CN114255913A - Satellite integrated cable structure and satellite - Google Patents
Satellite integrated cable structure and satellite Download PDFInfo
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- CN114255913A CN114255913A CN202111348066.6A CN202111348066A CN114255913A CN 114255913 A CN114255913 A CN 114255913A CN 202111348066 A CN202111348066 A CN 202111348066A CN 114255913 A CN114255913 A CN 114255913A
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B7/00—Insulated conductors or cables characterised by their form
- H01B7/08—Flat or ribbon cables
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B7/00—Insulated conductors or cables characterised by their form
- H01B7/0045—Cable-harnesses
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B7/00—Insulated conductors or cables characterised by their form
- H01B7/08—Flat or ribbon cables
- H01B7/0861—Flat or ribbon cables comprising one or more screens
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R31/00—Coupling parts supported only by co-operation with counterpart
- H01R31/06—Intermediate parts for linking two coupling parts, e.g. adapter
Abstract
The application relates to the field of satellite part assembly, in particular to a satellite integrated cable structure which comprises a layered cable assembly and a satellite structure plate, wherein the layered cable assembly comprises a plurality of cables which are adjacently arranged side by side; a cable accommodating through cavity is arranged in a plate of the satellite structure plate, a part of the layered cable assembly is arranged in the cable accommodating through cavity, and two ends of the layered cable assembly extend out of the cable accommodating through cavity and are respectively and electrically connected with the electric connector; the satellite integrated cable structure in this application links together stratiform cable subassembly and satellite structure board, has realized that the cable integrates, has effectively improved the installation effectiveness, has reduced the cost of labor. The cable is arranged in the cable accommodating through cavity, so that the utilization rate of the internal space of the satellite is improved.
Description
Technical Field
The application relates to the field of satellite part assembly, in particular to a satellite integrated cable structure and a satellite.
Background
In a satellite, the overall satellite circuitry is primarily responsible for the following tasks, one of which is to transmit electrical signal data of each subsystem of the satellite to each device via a cable, the electrical signals specifically including: power supply signals, RS422 signals, CAN signals, remote measuring signals, remote control signals and the like; the dual-purpose satellite system is used for realizing signal connection between the satellite and the carrier rocket; thirdly, the ground test cable is used for realizing the effective connection between the ground equipment and the satellite equipment, thereby completing the comprehensive test of the whole satellite and realizing the power supply of the ground space pseudomorphic array to the satellite; and the fourth can provide a safety test and a detonation channel for implementing the initiating explosive device.
As such, cables are important in the overall circuitry of the satellite. In the prior art, the cables in the general circuit system of the satellite are mainly conventional aerospace special cables and electric connectors, and the manufacturing process is complex and requires more process requirements. When the cable is installed on the star body, auxiliary tools such as a clamp and the like are often required to be manually fixed, so that the layout of the cable is rationalized.
Because the existing satellite cable for batch production has low installation efficiency, the installation of the cable depends on manual operation, operators are difficult to ensure the consistency of the installation process, and the operable space of the traditional small satellite is small, so that the installation efficiency is low, and the installation state is difficult to keep consistent, therefore, an improved satellite cable is needed to be provided, so that the problems are solved, and the installation efficiency and the space utilization rate are improved.
Disclosure of Invention
To the above-mentioned problem of prior art, the aim at of this application provides a satellite integrated cable structure links together stratiform cable subassembly and satellite structure board, has realized that the cable integrates for the installation of cable. The space for installing the cable routing is released, and the utilization rate of the internal space of the satellite is increased.
In order to solve the above problems, the present application provides a satellite integrated cable structure, including a layered cable assembly and a satellite structural plate, where the layered cable assembly includes a plurality of cables, and the plurality of cables are adjacently arranged side by side;
the satellite structure plate is characterized in that a cable holding through cavity is formed in the plate of the satellite structure plate, part of the layered cable assembly is arranged in the cable holding through cavity, and two ends of the layered cable assembly extend out of the cable holding through cavity and are respectively and electrically connected with the electric connector.
