages of the utility model are:

[0043] 1. The satellite simulator structure used for satellite ground testing of the utility model has two ends of the power distribution module, the satellite service module and the measurement and control module connected to the upper heat conduction block 6 on the inner surface of the two side panels 5; the locking strip in the traditional solution is replaced, and the satellite is connected to the single machine by screws, and then connected to the front panel 3, the rear panel 4, and the side panel 5 by screws. The screw connection can make each surface fully contact, so that the heat of the measurement and control, power distribution and satellite service single machine modules is transferred to the satellite simulator structure, and the reliability of the connection is also increased;

[0044] 2. The satellite simulator structure of the utility model used for satellite ground testing connects the measurement and control, power distribution and satellite service stand-alone modules in a stacked manner in the satellite simulator structure through the upper heat conductive block 6 and the lower heat conductive block 7; it can effectively reduce the volume to meet the requirements of lightweight and portability; each stand-alone module is installed independently, and each stand-alone can be disassembled separately to meet the requirements of testability and maintainability; the heat conductive block design is adopted to achieve thermal balance.

[0045] The above is only a specific implementation of the utility model, but the protection scope of the utility model is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the utility model, which should be included in the protection scope of the utility model. Therefore, the protection scope of the utility model should be based on the protection scope of the claims.

Claims

1. A satellite simulator structure used for satellite ground testing, characterized in that: It comprises a top plate (1), a bottom plate (2), a front plate (3), a rear plate (4), a side plate (5), an upper heat conducting block (6) and a lower heat conducting block (7); The side panels (5) are vertically connected to the left and right sides of the bottom plate (2), and the front panel (3) and the rear panel (4) are vertically connected to the front and rear sides of the bottom plate (2), respectively; Three upper heat conducting blocks (6) are connected in parallel and spaced apart on the inner surface of the side plate (5), and a lower heat conducting block (7) is connected between adjacent upper heat conducting blocks (6); The top plate (1) is provided on the upper end covers of the front panel (3), the rear panel (4) and the side panels (5).

2. The satellite simulator structure for satellite ground testing according to claim 1, characterized in that: Thermal conductive silicone grease is coated on the upper surface of the bottom plate (2).

3. The satellite simulator structure for satellite ground testing according to claim 1, characterized in that: Thermal conductive silicone grease is coated on the lower surface of the top plate (1).

4. The satellite simulator structure for satellite ground testing according to claim 1, characterized in that: Two installation corners (8) are connected to the bottom outside the side plate (5), and heat dissipation fins are installed on the installation corners (8).

5. The satellite simulator structure for satellite ground testing according to claim 1, characterized in that: The outer surfaces of the top plate (1), the bottom plate (2), the front panel (3), the rear panel (4) and the side panels (5) are subjected to black anodizing treatment.

6. The satellite simulator structure for satellite ground testing according to claim 1, characterized in that: A circle of support beams (41) is provided on the periphery of the inner surface of the rear panel (4), and a plurality of support columns (42) are also provided on the inner surface of the rear panel (4), wherein threaded holes (43) are provided on the support columns (42).

7. The satellite simulator structure for satellite ground testing according to claim 1, characterized in that: The front panel (3) and the rear panel (4) are both provided with a plurality of connector openings (31) for connecting test cables.

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