Satellite accessory and satellite

Abstract

The utility model relates to the technical field of satellites, in particular to a satellite accessory. The satellite accessory comprises a shell used for being installed on a satellite body, and the shell is provided with a bottom plate used for abutting against the satellite body and an installation plate which extends out of the edge of the bottom plate and is parallel to the bottom plate. The satellite accessory further comprises a connecting piece arranged in the mounting plate and the satellite body in a penetrating mode at the same time, a first insulating piece and a second insulating piece, the connecting piece is sleeved with the first insulating piece and the second insulating piece, the first insulating piece and the second insulating piece abut against the surfaces of the two sides of the mounting plate respectively, the first insulating piece is used for separating the connecting piece from the mounting plate, and the second insulating piece is used for separating the mounting plate from the satellite body. According to the utility model, the heat conduction and insulation installation requirements can be met, the installation rigidity and reliability requirements are met, and the cost is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of satellites, in particular to a satellite accessory. Background Art

[0002] Due to the satellite orbit environment and the requirements of long life and high reliability, the number of single machines on satellites that require insulation installation is gradually increasing. For example, when a single machine such as a battery pack is connected to a satellite cabin board, an insulating installation method is required to ensure the static discharge of the battery structure while achieving insulation between the battery structure and the satellite cabin board, thereby ensuring the safety of the single machine.

[0003] In addition, in order to ensure the temperature environment of the single unit on orbit, good thermal contact must be maintained during the insulation installation to meet the thermal control requirements. Currently, polyimide films, rubber pads and other materials that have both thermal conductivity and insulation functions are commonly used on satellites. Although they meet the requirements of thermal conductivity and electrical isolation, the nonlinear mechanical properties of these materials themselves often affect the installation stiffness between the single unit and the structural plate. For example, during installation, if the thermal insulation pad forms an elastic reaction force, the single unit will be subjected to a thrust in the opposite direction of the tightening direction, and then the thrust will be transmitted to the screws, affecting the connection reliability.

[0004] For single units such as batteries that have insulation requirements when installed on satellites, insulation design will be done on the single unit structure during the single unit design stage, such as changing some structural plate materials or doing insulation coating on the surface of the structure; when the single unit is delivered to the whole satellite for final assembly, the satellite installation operation is still carried out through fasteners. However, when flexible insulation materials are used to coat the installation surface of the satellite, the coating thickness cannot be quantitatively controlled, and there is no definite way to avoid the impact of the added flexible material on the installation surface on the installation performance.

[0005] For stand-alone units that are not designed for insulation or do not have thermal insulation requirements, when they need to have thermal insulation effects after being installed on the satellite, the stand-alone units can be covered with insulating materials, and to ensure the installation rigidity of the stand-alone units, the fasteners used for connection are replaced from traditional stainless steel, titanium alloy, etc. to insulating materials such as polyetheretherketone (PEEK), thereby achieving ground isolation between the stand-alone unit casing and the satellite structure. However, when the bottom surface of the stand-alone unit installation is covered with a thermal insulating pad, the changes in the mechanical properties of the stand-alone unit installation interface are also uncontrolled during installation; and when screws made of insulating materials are used to ensure the reliability of the mechanical properties of the stand-alone unit installation interface, the cost is increased and there is a risk of deviation from the installation state required by the stand-alone unit. Utility Model Content

[0006] The utility model aims to solve the problem in the prior art that when a single unit is installed on a satellite, while meeting the heat conduction and insulation installation requirements, it cannot meet the installation rigidity and reliability requirements, and the cost is increased.

[0007] In order to solve the above-mentioned problem, the utility model proposes a satellite accessory, including a shell for installation on a satellite body, the shell having a bottom plate for abutting against the satellite body and a mounting plate extending from the edge of the bottom plate and parallel to the bottom plate, the satellite accessory also includes a connecting member simultaneously passed through the mounting plate and the satellite body, a first insulating member and a second insulating member which are sleeved outside the connecting member and respectively abut against the two side surfaces of the mounting plate, the first insulating member being used to separate the connecting member from the mounting plate, and the second insulating member being used to separate the mounting plate from the satellite body.

