A support device and a method for laying a structured cable of a spacecraft using the support device

Abstract

The present invention discloses a supporting device and a method for laying a spacecraft structured cable using the supporting device. The supporting device includes a bracket and a guard plate detachably connected to the bracket. The bracket includes a crossbeam, a left leg, a right leg, a first positioning hole and a second positioning hole. The crossbeam has an upper and lower surface and a first opening. The left and right legs are alternately and vertically arranged on the lower surface of the crossbeam. In the present invention, a flexible circuit board is used to replace the traditional ordinary columnar cable as a component of the power supply subsystem, and a method for stably welding the flexible circuit board and the electrical connector is further provided, and a method for integrating the spacecraft structured cable into the spacecraft structural plate is given. The use of a flexible circuit board to form a spacecraft structured cable can reduce the weight of the spacecraft cable by more than 50%; it can save 20% of the spacecraft installation space, ensuring the overall lightweight of the spacecraft; it can save 20%-30% of the assembly cost, and realize the rapid assembly of the spacecraft.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace engineering, and in particular to a supporting device and a method for laying a structured cable of a spacecraft using the supporting device. Background Art

[0002] As spacecraft gradually develop towards integration and lightweight, new requirements are put forward for spacecraft weight reduction and low cost. Spacecraft cable network is one of the important products that connect various subsystems and realize spacecraft functions, and occupies a large weight ratio of spacecraft. Therefore, the traditional complex cable network urgently needs to seek new lightweight and low-cost methods to meet the application requirements of spacecraft.

[0003] Structured cables are new types of highly integrated cables that meet the requirements of spacecraft development. The cable network is integrated with the spacecraft structural panel by replacing traditional cables with flexible circuit boards and pre-buried in the structural panels. The flexible circuit board uses polyimide film as the substrate, which is small in size and light in weight, and can greatly reduce the weight of the spacecraft. At the same time, the method of embedding the cable network in the spacecraft structure also meets the needs of integration, which is an important direction for the development of future spacecraft. Chinese invention patent CN104527144A discloses a lightweight multifunctional sandwich structure panel, which includes an upper panel, a lower panel and a porous core panel arranged between the upper panel and the lower panel, the upper panel is provided with a plurality of electrical connectors, the porous core panel is provided with a plurality of reinforcement frames and a heat pipe, each reinforcement frame is provided with a cable, and each cable is fixedly connected to an electrical connector. Although Chinese invention patent CN104527144A integrates the spacecraft energy control module into the spacecraft structural panel, which reduces the weight of the spacecraft to a certain extent, it still has the following shortcomings: the cables of the energy module are not further lightweight, so that the energy control circuit board and cables of the spacecraft still occupy a large weight ratio. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a support device and a method for laying a spacecraft structured cable using the support device. In the present invention, a flexible circuit board is used to replace the traditional ordinary columnar cable as a component of the power supply subsystem, and a method for stably electrically connecting the flexible circuit board with the electrical connector is further provided, and a method for integrating the spacecraft structured cable into the spacecraft structural plate is further provided. The purpose of the present invention is achieved by the following technical solutions.

[0005] On the one hand, the present invention provides a support device for supporting a flexible circuit board in a spacecraft structured cable, and simultaneously supporting a spacecraft structural plate integrated with the spacecraft structured cable. The support device includes a bracket and a guard plate; the bracket includes a crossbeam, a left leg, a right leg, a first positioning hole and a second positioning hole; the crossbeam has an upper surface and a lower surface, and a first opening that passes through the upper and lower surfaces of the crossbeam; the left and right legs are alternately and vertically arranged on the lower surface of the crossbeam; the first positioning hole is arranged on the end surface of the free end of the left and right legs, and is used when the spacecraft structured cable is laid using the support device; the second positioning hole is arranged on the lower surface of the crossbeam between the left and right legs, and is used to fix and install the selected electrical connector and flexible circuit board.

[0006] The crossbeam and the left and right legs form a U-shape. The inner side profile dimensions of the crossbeam and the distance between the left and right legs need to be designed according to the outer dimensions of the electrical connector to be fixedly mounted on the bracket, so that the bracket and the selected electrical connector can be tightly and fixedly connected. The second positioning holes are threaded holes, and the size and spacing must match the positioning holes of the electrical connector. The shape of the first opening provided on the crossbeam of the bracket must match the mating surface of the electrical connector. When the electrical connector is fixedly mounted on the bracket, the mating surface of the electrical connector can be exposed from the first opening for electrical connection of the spacecraft circuit system.

