Satellite frame and solar wing yoke metal insert feedthrough structure and method

Abstract

The application provides a metal embedded part conducting structure and method of a satellite frame and a solar wing connecting frame, which comprises a rod, a plurality of embedded parts, wires and joints. At least two hollow structures are arranged on the embedded parts, the hollow structures reduce the weight of the embedded parts, the wires are wound around the embedded parts through the hollow structures, the wires do not affect the outer surfaces of the embedded parts, the outer surfaces of the embedded parts are in contact with the inner part of the rod, the winding and the contact do not affect each other, and the wires do not affect the subsequent assembly of the rod after being wound around the embedded parts. The plurality of embedded parts form an integral whole through the wires, the embedded parts are fixedly installed in the rod after the two ends of the wires are fixed, and the rod and the embedded parts form a complete conductor. As long as one embedded part is in conduction with the rod, the remaining embedded parts are also in conduction, all the embedded parts can be in conduction at the same time, and the electrical conduction of the frame body is effectively ensured.

Description

Technical Field

[0001] This invention relates to satellite frame structures, and more specifically, to a metal embedded conductive structure and method for connecting a satellite frame and a solar panel. Background Technology

[0002] The main structure of a satellite comprises numerous planar frames and three-dimensional trusses, while the satellite's solar panels typically include connecting frames. All of these structures are frame structures, assembled from several members via joints. These members are generally hollow cavities with a certain wall thickness, and contain several embedded parts.

[0003] Satellite frames, trusses, and solar panel connectors generally require the entire frame to be a uniform conductor, except for a few clearly insulated areas. Embedded components are typically bonded to the members using structural adhesive, which is an insulating material. This can lead to the embedded components being isolated by the adhesive, resulting in excessive insulation or resistance. For embedded components with poor insulation or conductivity, the traditional method is to use conductive adhesive, which is formulated with silver powder-filled structural adhesive. This conductive adhesive is unstable. Under conditions such as temperature and humidity changes in the storage environment and vibrations during transportation, the adhesive surface may age, become loose, or crack, leading to increased resistance.

[0004] Chinese patent CN223625230U discloses a high-conductivity solar panel substrate. It includes a substrate body and a metal embedded member. The substrate body comprises a honeycomb structure and a skin covering the surface of the honeycomb structure. The metal embedded member is embedded within the honeycomb structure. Copper wire is wound around the metal embedded member, with one end of the wire wound and fixed to the metal embedded member, and the other end extending away from the metal embedded member until it connects with the honeycomb structure. This prior art uses copper wire to connect the metal embedded member to the honeycomb structure, thereby improving the conductivity between the embedded member and the honeycomb structure. This fundamentally solves the problem of poor contact or high conductivity resistance between embedded members and other embedded members in the solar panel substrate, avoiding the need for repeated rework due to non-conductivity or poor conductivity of the grounding embedded member between solar panel substrates.

[0005] However, the other end of the copper wire in the high-conductivity solar panel substrate is connected to the honeycomb, achieving the conductivity effect of a single embedded part. Furthermore, the copper wire in the high-conductivity solar panel substrate is wound around the outside of the embedded part. When the embedded part is placed in the rod body, the copper wire cannot wrap around the embedded part. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a metal embedded conductive structure and method for connecting satellite frames and solar array connectors.

[0007] According to the present invention, a metal embedded conductive structure for a satellite frame and solar panel connecting frame includes: a rod, multiple embedded parts, a wire, and a connector; Each of the plurality of embedded parts includes at least two hollow structures. The wire passes through the hollow structure to wrap and fix the embedded part. The wire extends to the next embedded part and passes through the hollow structure to wrap and fix the next embedded part. The plurality of embedded parts are connected sequentially by the wire. The rod has a hollow structure, and the end of the wire is fixed to the inner cavity of the rod or the connector. Multiple embedded parts are respectively fixed in the cavity of the rod through the wire, and the outer surface of the embedded parts is in contact with the inner surface of the cavity of the rod.