[0008] Furthermore, the first insulating member includes a first insulating portion and a first guide portion, the first insulating portion and the first guide portion are both cylindrical and coaxially connected, the first insulating portion and the first guide portion have the same inner diameter, and the first insulating portion has an outer diameter greater than the outer diameter of the first guide portion. The axial lengths of the first insulating portion and the second insulating member are both 1.5 to 6.5 mm.

[0009] Furthermore, the satellite accessory also includes a flexible heat-conducting member arranged between the base plate and the satellite body, and the flexible heat-conducting member is used to separate the base plate from the satellite body.

[0010] Preferably, the second insulating member is also cylindrical in shape, and the difference between its axial length and the distance between the surface of the mounting plate close to the satellite body and the surface of the bottom plate close to the satellite body is equivalent to the thickness of the flexible thermal conductor when installed.

[0011] Furthermore, a first connection hole is formed on the mounting plate, and the first guide portion is inserted into the first connection hole. A surface of the mounting plate close to the satellite body is inwardly recessed to form a mounting groove for mounting the second insulating member, and the mounting groove is connected to the first connection hole.

[0012] Furthermore, the second insulating member includes a cylindrical second insulating portion and a second guide portion, the second insulating portion abuts between the mounting plate and the satellite body, the second guide portion is passed through the first connecting hole, and the sum of the lengths of the second guide portion and the first guide portion is less than the depth of the first connecting hole.

[0013] Preferably, the satellite accessory further includes an adjustment gasket, which is sleeved outside the connecting member and abuts between the second insulating member and the mounting plate.

[0014] In addition, the utility model also proposes a satellite, including a satellite body and the satellite accessories, the satellite body is provided with a mounting surface for installing the satellite accessories, the mounting surface is provided with a second connecting hole, the connecting member is simultaneously passed through the first connecting hole and the second connecting hole, and the flexible heat conductive member is arranged between the base plate and the mounting surface.

[0015] Compared with the prior art, the technical solution of the utility model has the following beneficial effects: while meeting the requirements of thermal conductivity and insulation installation, it also meets the requirements of installation rigidity and reliability, and reduces costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a partial cross-sectional view of a satellite accessory in one embodiment of the utility model.

[0018] Figure 2 for Figure 1 Isometric cutaway view of a .

[0019] Figure 3 This is a schematic diagram of satellite accessories assembly in another embodiment of the utility model.

[0020] Figure 4 for Figure 3 A partial cross-sectional view of .

[0021] Figure 5 It is a partial cross-sectional view of a satellite accessory in the third embodiment of the utility model.

[0022] In the figure:

[0023] 1-housing; 11-bottom plate; 12-mounting plate; 121-first connecting hole; 122-mounting slot;

[0024] 2-satellite body; 21-installation surface; 211 second connection hole;

[0025] 3-connecting member; 31-first insulating member; 32-second insulating member; 311-first insulating portion; 312-first guiding portion; 321-second insulating portion; 322-second guiding portion;

[0026] 4- Flexible thermal conductor. DETAILED DESCRIPTION

[0027] The following will describe in detail a specific embodiment of the utility model in conjunction with the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the utility model, rather than all the embodiments. Based on the description of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0028] The orientation or position relationship indicated by the terms "upper", "lower", "top", "bottom", "inside", "outside", etc. is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the utility model product is usually placed when used. It is only for the convenience of description and simplified description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as a limitation on the utility model.

[0029] The terms "first", "second", etc. are merely used to distinguish elements of similar nature, and do not indicate or imply relative importance or a particular order.

[0030] The terms "comprises," "comprising," or any other variations thereof, are intended to cover a non-exclusive inclusion of the elements listed and may also include additional elements not expressly listed.