[0007] The most important point in the conception of the present invention is to use a flexible circuit board to replace the cables of various parts of the traditional spacecraft, and to integrate the support device into the spacecraft structural plate. The use of such an integrated structural design method has the advantages of reducing the mass of the spacecraft structure, reducing the volume, improving the structural function density, and reducing the number of structural components, which is very suitable for the characteristics of the spacecraft itself. Compared with the traditional design method, the spacecraft structure using an integrated design can reduce the weight by 30% to 40%. The biggest advantage of light weight and small size is the reduction of launch costs, and it is more conducive to the launch of multiple satellites with one rocket.

[0008] In the field of aerospace technology, any technology that can reduce the weight of a spacecraft by 1 kg has extremely important research and development significance and economic significance. Reducing the weight by 1 kg can significantly save launch costs.

[0009] The development of spacecraft is constrained by demand and technology, and more extensive applications require revolutionary breakthroughs and innovations in key technologies. These new technologies mainly include electric propulsion technology, multifunctional structure, electromechanical system, integrated design, advanced memory and computer software technology, and orbit control technology. In terms of multifunctional structure and integrated design, the advanced technology of the present invention overcomes technical difficulties, further reduces the weight of the spacecraft while ensuring stable performance, and uses more advanced technology to support the development of spacecraft.

[0010] In the present invention, another technical problem to be solved is how to achieve a stable electrical connection between a flexible circuit board and an electrical connector. A flexible circuit board, also known as a "soft board", is a printed circuit board made of a flexible insulating substrate. It can be bent, wound, and folded freely, can be arranged arbitrarily according to the spatial layout requirements, and can be moved and stretched arbitrarily in three-dimensional space, so as to achieve the integration of component assembly and wire connection. Flexible circuit boards also have the advantages of good heat dissipation and solderability, easy installation and connection, and low overall cost. However, since the flexible substrate does not have rigidity, the inner contact part of the electrical connector and the inserted part of the flexible board are usually clamped and fixed by a pressing piece and a wedge-shaped push-up block located in the electrical connector housing. This detachable plug-in method is suitable for use in the earth's ground environment. When an unstable connection or a connection failure occurs, it is easy to disassemble and repair. After the spacecraft enters orbit, it needs to work normally for several months, years, or even more than ten years. Therefore, light weight, small size, high reliability, long life, and the ability to withstand complex environmental conditions are the basic requirements of spacecraft materials, devices, and equipment, and are also one of the basic principles of spacecraft design. Once a spacecraft is launched into space to undertake various missions, it is necessary to ensure the stable and trouble-free operation of various systems, especially the electronic control system and energy system. Therefore, as far as spacecraft are concerned, flexible circuit boards and electrical connectors are more suitable for electrical connection by welding. First of all, flexible circuit boards have good heat dissipation and weldability. Secondly, welding connections have excellent electrical connection stability. However, flexible circuit boards are soft and not rigid. They cannot support electrical connectors with a certain weight during welding and are usually not suitable for welding connections. The supporting device provided in the present invention can play a supporting role in the process of welding the electrical connector and the flexible circuit board, making it possible to weld the connection between the flexible circuit board and the welded electrical connector, and ensuring the stable transmission of power and signals.

[0011] Specifically, first, the connection end of the flexible circuit board matching the electrical connector is placed on the electrical connector between the left and right legs. Since the connection end of the flexible circuit board is also provided with a positioning through hole matching the size and position of the second positioning hole, the electrical connector and the flexible circuit board can be fixed to the bracket together with screws to form a bracket assembly. The thickness of the bracket beam, the distance between the left and right legs, the shape and contour of the left and right legs close to the beam, and the contour and size of the inner side of the beam are all customized according to the design of the electrical connector and the flexible circuit board to be installed, so the installation parts of the three can be fixed in close contact, which can ensure that the size of the bracket is minimized, reduce the overall weight of the bracket, and thus reduce the manufacturing and launch costs of the spacecraft.

[0012] The assembled bracket components can be placed in the welding process location for welding. Welding can be done manually.