[0008] Preferably, the wire is fixed with conductive adhesive after being wound around each of the embedded parts; Alternatively, the wire may be wound around each of the embedded parts and then secured with aluminum-based tape.

[0009] Preferably, the end of the conductor is fixed to the inner cavity of the rod with structural adhesive; Alternatively, the end of the wire is fixed to the inward-facing side of the tenon of the connector with structural adhesive.

[0010] Preferably, the structural adhesive is a conductive adhesive.

[0011] Preferably, the end of the conductor is fixed to the inner cavity of the rod with aluminum-based tape; Alternatively, the end of the wire is fixed to the inward-facing side of the tenon of the connector with aluminum-based tape.

[0012] Preferably, the metal embedded conductive structure further includes a conductive screw; The through screw is secured to the end of the wire; the inner side of the tenon of the connector has a pre-drilled internal thread through hole. The through screw is screwed into the internal thread through hole, and the wire is connected to the connector.

[0013] Preferably, after the through screw is screwed into the internal thread through hole on the tenon, it is fixed at the screw head of the through screw with structural adhesive.

[0014] Preferably, the structural adhesive is a conductive adhesive.

[0015] Preferably, after the conductive screw is bound to the wire, it is fixed with aluminum-based adhesive tape; After the guide screw is screwed into the internal threaded guide hole on the tenon, it is fixed at the screw head with aluminum-based tape.

[0016] According to the present invention, a method for conducting metal embedded parts of a satellite frame and a solar panel connector is provided, for the metal embedded part conducting structure of the satellite frame and solar panel connector as described in any one of the above-mentioned methods, comprising: Step S1: Set at least two hollow structures on each of the multiple embedded parts; Step S2: Install multiple embedded parts into the rod body, and use a wire to wind and fix the embedded parts by passing through the hollow structure of the embedded parts. The wire extends to the next embedded part and winds and fixes the next embedded part by passing through the hollow structure. Step S3: Repeat step S2 until the wire has wrapped and fixed all the embedded parts. Step S4: Fix the end of the wire to the inner cavity or connector of the rod; at this time, multiple embedded parts are respectively fixed in the cavity of the rod through the wire, and the outer surface of the embedded part is in contact with the inner surface of the cavity of the rod.

[0017] Compared with the prior art, the present invention has the following beneficial effects: This invention utilizes at least two perforated structures on the embedded parts. These perforations reduce the weight of the embedded parts, and the wires are wound around them without affecting the outer surface of the embedded parts. The outer surface of the embedded parts is in contact with the interior of the rod, and the winding and contact do not interfere with each other. The winding of the wires around the embedded parts does not affect the subsequent assembly of the rod. The wires allow multiple embedded parts to form a single unit, and after fixing both ends of the wires, the embedded parts are fixedly installed in the rod. The rod and embedded parts form a complete conductor. If one embedded part is conductive to the rod, the rest will also be conductive, ensuring the electrical conductivity of the frame effectively. Attached Figure Description

[0018] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the metal embedded conductive structure that mainly embodies the satellite frame and solar panel connecting frame of the present invention; Figure 2 This is a schematic diagram illustrating the structure of the embedded part, which is the main feature of this invention.

[0019] The figure shows: 1. Rod; 2. Embedded part; 21. Hollow structure; 3. Wire; 4. Connector; 41. Internal threaded through hole; 5. Conductor screw. Detailed Implementation

[0020] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0021] like Figure 1 As shown, a metal embedded conductive structure for a satellite frame and solar panel connector according to the present invention includes: a rod 1, multiple embedded parts 2, a wire 3, and a connector 4.

[0022] Multiple embedded parts 2 each include at least two hollow structures 21. Wires 3 pass through the hollow structures 21 and are wrapped and fixed to the embedded parts 2. Wires 3 extend to the next embedded part 2 and pass through the hollow structures 21 to wrap and fix the next embedded part. Multiple embedded parts 2 are connected sequentially by wires 3. Wires 3 are wrapped around the embedded parts 2, making close contact with each embedded part (2). A single wire 3 connects multiple embedded parts 2 into a whole.