Preferably, the cable comprises a flat shaped cable.
Preferably, the layered cable assembly comprises a through-flow layer and a cable shielding layer, the cable shielding layer is sleeved outside the through-flow layer, and the cable shielding layer can shield electronic signals.
In particular, the flow-through layer comprises the plurality of cables.
Preferably, the cable shield layer can be stretched under an external force to be elastically deformed.
Preferably, the material of the cable shielding layer comprises silver-plated oxygen-free copper wires.
Specifically, after the layered cable assembly is electrically connected to the electrical connector, both ends of the cable shielding layer are connected to a ground wire, either end of the cable shielding layer is connected to the ground wire, or both ends of the cable shielding layer are not connected to the ground wire.
Preferably, the satellite structural panel comprises a structural panel bottom plate and a structural panel cover, and the structural panel bottom plate and the structural panel cover are closed to form the cable accommodating cavity.
Preferably, the layered cable assembly further comprises a fixing and mounting edge, the fixing and mounting edge is connected with the cable shielding layer, and the fixing and mounting edge is connected to the structural bottom plate through the fixing pieces.
On the other hand, this application still provides a satellite, the satellite includes the satellite of this application and integrates the cable structure.
Because above-mentioned technical scheme, this application a satellite integrated cable structure have following beneficial effect:
1. the application a satellite integrated cable structure link together stratiform cable subassembly and satellite structure board, realized that the cable integrates, effectively improved the installation effectiveness, reduced the cost of labor. The cable is arranged in the cable accommodating through cavity, so that the utilization rate of the internal space of the satellite is improved.
2. The application a satellite integrated cable structure adopt many cables adjacent setting side by side for stratiform cable subassembly evenly distributed is on the satellite structure board, the barycenter of satellite structure board more is close its central point to put, is favorable to the adjustment to the satellite barycenter.
3. A satellite integrated cable structure, the through-flow layer outside is equipped with the cable shield layer, can reduce the through-flow layer to external environment and through-flow layer external environment to the space radiation of self, the cable shield layer has played the guard action to the through-flow layer simultaneously, has avoided the injury of through-flow layer external environment to the through-flow layer.
Drawings
In order to more clearly illustrate the technical solution of the present application, the drawings used in the description of the embodiment or the prior art will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the application, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a side view of a satellite integrated cable structure according to an embodiment of the present disclosure;
fig. 2 is a top view of a satellite integrated cable structure according to an embodiment of the present disclosure.
The satellite communication system comprises a layered cable assembly, a flow layer, a cable shielding layer, a fixed mounting edge, a second fixing groove, a 2-satellite structural plate, a 3-electric connector and a 4-satellite single machine, wherein the layered cable assembly is 1, the flow layer is 11, the cable shielding layer is 12, the fixed mounting edge is 131, the second fixing groove is 131, the satellite structural plate is 2, and the single machine is 4-satellite single machine.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic may be included in at least one implementation of the present application. In the description of the present application, it is to be understood that the terms "upper", "lower", "left", "right", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. Moreover, the terms "first," "second," and the like are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or described herein.
Example one
With reference to fig. 1-2, an embodiment of the present application provides a satellite integrated cable structure, including a layered cable assembly 1 and a satellite structural plate 2, where the layered cable assembly 1 includes a plurality of cables, and the plurality of cables are adjacently arranged side by side; the inboard cable holding that is equipped with of satellite structure board 2 leads to the chamber, and partial stratiform cable subassembly 1 sets up in the intracavity is led to the cable holding, and the both ends of stratiform cable subassembly 1 are stretched out behind the chamber is led to the cable holding and are connected with electric connector 3 electricity respectively.