[0031] See also Figure 1 , Figure 2 and Figure 5 The utility model provides a satellite, including a satellite body 2 and satellite accessories. The satellite body 2 is provided with a mounting surface 21 for installing the satellite accessories; the satellite accessories include a shell 1 for accommodating a single machine and mounting components 3, 31, 32 for mounting the shell 1 on the mounting surface 21 of the satellite body 2, and a flexible heat conductive member 4 arranged between the shell 1 and the mounting surface 21, which is used to separate the shell 1 and the mounting surface 21 to achieve heat conduction while satisfying insulation performance.

[0032] According to the thermal conductivity and insulation performance required by the single machine and the bottom structure of the single machine, the material of the flexible thermal conductive part 4 is preferably a rubber pad, and the thickness of the flexible thermal conductive part 4 is preferably between 0.4 and 0.6 mm. Affected by factors such as the weight of the single machine, the flexible thermal conductive part 4 will be compressed and deformed during installation. In a specific embodiment, the compressed thickness of the flexible thermal conductive part 4 made of rubber material after installation is generally between 0.2 and 0.4 mm.

[0033] Furthermore, the housing 1 has a bottom plate 11 for contacting with the satellite body 2 and a mounting plate 12 extending from the edge of the bottom plate 11 and parallel to the bottom plate 11. The mounting plate 12 is provided with a first connection hole 121, and the mounting surface 21 of the satellite body is provided with a second connection hole 211. The connector 3 is simultaneously passed through the first connection hole 121 and the second connection hole 211, so that the housing 1 is fixed on the mounting surface 21, and the single unit is mounted on the satellite body 2. Moreover, the mounting plate 12 and the bottom plate 11 are staggered in a direction perpendicular to the bottom plate 11, that is, the mounting plate 12 is designed to be elevated.

[0034] like Figure 1 , Figure 2 As shown, the mounting assembly includes a connector 3, such as a fastener such as a screw. When the housing 1 is fixed to the mounting surface 21 by the connector 3, in order to meet the thermal conductivity performance, the flexible thermal conductive member 4 needs to contact the housing 1 and the mounting surface 21 at the same time.

[0035] Furthermore, the satellite accessories in the utility model include a first insulating member 31 and a second insulating member 32. The first insulating member 31 is sleeved outside the connecting member 3 and abuts against the connecting member 3 and the surface of the mounting plate 12 away from the base plate 11, and is used to separate the connecting member 3 from the mounting plate 12; the second insulating member 32 is sleeved outside the connecting member 3 and abuts between the surface of the mounting plate 12 close to the base plate 11 and the mounting surface 21, and is used to separate the mounting plate 12 from the satellite body 2.

[0036] Preferably, the first insulating member 31 is sleeve-shaped, including a cylindrical first insulating portion 311 and a first guide portion 312, the outer diameter of the first insulating portion 311 is larger than the outer diameter of the first guide portion 312, the first insulating portion 311 and the first guide portion 312 have the same inner diameter, and the first insulating portion 311 and the first guide portion 312 are coaxially connected. The first insulating member 31 is an insulating material with a certain rigidity, preferably polyimide or fiberglass. The first insulating portion 311 abuts between the connector 3 and the mounting plate 12 to separate the connector 3 from the mounting plate 12, and the first guide portion 312 is inserted into the first connecting hole 121 to limit the direction of the connector 3 in the first connecting hole 121. In addition, the outer diameter of the first guide portion 312 is smaller than the diameter of the first connecting hole 121, that is, the first guide portion 312 and the first connecting hole 121 are clearance-matched, which is convenient for installation. Preferably, the axial length of the first insulating portion 311 is 1.5-6.5 mm, the inner diameter of the first guide portion 312 is 3-11 mm, the outer diameter is between 7.5 mm and the diameter of the first connecting hole 121 , and the length is between 1.5 mm and the depth of the first connecting hole 121 .