[0023] The rod 1 has a hollow structure, and both ends of the rod 1 can be connected to connectors 4; or, either end can be connected to a connector 4, or neither end can be connected to a connector 4. The tenon of the connector 4 is the part of the connector 4 that is inserted into the rod 1. The rod 1 has a certain wall thickness, and the end of the wire 3 is fixed to the inner cavity of the rod 1 or the connector 4. Multiple embedded parts 2 are respectively fixed in the cavity of the rod 1 through the wire 3, and the outer surface of the embedded parts 2 is in contact with the inner surface of the cavity of the rod 1.

[0024] The method for metal embedded component conduction of satellite frame and solar wing connector according to the present invention, used to manufacture the above-mentioned metal embedded component conduction structure of satellite frame and solar wing connector, includes: Step S1: Set at least two hollow structures 21 on each of the multiple embedded parts 2.

[0025] Step S2: Install multiple embedded parts 2 in the cavity of the rod 1, and use wires 3 to wind and fix the embedded parts 2 through the hollow structure 21. The wires 3 extend to the next embedded part 2 and wind and fix the next embedded part through the hollow structure 21.

[0026] Step S3, repeat step S2 until the wire 3 wraps around and fixes all the embedded parts 2.

[0027] In step S4, the end of the wire 3 is fixed to the inner cavity of the rod 1 or the connector 4. At this time, multiple embedded parts 2 are respectively fixed in the cavity of the rod 1 through the wire 3, and the outer surface of the embedded part 2 is in contact with the inner surface of the cavity of the rod 1.

[0028] At least two perforated structures 21 are provided on the embedded part 2. The perforated structures 21 reduce the weight of the embedded part 2. The wire 3 is wound around the embedded part through the perforated structures 21 without affecting the outer surface of the embedded part 2. The outer surface of the embedded part 2 is in contact with the inside of the rod 1. The winding and contact do not affect each other. The winding of the wire 3 around the embedded part 2 does not affect the subsequent assembly of the rod 1. The multiple embedded parts 2 are formed into a whole by the wire 3. After the two ends of the wire 3 are fixed, the embedded part 2 is fixedly installed in the rod 1. The rod 1 and the embedded part 2 form a complete conductor. As long as one embedded part 2 is conductive to the rod 1, the other embedded parts 2 will also be conductive. All embedded parts 2 can be conductive at the same time, effectively ensuring the electrical conductivity of the frame.

[0029] In one feasible implementation, the wire 3 is wrapped around each embedded part 2 and then secured with conductive adhesive. Alternatively, the wire 3 is wrapped around each embedded part 2 and then secured with aluminum-based tape.

[0030] In one feasible implementation, the end of the conductor 3 is fixed to the inner cavity of the rod 1 with structural adhesive. Alternatively, the end of the conductor 3 is fixed to the inward-facing surface of the tenon of the connector 4 with structural adhesive.

[0031] In one feasible implementation, the structural adhesive is a conductive adhesive.

[0032] In one feasible implementation, the end of the conductor 3 is fixed to the inner cavity of the rod 1 with aluminum-based tape; or, the end of the conductor 3 is fixed to the surface of the tenon of the connector 4 facing inward with aluminum-based tape.

[0033] In one feasible implementation, the metal embedded conductive structure further includes a conductive screw 5.

[0034] The through screw 5 is secured to the end of the wire 3. The inner side of the tenon of the connector 4 has a pre-drilled internal thread through hole 41.

[0035] The through screw 5 is screwed into the internal thread through hole 41, and the wire 3 is connected to the connector 4.

[0036] In one feasible implementation, after the through screw 5 is screwed into the internal threaded through hole 41 on the tenon, it is fixed at the screw head of the through screw 5 with structural adhesive.