In the embodiment of the application, a part assembly structure is formed by connecting the layered cable assembly 1 and the satellite structure plate 2 together, so as to realize cable integration, because the satellite star frame can be spliced by the plurality of satellite structure plates 2, when the layered cable assembly 1 and the satellite structure plate 2 are integrated, the installation of the satellite star frame and a cable can be completed by splicing the plurality of satellite structure plates 2, the installation of the layered cable assembly 1 through a satellite small window is avoided, further, the installation speed of a satellite is improved, and the labor and the time cost are saved.
Through installing most stratiform cable subassembly 1 in satellite structure board 2 to make stratiform cable subassembly 1 can walk the line in satellite structure board 2 and arrange, need not to occupy a large amount of spaces, and then with the space release of walking the line of cable, improved the utilization ratio of satellite inner space.
Through adopting many cables adjacent setting side by side, when stratiform cable subassembly 1 evenly distributed is on satellite structure board 2, satellite structure board 2's barycenter more is close satellite structure board 2's central point to put, is favorable to the adjustment to satellite barycenter.
The electrical connector 3 in the embodiment of the present application is used for electrical connection with a consumer inside a satellite.
In one embodiment, as shown in fig. 2, the layered cable assembly 1 includes a flow-through layer 11 and a cable shielding layer 12, the cable shielding layer 12 is disposed outside the flow-through layer 11, and the cable shielding layer 12 can shield electronic signals.
In this application embodiment, the electric current in the satellite passes through each mechanism in the circulation layer 11 transmission to the satellite, and cable shielding layer 12 can shield electronic signal, locates behind circulation layer 11 when cable shielding layer 12 cover, has reduced circulation layer 11 to external environment and circulation layer external environment to the space radiation of circulation layer self, and cable shielding layer 12 has played the guard action to circulation layer 11 simultaneously, has avoided circulation layer external environment to cause direct injury to circulation layer 11.
In one embodiment, the flow-through layer is a cable assembly comprised of a plurality of cables.
In particular embodiments, the cable may be a flat shaped cable.
In one embodiment, the cable shield 12 can be stretched under an external force to elastically deform.
That is to say, the cable shielding layer 12 has a certain elasticity, and good elasticity can wrap the current layer 11 more compactly, so that the cost can be saved while the shielding of electronic signals is realized.
In another embodiment, the cable shielding layer 12 has a certain wear resistance, and the good wear resistance can ensure that the cable shielding layer 12 is not damaged due to friction with the outside, thereby reducing the occurrence of the situation that the ventilation layer 11 is exposed in the cable accommodating through cavity.
In a specific embodiment, the material of the cable shielding layer 12 may be silver-plated oxygen-free copper wire.
Because the silver-plated oxygen-free copper wire is made of a lighter material, when the cable shielding layer 12 is formed by weaving the silver-plated oxygen-free copper wire, the weight of the layered cable assembly 1 is reduced, and further the fuel cost required by satellite launching is saved.
In one embodiment, when the layered cable assembly 1 and the electrical connector 3 are electrically connected, both ends of the cable shield 12 are connected to the ground, either end of the cable shield 12 is connected to the ground, or both ends of the cable shield 12 are not connected to the ground.
In a specific embodiment, after the layered cable assembly 1 and the electrical connector 3 are electrically connected, the following connection method can be selected between the cable shielding layer and the electrical wire:
both ends of the cable shielding layer 12 are connected with the ground wire, so that the layered cable assembly 1 realizes double-point grounding connection; either end of the cable shield layer 12 is connected with the ground wire, so that the layered cable assembly 1 realizes single-point grounding connection; both ends of the cable shielding layer 12 are not connected with the ground wire, so that the layered cable assembly 1 realizes floating connection.
Because the laminated cable assembly 1 is arranged in the cable accommodating through cavity, the grounding treatment of the laminated cable assembly 1 is already realized, and therefore, the floating connection can be realized without any ground wire, so that the weight of the satellite and the cost of the satellite are reduced. When the layered cable assembly 1 performs single-point ground connection or double-point ground connection, the reliability of the satellite operation can be increased. Thus, the specific connection mode between the layered cable assembly 1 and the ground wire can be set differently according to different requirements of the satellite in manufacturing.