[0013] Preferably, a wave soldering device is used to solder the electrical connector and the flexible circuit board. Wave soldering is a method of soldering by forming a solder wave of a specific shape on the surface of the molten liquid solder with the help of pump pressure. It is a process technology that forms solder joints in the pin soldering area when the assembly with components inserted passes through the solder wave at a certain angle. The bracket assembly is first preheated in the preheating area of ​​the welder during the process of being conveyed by the chain conveyor. After preheating, the bracket assembly enters the tin bath for soldering. The tin bath contains molten liquid solder, and the nozzle at the bottom of the steel tank sets the molten solder into a wave crest of a certain shape. In this way, the solder wave heats the solder wave when the welding surface of the bracket assembly passes through the wave, and the solder wave also wets the soldering area and expands and fills it, finally realizing the soldering process. Wave soldering is generally used for the soldering of rigid printed circuit boards, and the pins of the rigid printed circuit board provide a path for the liquid solder to immerse into the metallized through-holes. In the present invention, the electrical connector and the flexible circuit board use the bracket as a supporting element to fix the welding terminal and the welding pin together. When the pin contacts the solder wave, the liquid solder climbs up along the pin and the hole wall due to the effect of surface tension. The capillary action of the metallized through-hole further promotes the climbing of the solder. After the solder reaches the pad of the rigid printed circuit board, it spreads out under the surface tension of the pad. The rising solder discharges the flux gas and air in the through-hole, thereby filling the through-hole and finally forming a solder joint after cooling. It is precisely because of the support device of the present invention as a supporting element that the flexible circuit board used for the structured cable of the spacecraft can be electrically connected with the welding type electrical connection using the wave soldering method.

[0014] Preferably, a selective soldering device is used to solder the electrical connector and the flexible circuit board. Selective wave soldering uses a selective flux spraying system, that is, after the flux nozzle runs to the specified position according to the pre-programmed instructions, the flux is only sprayed on the area on the circuit board that needs to be soldered, and the spraying amount in different areas can be adjusted according to the program. For different solder joints, the welding module can personalize the welding time, wave head height and welding position, which facilitates process adjustment, so that the welding effect of each solder joint is optimized.

[0015] According to one aspect of the present invention, the guard plate is embedded in the free ends of the left and right legs. The guard plate and the bracket assembly form a bracket frame assembly with four closed surfaces and two side surfaces of the left and right legs as open surfaces. Such a structure is more effective in protecting the electrical connector and the flexible circuit board. The height of the bracket needs to be greater than the sum of the thicknesses of the electrical connector, the flexible circuit board and the guard plate. When the guard plate is fixedly embedded in the free ends of the left and right legs, there is a certain distance between the guard plate and the flexible circuit board. This distance is used to protect the welding terminals that have been welded.

[0016] According to one aspect of the present invention, optionally, the guard plate covers the free ends of the left and right legs; a third positioning hole is provided on the guard plate, and the third positioning hole is a through hole and matches the first positioning hole. When the bracket assembly and the guard plate are mounted on the spacecraft structure plate, the bracket assembly and the guard plate can be threadedly fixedly connected through the first positioning hole and the third positioning hole, and the connection is more reliable.

[0017] According to one aspect of the present invention, preferably, flanges are provided on the free ends of the left and right legs, and the first positioning hole is located on the flanges. The thickness of the left and right legs close to the crossbeam is further reduced, and the flanges are formed at the free ends. Reducing the thickness of the left and right legs can further reduce the weight of the bracket, thereby reducing the weight of the spacecraft and saving manufacturing and launch costs.

[0018] According to one aspect of the present invention, the first and second positioning holes are threaded holes, the third positioning hole is a through hole, and a threaded fixed connection can be formed between the electrical connector, the flexible circuit board and the bracket.

[0019] In another aspect, the present invention provides a method for laying a structured cable of a spacecraft using the supporting device. The steps are as follows:

[0020] S1. The electrical connector and the flexible circuit board are fixedly mounted on the bracket;

[0021] S2. The assembled bracket assembly is connected to the electrical connector by welding to the flexible circuit board;

[0022] S3. The guard plate is embedded in or fixedly covered across the assembled bracket assembly, and the free ends of the left and right legs are assembled into a bracket frame assembly;

[0023] S4. A fourth positioning hole matching the first positioning hole is provided on the first packaging board, and the first packaging board and the bracket frame assembly are fixedly connected;

[0024] S5. Clamp the honeycomb sandwich between the first and second packaging plates, place the bracket assembly and the guard plate in the gap of the honeycomb sandwich, fix the first and second packaging plates to connect, and expose the docking surface from the outside of the second packaging plate.

[0025] Specifically, in step S1, the fixed installation method is threaded connection.

[0026] Specifically, in step S2, the welding connection is performed by manual welding. Preferably, the crossbeam is placed on top and the left and right legs are placed on the bottom in a wave soldering device for wave soldering. Further preferably, wave selective soldering is used.

[0027] Specifically, in step S3, the embedding and fixing method is bonding.

