An integrated cable space line connector for spacecraft

Abstract

The present invention discloses an integrated cable space line connector for use in a spacecraft, including a stator end bearing part, a rotor end bearing part, and a conductive cable part. The stator end bearing part is installed and connected to a fixed part of the spacecraft to provide fixation and support for the stator cable. The rotor end bearing part is installed and connected to a rotating part of the spacecraft, and is arranged in the stator end bearing part in a coaxial and two-end rotation support manner, including a plurality of columnar petals arranged along the circumferential direction, forming a central hole area to clamp and support the rotor cable bundle. The conductive cable part is a spiral curve-shaped integrated wiring cable, which has a rebound characteristic and is insulated, and is arranged in an annular space area between the stator end bearing part and the rotor end bearing part. The spiral curve and the rebound characteristic thereof realize the curling and resetting movement of a limited rotation angle, thereby ensuring the continuous and reliable transmission of multi-channel power and / or signal current between the rotating part and the fixed part.

Description

Technical Field

[0001] The present invention belongs to the field of spacecraft electrical transmission technology, and relates to the transmission of power current and / or signal current between rotating and fixed parts of a spacecraft, such as between a solar sail panel and a spacecraft body. Specifically, the present invention is an integrated cable space line connector used in spacecraft, which realizes continuous and reliable transmission of multi-channel power and signals by adopting a spacecraft integrated wiring cable in a spiral curve shape. Background Art

[0002] Line connectors are key components of the spacecraft's solar panel drive, antenna drive, radar servo transmission, laser communication components and other motion mechanisms. Their main function is to transmit the acquired electrical signals to the spacecraft body through the line connector when these motion mechanisms are working, thereby ensuring the normal operation of the system. Line connectors are components that use the relative motion between conductive parts to transfer energy or electrical signals. They are widely used in electromechanical systems that require continuous rotation while also transmitting current from a fixed position to a rotating position.

[0003] At present, space line connectors are mainly based on conductive rings, which usually include a power ring for transmitting power current and a signal ring for transmitting signal current. However, existing conductive ring line connectors have problems such as large moment of inertia and high contact resistance, resulting in low energy transmission efficiency. Secondly, the lack of complete isolation between the ring brushes makes it easy for the power ring and the signal ring to interfere with each other, especially when high-frequency signals are transmitted, this interference will be more obvious. In addition, the conductive ring is prone to vacuum discharge problems in a vacuum environment, affecting the stability and reliability of the line connector.

[0004] On the other hand, in order to absorb as much solar energy as possible, spacecraft usually need to be equipped with line connectors with limited angle rotation. Most of the cable assembly line connectors currently used, such as Chinese invention patent CN202410317826.4, adopt the method of external line swinging of the mechanism. The rotation angle range of this design is usually small, most of which are within the range of ±90°. In addition, in the case of multi-channel communication needs, the loose cables with external line swinging are prone to problems such as entanglement, and the movement state of the cables cannot be effectively controlled. If multiple cables are tied into a harness for use, although the entanglement problem can be solved to a certain extent, the hardness of the harness is relatively large and requires a larger moment of inertia. More importantly, the cable will be subjected to tensile force during rotation, and it is easy to have faults such as broken wires after working for a long time, thereby reducing the service life of the line connector.

[0005] In addition to cable-type line connectors, line connectors with structures such as conductive slip rings and roller rings also have certain applications, but their manufacturing and assembly are difficult and require high-precision processing and assembly processes. At the same time, these devices are prone to introducing redundant objects during operation, which may cause faults such as short circuits and unstable signals. In addition, line connectors such as conductive slip rings and roller rings have large signal attenuation during high-frequency signal transmission, affecting the quality and stability of signal transmission. At the same time, when these devices operate in harsh aerospace environments, the vibration and temperature changes they are subjected to will also increase their aging and failure risks.

[0006] In summary, existing line connectors have many problems in spacecraft applications, including large moment of inertia, high contact resistance, ring brush interference, vacuum discharge, small rotation angle range, cable entanglement, high wire harness hardness, difficulty in manufacturing and assembly, signal attenuation and interference, etc. These problems seriously affect the performance and reliability of line connectors and limit their application in spacecraft. Therefore, in order to meet the demand of spacecraft for efficient and reliable line connectors, developing a high-performance and high-reliability line connector is a technical problem that needs to be solved urgently. Summary of the invention

[0007] (I) Purpose of the invention

[0008] In view of the defects and shortcomings of existing line connectors in spacecraft applications, such as large torque, large contact resistance, mutual interference between power ring and signal ring, vacuum discharge, small rotation angle range, cable entanglement, high wire harness hardness, great difficulty in manufacturing and assembly, signal attenuation and interference, and in order to solve at least one of the above-mentioned and other technical problems in the prior art, the present invention aims to provide an integrated cable space line connector mainly used in spacecraft, wherein the middle conductive cable part adopts an integrated wiring cable, which is assembled in the interior of the line connector in a spiral curve shape after molding, and is accompanied by the reciprocating motion of the rotor end bearing part with a limited rotation angle of curling and resetting, so as to realize continuous and reliable transmission of multiple power currents and / or signal currents between the rotating and fixed parts of the spacecraft.