In a particular embodiment, the ground wire is soldered to one end of the cable shield 12.
In one embodiment, the satellite structural panel 2 includes a structural panel base panel and a structural panel cover that are closed to form a cable receiving cavity.
In the specific implementation mode, be equipped with the apron through-hole on the structural slab closing cap, be equipped with on the structural slab bottom plate with apron through-hole assorted first fixed slot, lock screw wear to establish behind the apron through-hole with first fixed slot cooperation for structural slab closing cap and structural slab bottom plate fixed connection, and form cable holding chamber after structural slab bottom plate and structural slab closing cap are closed.
In the embodiment of the application, through setting up to dismantling the connection between structure board bottom plate and the structure board closing cap, when the suspected damage appears in stratiform cable subassembly 1, can separate structure board closing cap and structure board bottom plate through extracting tool, and then inspect or change stratiform cable subassembly 1, the damage of having avoided stratiform cable subassembly 1 leads to scrapping of satellite integrated cable structure. Before the structural slab bottom plate and the structural slab closing cap are closed, the layered cable assembly 1 can be randomly arranged on the structural slab bottom plate to be wired, after the structural slab bottom plate and the structural slab closing cap are closed, the layered cable assembly 1 can be changed between the wiring through detaching the structural slab bottom plate and the structural slab closing cap, and the replacement cost of the satellite integrated cable structure is reduced.
In one embodiment, the satellite integrated cable structure further includes a plurality of fixing members, the layered cable assembly 1 further includes a fixing and mounting edge 13, the fixing and mounting edge 13 is connected to the cable shielding layer 12, and the fixing and mounting edge 13 is connected to the structural bottom plate through the plurality of fixing members.
In a specific embodiment, a fixed mounting hole is formed in the fixed mounting edge 13, a second fixing groove 131 matched with the fixed mounting hole is formed in the structural plate bottom plate, and the fixing member penetrates through the fixed mounting hole to be matched with the second fixing groove 131, so that the fixed mounting edge 13 is installed on the structural plate bottom plate.
Through the satellite integrated cable structure that this application embodiment provided has following beneficial effect:
1. the application a satellite integrated cable structure link together stratiform cable subassembly and satellite structure board, realized that the cable integrates, effectively improved the installation effectiveness, reduced the cost of labor. The cable is arranged in the cable accommodating through cavity, so that the utilization rate of the internal space of the satellite is improved.
2. The application a satellite integrated cable structure adopt many cables adjacent setting side by side for stratiform cable subassembly evenly distributed is on the satellite structure board, the barycenter of satellite structure board more is close its central point to put, is favorable to the adjustment to the satellite barycenter.
3. A satellite integrated cable structure, the through-flow layer outside is equipped with the cable shield layer, can reduce the through-flow layer to external environment and through-flow layer external environment to the space radiation of self, the cable shield layer has played the guard action to the through-flow layer simultaneously, has avoided the injury of through-flow layer external environment to the through-flow layer.
Example two
With reference to fig. 1-2, an embodiment of the present application provides a satellite integrated cable structure, including a layered cable assembly 1 and a satellite structural plate 2, where the layered cable assembly 1 includes a plurality of cables, and the plurality of cables are adjacently arranged side by side; the inboard cable holding that is equipped with of satellite structure board 2 leads to the chamber, and partial stratiform cable subassembly 1 sets up in the intracavity is led to the cable holding, and the both ends of stratiform cable subassembly 1 are stretched out behind the chamber is led to the cable holding and are connected with electric connector 3 electricity respectively.
In the embodiment of the application, a part assembly structure is formed by connecting the layered cable assembly 1 and the satellite structure plate 2 together, so as to realize cable integration, because the satellite star frame can be spliced by the plurality of satellite structure plates 2, when the layered cable assembly 1 and the satellite structure plate 2 are integrated, the installation of the satellite star frame and a cable can be completed by splicing the plurality of satellite structure plates 2, the installation of the layered cable assembly 1 through a satellite small window is avoided, further, the installation speed of a satellite is improved, and the labor and the time cost are saved.