[0028] Specifically, in step S4, when the guard plate is embedded and fixed between the left and right legs, the bracket and the first packaging plate are fixed as one body using the first and fourth positioning holes;

[0029] When the guard plate is bridged and covers the free ends of the left and right legs, the first, third and fourth positioning holes are used to fix the bracket, the guard plate and the first packaging plate into one body.

[0030] The composite honeycomb sandwich structure has the advantages of high bending stiffness, strong resistance to instability, high specific strength and high specific stiffness, and is widely used in spacecraft structures and becomes the main load-bearing component of spacecraft structures. The composite honeycomb sandwich structure is composed of a honeycomb sandwich and a first packaging plate and a second packaging plate. The first packaging plate and the second packaging plate serve as upper and lower panels, and the honeycomb sandwich is clamped in the middle to form a spacecraft structural plate. After the bracket frame assembly is placed in the notch of the honeycomb sandwich, the upper crossbeam and the lower guard plate can provide more rigid support for the upper and lower panels.

[0031] Compared with the prior art, the present invention has the following significant beneficial effects:

[0032] The support device provided by the present invention has three functions at the same time. First, it is used as a welding support tool during the process of welding the electrical connector and the flexible circuit board. Then, after the guard plate is set on the welded bracket assembly, the rigid support device with a frame structure can well protect the welded electrical connector and the flexible circuit board. There is no need to install an additional honeycomb interlayer in the accommodating cavity of the frame assembly, which prevents the electrical connector and the flexible circuit board from being bumped or scratched by the honeycomb interlayer, thereby ensuring the stability of the electrical connection. In addition, it is very important that after the assembled support device is installed on the structural plate, it can well support the first packaging plate and the second packaging plate of the spacecraft structural plate, constitute a spacecraft structural plate support component of the integrated structured cable, and ensure the strength and rigidity of the spacecraft.

[0033] In the method of paving a spacecraft structured cable using the support device of the present invention, a flexible circuit board is used instead of a traditional cable, which greatly reduces the weight of the spacecraft energy and communication system. A method for assembling a flexible circuit board and an electrical connector is further provided, and a method for paving a spacecraft structured cable is provided using the support device, thereby finally forming an integrated structure that highly integrates electrical functional parts and structural parts. In the process of implementing the entire method, on the basis of ensuring the function, starting from reducing the weight of the spacecraft, from the perspective of saving manufacturing costs and launch costs, the use of a flexible circuit board to form a spacecraft structured cable can reduce the weight of the spacecraft cable insulation structure by more than 50%, can save 20% of the spacecraft installation space, maximize the installation space of the spacecraft load including antennas, optical cameras, etc., and ensure the overall lightweight of the spacecraft; and greatly simplify the process of spacecraft assembly, effectively improve the efficiency of single machine or spacecraft assembly, can save 20%-30% of assembly costs, and realize the rapid assembly of spacecraft. The support device is set according to the size of different electrical connectors and flexible circuit boards, so that the support device and the structured cable can be installed tightly and integrally, and the flexible circuit board and the electrical connector can be buried and positioned internally to protect them, while reducing their own weight as much as possible, which can further reduce the weight of the integrated structural plate of the spacecraft. In summary, the support device and the method of paving the structured cable of the spacecraft using the support device involved in the present invention have overcome the technical difficulties that hinder the development of spacecraft and provided assistance for the development of spacecraft. Any component in aerospace costs millions of dollars, and a spacecraft system can be sold at a market price of several hundred million. From an economic point of view, being able to reduce the weight of the spacecraft cable by more than 50% and saving 20%-30% of the assembly cost can save a lot of manufacturing cost and launch cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1is a schematic diagram of a three-dimensional structure of a support device of an embodiment of the present invention;

[0035] Figure 2 is a schematic diagram of a three-dimensional structure of an embodiment of a guard plate of a supporting device of the present invention;

[0036] Figure 3 It is an assembly schematic diagram of an embodiment of the method for laying a structured cable of a spacecraft using the supporting device of the present invention;

[0037] Figure 4 It is a general assembly cross-sectional view of an embodiment of the method for laying a structured cable of a spacecraft using the supporting device of the present invention;

[0038] Figure 5 It is a flow chart of an implementation method of the present invention for laying spacecraft structured cables using the supporting device.