[0037] Preferably, the second insulating member 32 is also cylindrical in shape and is made of insulating materials such as polyimide or fiberglass with a certain rigidity. The selection of the axial length of the second insulating member 32 is related to the material and thickness of the flexible heat-conducting member 4. Specifically, the difference between the axial length of the second insulating member 32 and the distance between the surface of the mounting plate 12 close to the satellite body 2 and the surface of the bottom plate 11 close to the satellite body 2 is equivalent to the thickness of the flexible heat-conducting member 4 when installed. That is, by raising the height of the surface of the mounting plate 12 close to the mounting surface, and by respectively abutting the first insulating member 31 and the second insulating member 32 on the two side surfaces of the mounting plate 12, the housing 1 is insulated and installed through the connector 3, while meeting the requirements of installation rigidity and reliability.

[0038] like Figure 4 As shown, in another embodiment, the second insulating member 32 also includes a cylindrical second insulating portion 321 and a second guide portion 322, the second insulating portion 321 abuts between the surface of the mounting plate 12 close to the bottom plate 11 and the mounting surface 21, and the second guide portion 322 is inserted into the first connecting hole 121. The axial length of the second insulating portion 321 is preferably 1.5 to 6.5 mm, the inner diameter of the second guide portion 322 is 3 to 11 mm, the outer diameter is between 7.5 mm and the diameter of the first connecting hole 121, and a gap is left between the end face of the second guide portion 322 and the end face of the first guide portion 312, that is, the sum of the axial lengths of the second guide portion 322 and the first guide portion 312 is less than the depth of the first connecting hole 121, thereby ensuring the connection strength of the connecting member 3 inserted in the first connecting hole 121 and the second connecting hole 211, that is, ensuring that the force propagation direction when the connecting member 3 is tightened after installation can meet the connection stiffness and strength requirements.

[0039] In a specific embodiment, the sum of the axial lengths of the second guide portion 322 and the first guide portion 312 is less than the depth of the first connecting hole 121. During installation, after the connector 3 is tightened, the force transmission path of the connector 3 is connector 3-first insulating member 31-mounting plate 12 on the stand-alone housing 1-second insulating member 32-mounting surface 21 on the satellite body 2; rather than connector 3-first insulating member 31-second insulating member 32-mounting surface 21 on the satellite body 2. This can improve the connection strength between the satellite accessories and the satellite body 2, avoid the stand-alone housing 1 being suspended by the first insulating pad and the second insulating member 32, and causing the housing 1 to be virtually connected to the satellite body 2, thereby affecting the connection strength between the satellite accessories and the satellite body 2, and may also affect the thermal conductivity of the flexible thermal conductive member 4.

[0040] like Figure 1 , Figure 4 As shown, preferably, the surface of the mounting plate 12 close to the mounting surface 21 is recessed inward to form a mounting groove 122 for mounting the second insulating member 32 , and the mounting groove 122 is communicated with the first connecting hole 121 .

[0041] Depending on the material of the flexible thermal conductive part 4, the compression thickness is different when subjected to pressure, and depending on the height of the mounting plate 12 relative to the base plate 11, to ensure that the first insulating part 31 and the second insulating part 32 can be suitable for different units and cooperate with flexible thermal conductive pads 4 of different materials, preferably, the satellite accessories also include an adjustment gasket, which is sleeved on the outside of the connecting part 3 and abuts between the second insulating part 32 and the mounting plate 12. The adjustment gasket is preferably annular and can be 0.01 to 1 mm thick. Preferably, the thickness of the adjustment gasket is 0.01 mm, 0.02 mm, or 0.05 mm.

[0042] In addition, according to different stand-alone products and the actual conditions of the mounting surface 21 , the shape of the cross-sectional edges of the first insulating member 31 and the second insulating member 32 may be a polygon such as a square.