Through installing most stratiform cable subassembly 1 in satellite structure board 2 to make stratiform cable subassembly 1 can walk the line in satellite structure board 2 and arrange, need not to occupy a large amount of spaces, and then can release the space of walking the line of cable, improved satellite inner space's utilization ratio.
Through adopting many cables adjacent setting side by side, when stratiform cable subassembly 1 evenly distributed in satellite structural slab 2, the central point that satellite structural slab 2's barycenter more is close satellite structural slab 2 puts, is favorable to the adjustment to satellite barycenter.
In the specific embodiment, the electrical connector 3 is used for connecting with the on-board unit 4.
In particular embodiments, the satellite structural panel 2 may be a satellite honeycomb panel.
When the layered cable assembly 1 is integrated in the satellite honeycomb structure plate, the honeycomb structure has certain anti-interference capability, so that external signals can be prevented from interfering with the layered cable assembly 1 in the honeycomb structure.
In particular embodiments, the cable may be a flat shaped cable.
In one embodiment, the flat cable may be made of a flat copper foil, which is lighter than other cables, thereby reducing the weight of the satellite. For example: the cable in the embodiment of the application is only 1.68 g per meter, and compared with the cable which is made in China and is about 4.17 g per meter and the cable which is 3.95 g per meter, the weight of the cable is greatly reduced.
In one embodiment, the layered cable assembly 1 includes a flow-through layer 11 and a cable shielding layer 12, the cable shielding layer 12 is disposed outside the flow-through layer 11, and the cable shielding layer 12 is capable of shielding electronic signals.
In this application embodiment, the electric current in the satellite passes through each mechanism in the circulation layer 11 transmission to the satellite, and cable shielding layer 12 can shield electronic signal, locates behind circulation layer 11 when cable shielding layer 12 cover, has reduced circulation layer 11 to external environment and circulation layer external environment to the space radiation of circulation layer self, and cable shielding layer 12 has played the guard action to circulation layer 11 simultaneously, has avoided circulation layer external environment to cause direct injury to circulation layer 11.
The through-flow layer 11 and the cable shielding layer 12 form the layered cable assembly 1, and different layered cable assemblies 1 can be overlapped with each other without influencing the mutual interference of the through-flow layers 11 in the layered cable assemblies 1.
In one embodiment, the through-flow layer 11 is a cable assembly consisting of a plurality of cables.
In one embodiment, the cable shield 12 can be stretched under an external force to elastically deform.
That is to say, the cable shielding layer 12 has a certain elasticity, and good elasticity can wrap the current layer 11 more compactly, so that the cost can be saved while the shielding of electronic signals is realized.
In another embodiment, the cable shielding layer 12 has a certain wear resistance, and the good wear resistance can ensure that the cable shielding layer 12 is not damaged due to friction with the outside, thereby reducing the occurrence of the situation that the ventilation layer 11 is exposed in the cable accommodating through cavity.
In a specific embodiment, the material of the cable shielding layer 12 may be silver-plated oxygen-free copper wire.
Because the silver-plated oxygen-free copper wire is made of a lighter material, when the cable shielding layer 12 is formed by weaving the silver-plated oxygen-free copper wire, the weight of the layered cable assembly 1 is reduced, and further the fuel cost required by satellite launching is saved.
In one embodiment, when the layered cable assembly 1 and the electrical connector 3 are electrically connected, both ends of the cable shield 12 are connected to the ground, either end of the cable shield 12 is connected to the ground, or both ends of the cable shield 12 are not connected to the ground.
In a specific embodiment, after the layered cable assembly 1 and the electrical connector 3 are electrically connected, the following may be selected between the cable shield and the electrical wire:
both ends of the cable shielding layer 12 are connected with the ground wire, so that the layered cable assembly 1 realizes double-point grounding connection; either end of the cable shield layer 12 is connected with the ground wire, so that the layered cable assembly 1 realizes single-point grounding connection; both ends of the cable shielding layer 12 are not connected with the ground wire, so that the layered cable assembly 1 realizes floating connection.