[0039] Figure numbers: 1-bracket; 11-crossbeam; 111-first opening; 12-left leg; 12a-left flange; 13-right leg; 13a-right flange; 14-first positioning hole; 15-second positioning hole; 2-guard plate; 3-electric connector; 4-flexible circuit board; 5-first packaging board; 6-second packaging board; 7-honeycomb sandwich; DETAILED DESCRIPTION

[0040] In order to more clearly illustrate the implementation of the present invention or the technical solutions in the prior art, the drawings required for use in the implementation are briefly introduced below. Obviously, the drawings described below are only some implementations of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0041] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0042] Figure 1 and Figure 2 It is a schematic diagram of the three-dimensional structure of an embodiment of the supporting device of the present invention. Figure 3 It is a schematic assembly diagram of an embodiment of the method for laying spacecraft structured cables using a supporting device according to the present invention. Figure 4 It is an assembly cross-sectional view of an embodiment of a method for laying spacecraft structured cables using a supporting device according to the present invention.

[0043] like Figure 1 , Figure 2 and Figure 4As shown, in one embodiment of the support device provided by the present invention, the support device includes a bracket 1 and a guard plate 2. The bracket 1 includes a crossbeam 11, a left leg 12, a right leg 13, a first positioning hole 14 and a second positioning hole 15. The crossbeam 11 has an upper surface and a lower surface, and a first opening 111 that passes through the upper and lower surfaces of the crossbeam 11, and the left and right legs 12, 13 are alternately and vertically arranged on the lower surface of the crossbeam 11. The first positioning hole 14 is arranged on the end surface of the free ends of the left and right legs 12, 13. The second positioning hole 15 is arranged on the lower surface of the crossbeam 11 between the left and right legs 12, 13.

[0044] In this embodiment, the bracket 1 needs to be designed and customized according to the size of different types of electrical connectors 3 and the width of the flexible circuit board 4. A first opening 111 that matches the size of the mating surface of the electrical connector 3 is provided in the middle of the bracket 1 to ensure that the mating surface of the electrical connector 3 can be fully exposed. A second positioning hole 15 corresponding to the position of the mounting hole of the electrical connector 3 is provided on the lower surface of the crossbeam 11 between the left and right legs 12 and 13, and is specifically a threaded hole for fixed connection between the bracket 1 and the electrical connector 3 and the flexible circuit board 4. The width between the left and right legs 12 and 13 of the bracket 1 is set according to the width of the flexible circuit board 4, and is slightly larger than the width of the flexible circuit board 4. Figure 2 Shown is the Figure 1 The support 1 shown is matched with a guard plate 2 , and the guard plate 2 can be embedded between the left and right legs 12 , 13 of the support 1 .

[0045] In this embodiment, preferably, left and right flanges 12a and 13a are provided on the free ends of the left and right legs 12 and 13. The left and right flanges 12a and 13a are obtained by removing a portion of the material of the left and right legs 12 and 13 close to the cross beam 11. The thickness of the portions of the left and right legs 12 and 13 close to the cross beam 11 is reduced, further reducing the overall weight of the bracket 1. Threaded through holes are provided on the left and right flanges 12a and 13a, which are first positioning holes 14, and are used for connecting and fixing the bracket 1 to the spacecraft structure plate in the subsequent sequence.

[0046] In another embodiment of the support device provided by the present invention, the support device includes a bracket and a guard plate. The bracket includes a crossbeam, a left leg, a right leg, a first positioning hole and a second positioning hole. The crossbeam has an upper surface and a lower surface, and a first opening that passes through the upper and lower surfaces of the crossbeam, and the left and right legs are alternately and vertically arranged on the lower surface of the crossbeam. The first positioning hole is arranged on the end surface of the free end of the left and right legs. The second positioning hole is arranged on the lower surface of the crossbeam between the left and right legs.

[0047] In this embodiment, the bracket needs to be designed and customized according to the size of different types of electrical connectors 3 and the width of the flexible circuit board 4. A first opening that matches the size of the mating surface of the electrical connector 3 is provided in the middle of the bracket to ensure that the mating surface of the electrical connector 3 can be fully exposed. A second positioning hole corresponding to the position of the mounting hole of the electrical connector 3 is provided on the lower surface of the crossbeam 11 between the left and right legs 12 and 13, specifically a threaded hole, which is used for the fixed connection between the bracket and the electrical connector 3 and the flexible circuit board 4. The width between the left and right legs of the bracket is set according to the width of the flexible circuit board 4, which is slightly larger than the width of the flexible circuit board 4. The free ends of the left and right legs are provided with threaded through holes, which are the first positioning holes, which are used for the connection and fixation of the bracket and the spacecraft structure plate in the subsequent sequence. The guard plate spans and covers the free ends of the left and right legs, and a third positioning hole is provided on the guard plate. The third positioning hole is a through hole and matches the first positioning hole. In the subsequent assembly process, the first positioning hole, the third positioning hole and the fourth positioning hole provided on the first packaging board are used to fix the bracket, the guard plate and the first packaging board 5 into one piece with screws. This structure makes the connection between the bracket and the guard plate more firm and stable.