[0043] The utility model provides a first insulating member 31 between the connecting member 3 and the single-unit housing 1, a second insulating member 32 between the single-unit housing 1 and the satellite body 2, and a flexible heat-conducting member 4 between the single-unit housing 1 and the satellite body 2. This eliminates the need to change the material of the structural plate at the contact point between the single-unit or satellite, and eliminates the need for connecting members made of insulating materials, thereby reducing costs.

[0044] The above is only a specific implementation of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed in the present invention should be included in the protection scope of the present invention.

Claims

1. A satellite accessory, characterized in that: The invention comprises a shell (1) for being installed on a satellite body (2), wherein the shell (1) has a bottom plate (11) for abutting against the satellite body (2) and a mounting plate (12) extending from the edge of the bottom plate (11) and parallel to the bottom plate (11); the satellite accessory also comprises a connecting member (3) simultaneously inserted into the mounting plate (12) and the satellite body (2), a first insulating member (31) and a second insulating member (32) sleeved outside the connecting member (3) and respectively abutting against the surfaces of both sides of the mounting plate (12); the first insulating member (31) is used to separate the connecting member (3) from the mounting plate (12), and the second insulating member (32) is used to separate the mounting plate (12) from the satellite body (2).

2. The satellite accessory according to claim 1, characterized in that: The first insulating member (31) comprises a first insulating portion (311) and a first guiding portion (312); the first insulating portion (311) and the first guiding portion (312) are both cylindrical and coaxially connected; the first insulating portion (311) and the first guiding portion (312) have the same inner diameter, and the outer diameter of the first insulating portion (311) is greater than the outer diameter of the first guiding portion (312).

3. The satellite accessory according to claim 2, characterized in that: The axial lengths of the first insulating portion (311) and the second insulating member (32) are both 1.5 to 6.5 mm.

4. The satellite accessory according to claim 2, characterized in that: It also includes a flexible heat-conducting member (4) arranged between the base plate (11) and the satellite body (2), wherein the flexible heat-conducting member (4) is used to separate the base plate (11) from the satellite body (2).

5. The satellite accessory according to claim 4, characterized in that: The second insulating member (32) is also cylindrical in shape, and the difference between its axial length and the distance between the surface of the mounting plate (12) close to the satellite body (2) and the surface of the base plate (11) close to the satellite body (2) is equivalent to the thickness of the flexible heat conductive member (4) when installed.

6. The satellite accessory according to claim 4, characterized in that: The mounting plate (12) is provided with a first connecting hole (121), and the first guiding portion (312) is inserted into the first connecting hole (121).

7. The satellite accessory according to claim 6, characterized in that: The surface of the mounting plate (12) close to the satellite body (2) is recessed inward to form a mounting groove (122) for mounting the second insulating member (32), and the mounting groove (122) is connected to the first connecting hole (121).

8. The satellite accessory according to claim 7, characterized in that: The second insulating member (32) comprises a cylindrical second insulating portion (321) and a second guiding portion (322), wherein the second insulating portion (321) is in contact between the mounting plate (12) and the satellite body (2), the second guiding portion (322) is passed through the first connecting hole (121), and the sum of the lengths of the second guiding portion (322) and the first guiding portion (312) is less than the depth of the first connecting hole (121).

9. The satellite accessory according to any one of claims 1 to 8, characterized in that: It also comprises an adjusting gasket, which is sleeved outside the connecting member (3) and abuts between the second insulating member (32) and the mounting plate (12).

10. A satellite, comprising a satellite body (2), characterized in that: It also includes the satellite accessory according to any one of claims 6 to 8, wherein the satellite body (2) is provided with a mounting surface (21) for mounting the satellite accessory, the mounting surface (21) is provided with a second connecting hole (211), the connecting member (3) is simultaneously passed through the first connecting hole (121) and the second connecting hole (211), and the flexible heat conductive member (4) is arranged between the base plate (11) and the mounting surface (21).

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