Because the laminated cable assembly 1 is arranged in the cable accommodating through cavity, the grounding treatment of the laminated cable assembly 1 is already realized, and therefore, the floating connection can be realized without any ground wire, so that the weight of the satellite and the cost of the satellite are reduced. When the layered cable assembly 1 performs single-point ground connection or double-point ground connection, the reliability of the satellite operation can be increased. The specific connection between the laminated cable assembly 1 and the ground can thus be arranged differently according to the different requirements of the satellite in its manufacture.
In a particular embodiment, the ground wire is soldered to one end of the cable shield 12.
In one embodiment, the satellite structural panel 2 includes a structural panel base panel and a structural panel cover that are closed to form a cable receiving cavity.
In the specific implementation mode, be equipped with the apron through-hole on the structural slab closing cap, be equipped with on the structural slab bottom plate with apron through-hole assorted first fixed slot, lock screw wear to establish behind the apron through-hole with first fixed slot cooperation for structural slab closing cap and structural slab bottom plate fixed connection, and form cable holding chamber after structural slab bottom plate and structural slab closing cap are closed.
In the embodiment of the application, through setting up to dismantling the connection between structural slab bottom plate and the structural slab closing cap, when the suspected damage of stratiform cable subassembly 1 appears, can separate structural slab closing cap and structural slab bottom plate through extracting tool, and then inspect or change stratiform cable subassembly 1, the damage of having avoided stratiform cable subassembly 1 leads to scrapping of satellite integrated cable structure. Before the structural slab bottom plate and the structural slab closing cap are closed, the layered cable assembly 1 can be randomly arranged on the structural slab bottom plate to be wired, after the structural slab bottom plate and the structural slab closing cap are closed, the layered cable assembly 1 can be wired in order to change the wiring between the layered cable assembly 1 by detaching the structural slab bottom plate and the structural slab closing cap, and the replacement cost of the satellite integrated cable structure is reduced.
In one embodiment, the satellite integrated cable structure further includes a plurality of fixing members, the layered cable assembly 1 further includes a fixing and mounting edge 13, the fixing and mounting edge 13 is connected to the cable shielding layer 12, and the fixing and mounting edge 13 is connected to the structural bottom plate through the plurality of fixing members.
In a specific embodiment, the fixed mounting edge 13 is provided with a fixed mounting hole, the structural plate bottom plate is provided with a second fixing groove 131 matched with the fixed mounting hole, and the fixing member penetrates through the fixed mounting hole to be matched with the second fixing groove 131, so that the fixed mounting edge 13 is installed on the structural plate bottom plate.
The cable shielding layer 12 wraps the through-flow layer 11 in a flat shape, so that the layered cable assembly 1 has two wider sides, the fixed mounting edges 13 are arranged on the two wider sides and connected with the structural bottom plate, and the fixed mounting edges 13 are connected with the structural bottom plate, so that the layered cable assembly 1 is connected with the satellite structural plate 2.
The beneficial effects of the satellite integrated cable structure in the embodiment of the present application are substantially the same as those in the first embodiment, and are not described herein in detail.
EXAMPLE III
In addition, the embodiment of the present application further provides a satellite, where the satellite includes the satellite integrated cable structure in the embodiment of the present application, and beneficial effects of the satellite provided by the embodiment are substantially the same as those of the first embodiment, and are not described herein in any more detail.
The foregoing description has disclosed fully embodiments of the present application. It should be noted that those skilled in the art can make modifications to the embodiments of the present application without departing from the scope of the claims of the present application. Accordingly, the scope of the claims of the present application is not to be limited to the particular embodiments described above.