[0037] In one feasible implementation, the structural adhesive is a conductive adhesive.

[0038] In one feasible implementation, after the conductive screw 5 is bound to the wire 3, it is fixed with aluminum-based tape; after the conductive screw 5 is screwed into the internal threaded through hole 41 on the tenon, it is fixed at the screw head of the conductive screw 5 with aluminum-based tape.

[0039] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0040] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A metal embedded conductive structure for connecting a satellite frame and a solar panel, characterized in that, include: Rod (1), multiple embedded parts (2), wire (3) and connector (4); Each of the multiple embedded parts (2) includes at least two hollow structures (21). The wire (3) passes through the hollow structure (21) to wrap and fix the embedded part (2). The wire (3) extends to the next embedded part (2) and passes through the hollow structure (21) to wrap and fix the next embedded part. The multiple embedded parts (2) are connected in sequence through the wire (3). The rod (1) has a hollow structure. The end of the wire (3) is fixed to the inner cavity of the rod (1) or the connector (4). Multiple embedded parts (2) are fixedly installed in the cavity of the rod (1) through the wire (3). The outer surface of the embedded part (2) is in contact with the inner surface of the cavity of the rod (1).

2. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 1, characterized in that, The wire (3) is wrapped around each of the embedded parts (2) and then fixed with conductive adhesive; Alternatively, the wire (3) is wrapped around each of the embedded parts (2) and then fixed with aluminum-based tape.

3. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 1, characterized in that, The end of the conductor (3) is fixed to the inner cavity of the rod (1) with structural adhesive; Alternatively, the end of the wire (3) is fixed to the inward side of the tenon of the connector (4) with structural adhesive.

4. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 3, characterized in that, The structural adhesive is a conductive adhesive.

5. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 1, characterized in that, The end of the conductor (3) is fixed to the inner cavity of the rod (1) with aluminum-based tape; Alternatively, the end of the wire (3) is fixed to the inward side of the tenon of the connector (4) with aluminum-based tape.

6. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 1, characterized in that, The metal embedded conductive structure also includes a conductive screw (5). The through screw (5) is bound to the end of the wire (3); the inner thread through hole (41) is pre-made on the tenon side of the connector (4). The through screw (5) is screwed into the internal thread through hole (41), and the wire (3) is connected to the connector (4).

7. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 6, characterized in that, After the through screw (5) is screwed into the internal thread through hole (41) on the tenon, it is fixed at the screw head of the through screw (5) with structural adhesive.

8. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 7, characterized in that, The structural adhesive is a conductive adhesive.

9. The metal embedded conductive structure for the satellite frame and solar panel connecting frame as described in claim 6, characterized in that, After the conductive screw (5) is bound to the wire (3), it is fixed with aluminum-based tape; After the through screw (5) is screwed into the internal thread through hole (41) on the tenon, aluminum-based tape is used to fix the screw head of the through screw (5).

10. A method for establishing electrical connection between a metal embedded part of a satellite frame and a solar panel connector, characterized in that, The metal embedded conductive structure for manufacturing the satellite frame and solar panel connector frame according to any one of claims 1 to 9 comprises: Step S1: Set at least two hollow structures (21) on each of the multiple embedded parts (2); Step S2: Install multiple embedded parts (2) inside the rod body (1), and use a wire (3) to pass through the hollow structure (21) of the embedded part (2) to wind and fix the embedded part (2). The wire (3) extends to the next embedded part (2) and passes through the hollow structure (21) to wind and fix the next embedded part. Step S3, repeat step S2 until the wire (3) wraps and fixes all the embedded parts (2); Step S4: Fix the end of the wire (3) to the inner cavity or connector (4) of the rod (1); at this time, multiple embedded parts (2) are fixedly installed in the cavity of the rod (1) through the wire (3), and the outer surface of the embedded part (2) is in contact with the inner surface of the cavity of the rod (1).

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