[0048] Figure 5 It is a flow chart of an embodiment of the method for laying spacecraft structured cables using a supporting device of the present invention.

[0049] like Figure 4 and Figure 5 As shown, in step S1, the electrical connector 3 and the flexible circuit board 4 are fixedly mounted on the bracket 1; specifically, the pins of the electrical connector 3 are first placed in cooperation with the corresponding welding terminals on the flexible circuit board 4, and then the bracket 1 is placed on the electrical connector 3 so that the mating surface of the electrical connector 3 is exposed from the first opening 111 on the bracket 1. The flexible circuit board 4 needs to be provided with a through hole corresponding to the threaded hole of the second positioning hole 15 on the bracket 1, and the flexible circuit board 4, the electrical connector 3 and the bracket 1 are fixed together from the bottom of the flexible circuit board 4 with screws.

[0050] The height of the bracket 1 is consistent with the spacing between the upper and lower plates of the spacecraft structure plate and is greater than the sum of the thicknesses of the electrical connector 3, the flexible circuit board 4 and the guard plate 2. In this way, when the electrical connector 3 and the flexible circuit board 4 are fixed to the bracket 1 and the guard plate 2 is bonded between the left and right legs 12 and 13, there can be a protective spacing between the flexible circuit board 4 and the guard plate 2 to protect the welding terminals of the flexible circuit board 4 from being bumped during subsequent operations, thereby ensuring the stability of the electrical connection.

[0051] In step S2 , the assembled electrical connector 3 on the bracket assembly is connected to the flexible printed circuit board 4 by welding.

[0052] Specifically, after the electrical connector 3 and the flexible circuit board 4 are fixed together by the bracket 1, wave soldering can be used for connection. The bracket 1 is placed in the wave soldering equipment with the crossbeam 11 on top and the left and right legs 12 and 13 on the bottom. Due to the open design below the bracket 1 and the rigidity of the bracket 1 itself, the conditions for placing the flexible circuit board 4 in the wave soldering equipment for soldering can be met. Because the bracket 1 has a certain weight, after the flexible circuit board 4 is fixed on the bracket 1, during the soldering process, the flexible circuit board 4 will not be pushed up by the soldering wave due to the lightness of the flexible circuit board 4 or the lifting force of the wave, causing the flexible circuit board 4 to be skewed or lifted. The wave soldering method can greatly improve the efficiency of the connection of structured cables and improve the accuracy of soldering and connection.

[0053] In step S3, the guard plate 2 is embedded in the free ends of the left and right legs 12, 13 of the assembled bracket assembly. Specifically, the free ends of the left and right legs 12, 13 are provided with notches matching the shape of the guard plate 2, and the guard plate 2 is embedded and bonded to the left and right legs 12, 13 to assemble the bracket frame assembly.

[0054] In step S4, a fourth positioning hole matching the first positioning hole 14 is provided on the first packaging board 5, and the first packaging board 5 and the bracket frame assembly are fixed together;

[0055] The flexible circuit board 4 at the connection point of the electrical connector 3 needs to maintain a certain distance from the first packaging board 5 due to the exposed solder terminals below, which is the protection distance. The bracket 1 is designed with left and right legs 12 and 13, which can increase the height of the flexible circuit board 4 at the connection point by a certain distance to obtain the protection distance. Figure 2 The guard plate 2 shown is bonded between the notches of the free ends of the left and right legs 12 and 13 below the electrical connector 3, which can protect the welding terminals of the electrical connector 3 and support the first packaging plate 5 of the structural plate, thereby protecting the flexible circuit board 4 when the structural plate is under pressure. A fourth positioning hole corresponding to the threaded through hole of the left and right legs 12 and 13 of the bracket 1 needs to be provided at the contact point of the first packaging plate 5 with the left and right legs 12 and 13 of the bracket 1. The first packaging plate 5 of the structural plate is fixed to the bracket frame assembly from the top and bottom with screws.

[0056] In step S5 , the honeycomb sandwich 7 is clamped between the first and second packaging plates 5 , 6 , the bracket frame assembly is accommodated in the gap of the honeycomb sandwich 7 , the first and second packaging plates 5 , 6 are fixedly connected, and the docking surface of the electrical connector 3 is exposed from the outside of the second packaging plate 6 .