Claims (10)
1. A satellite integrated cable structure is characterized by comprising a layered cable component (1) and a satellite structure plate (2),
the layered cable assembly (1) comprises a plurality of cables arranged side by side adjacently;
the satellite structure plate is characterized in that a cable holding through cavity is formed in the plate of the satellite structure plate (2), part of the layered cable assembly (1) is arranged in the cable holding through cavity, and two ends of the layered cable assembly (1) extend out of the cable holding through cavity and then are respectively electrically connected with the electric connector (3).
2. The satellite integrated cable structure of claim 1, wherein the cable comprises a flat shaped cable.
3. The satellite integrated cable structure according to claim 1, wherein the layered cable assembly (1) comprises a current flowing layer (11) and a cable shielding layer (12), the cable shielding layer (12) is sleeved outside the current flowing layer (11), and the cable shielding layer (12) can shield electronic signals.
4. A satellite integrated cable structure according to claim 3, wherein said flow layer (11) comprises said plurality of cables.
5. A satellite integrated cable structure according to claim 3, wherein the cable shield (12) is capable of being stretched under an external force to be elastically deformed.
6. The satellite integrated cable structure according to claim 5, wherein the material of the cable shielding layer (12) comprises silver-plated oxygen-free copper wires.
7. The satellite integrated cable structure according to claim 3, wherein after the layered cable assembly (1) and the electrical connector (3) are electrically connected, both ends of the cable shielding layer (12) are connected to the ground, either end of the cable shielding layer (12) is connected to the ground, or both ends of the cable shielding layer (12) are not connected to the ground.
8. A satellite integrated cable structure according to claim 3, wherein the satellite structural plate (2) comprises a structural plate bottom plate and a structural plate cover, and the structural plate bottom plate and the structural plate cover are closed to form the cable accommodating cavity.
9. The satellite integrated cable structure according to claim 8, further comprising a plurality of fixing members, wherein the layered cable assembly (1) further comprises a fixing and mounting edge (13), the fixing and mounting edge (13) is connected to the cable shielding layer (12), and the fixing and mounting edge (13) is connected to the structural bottom plate through the plurality of fixing members.
10. A satellite comprising the satellite integrated cable structure of any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111348066.6A CN114255913A (en) | 2021-11-15 | 2021-11-15 | Satellite integrated cable structure and satellite |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111348066.6A CN114255913A (en) | 2021-11-15 | 2021-11-15 | Satellite integrated cable structure and satellite |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1111400A (en) * | 1997-06-24 | 1999-01-19 | Nec Eng Ltd | Structural panel for on-artificial-satellite electronic equipment |
| US20070221786A1 (en) * | 2006-03-22 | 2007-09-27 | Mitsubishi Electric Corporation | Artificial satellite equipment panel |
| US20100130054A1 (en) * | 2008-06-04 | 2010-05-27 | Williams-Pyro, Inc. | Flexible high speed micro-cable |
| CN108986971A (en) * | 2018-07-02 | 2018-12-11 | 上海微小卫星工程中心 | A kind of cable shield device |
| CN217049076U (en) * | 2021-11-15 | 2022-07-26 | 浙江时空道宇科技有限公司 | Satellite integrated cable structure and satellite |
-
2021
- 2021-11-15 CN CN202111348066.6A patent/CN114255913A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1111400A (en) * | 1997-06-24 | 1999-01-19 | Nec Eng Ltd | Structural panel for on-artificial-satellite electronic equipment |
| US20070221786A1 (en) * | 2006-03-22 | 2007-09-27 | Mitsubishi Electric Corporation | Artificial satellite equipment panel |
| US20100130054A1 (en) * | 2008-06-04 | 2010-05-27 | Williams-Pyro, Inc. | Flexible high speed micro-cable |
| CN108986971A (en) * | 2018-07-02 | 2018-12-11 | 上海微小卫星工程中心 | A kind of cable shield device |
| CN217049076U (en) * | 2021-11-15 | 2022-07-26 | 浙江时空道宇科技有限公司 | Satellite integrated cable structure and satellite |
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