[0009] (II) Technical solution

[0010] In order to achieve the purpose of the invention and solve the technical problems, the present invention adopts the following technical solutions:

[0011] An integrated cable space line connector for use in a spacecraft, used to transmit power current and / or signal current between a rotating part and a fixed part of a spacecraft, such as between a solar sail panel and a spacecraft body, comprises a stator end bearing part, a rotor end bearing part and a conductive cable part, wherein:

[0012] The stator end bearing part is installed and connected to the fixed part of the spacecraft and provides fixation and support for the stator cable harness, wherein the hollow interior thereof is formed into a cylindrical space extending along the central axis;

[0013] The rotor end bearing part is installed and connected to the rotating part of the spacecraft, and is disposed in the cylindrical space of the stator end bearing part in a coaxial manner and supported for rotation at both ends, and includes a plurality of columnar lobed bodies that are discretely arranged along the circumference and extend along the central axis, and a central hole area extending along the axial direction is formed between the inner side walls of each of the columnar lobed bodies around the central axis, and the central hole area is used to clamp and support the rotor cable bundle, and an annular space area is formed between the outer side walls of each of the columnar lobed bodies and the inner side walls of the stator end bearing part;

[0014] The conductive cable portion is integrally processed to form a spiral curved integrated wiring cable with rebound characteristics and insulation treatment, and is spatially distributed in the annular space area between the stator end bearing portion and the rotor end bearing portion. The first end of the spiral curved integrated wiring cable is fixedly arranged on the columnar petal body of the rotor end bearing portion in an axially flat manner, and is bent into the center hole area and then divided into strands of loose cables that extend axially to the external space to form a rotor cable bundle. The second end is fixedly arranged on the wall surface of the stator end bearing portion in an axially flat manner, and extends radially outward to the external space to form a stator cable bundle, so that the conductive cable portion, through its own spiral curve and rebound characteristics, accompanies the rotor end bearing portion to perform a limited rotation angle of curling and resetting movement during the rotation process, thereby realizing continuous and reliable transmission of multi-channel power and / or signal current between the rotating part and the fixed part.

[0015] (III) Technical Effect

[0016] Compared with the prior art, the integrated cable space line connector applied to a spacecraft of the present invention has the following beneficial and significant technical effects:

[0017] (1) Compared with the existing traditional line connectors, the present invention does not use brushes, metal conductors and a large number of insulating structural parts, so the size and weight of the cable assembly required to transmit the same current are greatly reduced, which is more suitable for the compact and lightweight design requirements of spacecraft. At the same time, the present invention avoids the use of friction components, eliminates the wear and debris problems caused by friction, and the frictionless transmission also ensures the long-term stability of the electrical transmission performance, and the resistance torque will not increase over time, thereby ensuring the long-term reliability and stability of the system. In addition, the cable-type line connector of the present invention has a simple structure, reduces the design and processing of parts, reduces manufacturing costs, and shortens the development cycle.

[0018] (2) The cable assembly of the present invention uses an integrated wiring cable. When performing multi-channel electrical transmission, the cable is wrapped in its own insulation layer. The existence of the insulation layer effectively isolates the interference between the transmission channels, and the problem of multi-channel signal interference is greatly reduced, thereby ensuring the stability and reliability of signal transmission. In addition, the cable assembly is an integrated wiring cable design without intermediate switching components, with stable resistance, reducing potential connection failure points and reducing the difficulty of operation and maintenance. At the same time, the integrated wiring cable itself has a uniformly distributed resistance and uniform heat generation, which simplifies the thermal management design, reduces the heat dissipation burden of the system, and improves the overall efficiency and reliability.

[0019] (3) The line connector of the present invention cannot rotate continuously in one direction, but can meet the requirements of a reciprocating motion mechanism within a limited rotation angle. The rotation angle is greater than 0°, and the maximum rotation angle is limited but not limited to 360°, 540° or 720°. This flexible design adapts to different task requirements and provides a wider range of application possibilities. At the same time, the cable arrangement can be customized according to the number of cables used, current size, spatial layout, insulation material, etc., with greater flexibility in terms of the number of cables per row, wire diameter, total length, and length of scattered wires at both ends.