[0057] Specifically, the upper surface of the bracket 1 is fitted with the second packaging plate 6 of the structural plate. The second packaging plate 6 of the structural plate is provided with a second opening, which is located at the same position as the first opening 111 of the crossbeam 11 of the bracket 1 and is slightly larger in size to ensure that the mating surface of the electrical connector 3 can be fully exposed. Figure 2 The guard plate 2 shown can well support the first and second packaging plates 5 and 6 of the structural plate, so that the filling of the complex honeycomb sandwich 7 between the bracket frame assembly on which the flexible circuit board 4 and the electrical connector 3 are installed is not required. The honeycomb sandwich 7 with many sharp structures is prevented from causing damage to the flexible circuit board 4. Next, a notch matching the shape of the bracket frame assembly is set on the honeycomb sandwich 7, the honeycomb sandwich 7 is clamped between the first and second packaging plates 5 and 6, the bracket frame assembly is accommodated in the notch of the honeycomb sandwich 7, the first and second packaging plates 5 and 6 are fixedly connected, and the butt joint surface is exposed from the outside of the second packaging plate 6.

[0058] Figure 5 The present invention is also a flow chart of another embodiment of the method for laying spacecraft structural cables using a supporting device.

[0059] like Figure 3 and Figure 5 As shown, in step S1, the electrical connector 3 and the flexible circuit board 4 are fixedly mounted on the bracket; specifically, the pins of the electrical connector 3 are first placed in cooperation with the corresponding welding terminals on the flexible circuit board 4, and then the bracket is placed on the electrical connector 3 so that the mating surface of the electrical connector 3 is exposed from the first opening on the bracket. The flexible circuit board 4 needs to be provided with a through hole corresponding to the threaded hole of the second positioning hole on the bracket, and the flexible circuit board 4, the electrical connector 3 and the bracket are fixed together from the bottom of the flexible circuit board 4 with screws.

[0060] The height of the bracket is consistent with the spacing between the upper and lower plates of the spacecraft structure plate and is greater than the sum of the thicknesses of the electrical connector 3, the flexible circuit board 4 and the protective plate. In this way, when the electrical connector 3 and the flexible circuit board 4 are fixed to the bracket and the protective plate is bridged and covered on the free end surfaces of the left and right legs, there can be a protective spacing between the flexible circuit board 4 and the protective plate to protect the welding terminals of the flexible circuit board 4 from being bumped during subsequent operations, thereby ensuring the stability of the electrical connection.

[0061] In step S2 , the assembled electrical connector 3 on the bracket assembly is connected to the flexible printed circuit board 4 by welding.

[0062] Specifically, after the electrical connector 3 and the flexible circuit board 4 are fixed together by the bracket, wave soldering can be used for connection. Specifically, the crossbeam is placed on top and the left and right legs are placed on the bottom, and the wave soldering equipment is placed. Due to the open design under the bracket and the rigidity of the bracket itself, the flexible circuit board 4 can be placed in the wave soldering equipment for soldering. For different soldering points, the soldering module can personalize the soldering time, wave head height and soldering position, so as to achieve the best soldering effect for each soldering point.

[0063] In step S3, the guard plate spans and covers the free ends of the left and right legs, and a third positioning hole is set on the guard plate. The third positioning hole is a through hole and matches the first positioning hole.

[0064] In step S4, a fourth positioning hole matching the first positioning hole is set on the first packaging board 5, and then the first positioning hole, the third positioning hole and the fourth positioning hole set on the first packaging board are used to fix the bracket, the guard plate and the first packaging board 5 into one piece with screws. This structure makes the connection between the bracket and the guard plate more firm and stable. The fixing of the bracket frame assembly assembled by the bracket and the guard plate and the fixing of the bracket frame assembly and the first packaging board 5 are completed in the same process, which simplifies the assembly process and saves assembly time and cost.

[0065] The flexible circuit board 4 at the connection point of the electrical connector 3 needs to maintain a certain distance from the first packaging board 5 due to the exposed welding terminals below, which is the protection distance. The bracket is designed with a left and right leg structure, which can play the role of raising the flexible circuit board 4 at the connection point by a certain distance to obtain the protection distance.

[0066] In step S5 , the honeycomb sandwich 7 is clamped between the first and second packaging plates 5 , 6 , the support frame assembly is accommodated in the gap of the honeycomb sandwich 7 , the first and second packaging plates 5 , 6 are fixedly connected, and the butt joint surface is exposed from the outside of the second packaging plate 6 .

[0067] Fit the upper surface of the bracket to the second packaging plate 6 of the structural plate. The second packaging plate 6 of the structural plate is provided with a second opening, which is located at the same position as the first opening of the bracket crossbeam and is slightly larger in size to ensure that the docking surface of the electrical connector 3 can be fully exposed. The crossbeam and guard plate of the bracket can well support the first and second packaging plates 5, 6 of the structural plate, so that there is no need for complex honeycomb interlayer 7 to be filled between the bracket frame assembly on which the flexible circuit board 4 and the electrical connector 3 are installed. The honeycomb interlayer 7 with many sharp structures is prevented from causing damage to the flexible circuit board 4. A notch matching the shape of the bracket frame assembly is provided on the honeycomb interlayer 7, the honeycomb interlayer 7 is clamped between the first and second packaging plates 5, 6, the bracket frame assembly is accommodated in the notch of the honeycomb interlayer 7, the first and second packaging plates 5, 6 are fixedly connected, and the docking surface is exposed from the outside of the second packaging plate 6.

[0068] The above contents are merely examples of specific technical solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they are implemented by adopting general devices and general methods available in the art.

[0069] The above is only a specific implementation of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A supporting device, characterized in that: Comprising a bracket (1) and a guard plate (2); The bracket (1) comprises a crossbeam (11), a left leg (12), a right leg (13), a first positioning hole (14) and a second positioning hole (15); The crossbeam (11) has an upper surface and a lower surface, and a first opening (111) penetrating the upper and lower surfaces of the crossbeam (11); the left and right legs (12, 13) are alternately and vertically arranged on the lower surface of the crossbeam (11); The first positioning hole (14) is arranged on the end surfaces of the free ends of the left and right supporting legs (12, 13); the second positioning hole (15) is arranged on the lower surface of the crossbeam (11) between the left and right supporting legs (12, 13); The guard plate (2) is embedded in or straddles and covers the free ends of the left and right legs (12, 13).

2. The support device according to claim 1, characterized in that: The first and second positioning holes (14, 15) are threaded holes.

3. The supporting device according to claim 1, characterized in that: A third positioning hole is provided on the guard plate (2), the third positioning hole being a through hole and matching the first positioning hole (14).

4. The supporting device according to claim 2, characterized in that: The free ends of the left and right supporting legs (12, 13) are provided with left and right flanges (12a, 13a), and the first positioning hole (14) is located on the left and right flanges (12a, 13a).

5. The supporting device according to claim 3, characterized in that: The free ends of the left and right supporting legs (12, 13) are provided with left and right flanges (12a, 13a), and the first positioning hole (14) is located on the left and right flanges (12a, 13a).

6. A method for laying a spacecraft structured cable using the support device according to any one of claims 1 to 5, the steps of which are as follows: S1. The electrical connector (3) and the flexible circuit board (4) are fixedly mounted on the bracket (1) to form a bracket assembly; S2. The electrical connector (3) on the assembled bracket assembly is welded to the flexible circuit board (4); S3. The guard plate (2) is embedded and fixed or bridged to cover the free ends of the left and right legs (12, 13) of the assembled bracket assembly to form a bracket frame assembly; S4. A fourth positioning hole matching the first positioning hole (14) is provided on the first packaging plate (5), and the first packaging plate (5) and the bracket frame assembly are fixed together; S5. Clamp the honeycomb sandwich (7) between the first and second packaging plates (5, 6), accommodate the support frame assembly in the notch of the honeycomb sandwich (7), fix the first and second packaging plates (5, 6) to connect, and expose the docking surface of the electrical connector (3) from the outside of the second packaging plate (6).

7. The method according to claim 6, characterized in that In the step S1, the fixed installation method is threaded connection.

8. The method according to claim 6, characterized in that In step S2, the welding connection is carried out by manual welding or by placing the crossbeam (11) at the top and the left and right legs (12, 13) at the bottom into a wave soldering device or a wave selective soldering device for wave soldering.

9. The method according to claim 6, characterized in that In the step S3, the embedding and fixing method is bonding.

10. The method according to claim 6, characterized in that In the step S4, the guard plate (2) is embedded and fixed between the left and right legs (12, 13), and the bracket (1) and the first packaging plate (5) are fixed as a whole using the first positioning hole (14) and the fourth positioning hole; When the guard plate (2) spans and covers the free ends of the left and right legs (12, 13), the bracket (1), the guard plate (2) and the first packaging plate (5) are fixed as a whole using the first positioning hole (14), the third positioning hole on the guard plate (2) and the fourth positioning hole.

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