[0020] (4) The wire outlet at the bearing part of the rotor end of the present invention can be designed as a single-layer wire arrangement with two wire outlets, or it can be designed as multiple wire outlets and multiple layers of wire arrangement superposition according to actual needs, thereby enhancing the expansion capability of the system and being able to adapt to more complex application scenarios. At the same time, in order to achieve effective utilization of the internal space, the present invention designs the wire crimping cover component as a resettable component structure, or designs the wire crimping cover component as an integrated structure when space permits. In addition, more importantly, the curved surface feature design in the integrated structure of the wire crimping cover component and the resettable limit plate design in the component structure can prevent the bending radius of the wire arrangement from being smaller than the curvature radius of the wire arrangement, thereby effectively avoiding damage and wear of the wire arrangement cable due to excessive bending, ensuring that the conductive cable part maintains a smooth movement path during rotation, and extending the service life of the cable. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a schematic diagram of an integrated cable space line connector applied to a spacecraft of the present invention;

[0023] Figure 2It is a schematic diagram of the internal structure of the integrated cable space line connector of the present invention;

[0024] Figure 3 It is a schematic structural diagram of an integrated wiring cable of a conductive cable portion in an embodiment of the present invention;

[0025] Figure 4 It is a schematic diagram of a component structure of a wire crimping cover component in an embodiment of the present invention;

[0026] Description of reference numerals:

[0027] Stator end bearing part 1, rotor end bearing part 2, conductive cable part 3, stator cable bundle 4, rotor cable bundle 5, columnar petal body 6, strip wire groove 7, wire pressing plate 8, wire installation groove 9, wire pressing cover part 10, cover plate body 11, limit plate 12, return spring 13. DETAILED DESCRIPTION

[0028] In order to better understand the present invention, the content of the present invention is further explained in conjunction with the embodiments below. In the accompanying drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be understood as limitations on the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present invention. The structure and technical solution of the present invention are further described in detail below in conjunction with the accompanying drawings, and an embodiment of the present invention is given.

[0029] The present invention aims to provide an integrated cable space line connector mainly used in spacecraft, wherein the intermediate conductive cable part adopts an integrated cable arrangement, which is assembled in a spiral curve shape inside the line connector after molding, and the rotor end bearing part performs a limited rotation angle retraction and reset reciprocating motion, thereby realizing continuous and reliable transmission of multiple power currents and / or signal currents between the rotating and fixed parts of the spacecraft. As a specific example, Figure 1 , 2 As shown, the integrated cable space line connector applied to a spacecraft of the present invention is used to transmit power current and / or signal current between a rotating part and a fixed part of a spacecraft, such as between a solar sail panel and a spacecraft body, and includes a stator end bearing part 1, a rotor end bearing part 2 and a conductive cable part 3, wherein:

[0030] The stator end bearing part 1 is installed and connected to a fixed position of the spacecraft and provides fixation and support for the stator cable harness 4, wherein the hollow interior thereof is formed into a cylindrical space extending along the central axis.

[0031] The rotor end bearing part 2, such as Figure 2 As shown, it is installed and connected to the rotating part of the spacecraft, and is arranged in the cylindrical space of the stator end bearing part 1 in a coaxial and rotationally supported manner at both ends. It includes a plurality of columnar lobed bodies 6 discretely arranged along the circumference and extending along the axis. A central hole area extending along the axial direction is formed between the inner wall surfaces of each columnar lobed body 6 around the central axis. The central hole area is used to clamp and support the rotor cable bundle 5, and an annular space area is formed between the outer wall surface of each columnar lobed body 6 and the inner wall surface of the stator end bearing part 1.

[0032] Conductive cable part 3, such as Figure 2 , 3 As shown, the whole is processed to form a spiral curve integrated wiring cable with rebound characteristics and insulation treatment, and is spatially distributed in the annular space area between the stator end bearing part 1 and the rotor end bearing part 2. The first end of the spiral curve integrated wiring cable is fixedly arranged on the columnar petal body 6 of the rotor end bearing part 2 in an axially flat manner, and is bent into the center hole area and then divided into strands of loose cables, which extend axially to the external space to form a rotor cable bundle 5. The second end is fixedly arranged on the wall surface of the stator end bearing part 1 in an axially flat manner, and extends radially outward to the external space to form a stator cable bundle 4, so that the conductive cable part 3, through its own spiral curve and rebound characteristics, accompanies the rotor end bearing part 2 to perform a limited rotation angle of curling and resetting movement during the rotation process, thereby realizing continuous and reliable transmission of multi-channel power current and / or signal current between the rotating and fixed parts.

[0033] In some preferred embodiments of the present invention, the stator cable harness 4 extending to the external space has its end electrically connected to a fixed part of the spacecraft, and the structural form of the harness is selected as an integrated wiring cable or a plurality of strands of conductors in the form of scattered wires according to the application scenario and the spatial layout requirements, so as to meet the electrical transmission requirements under different mission conditions; the rotor cable harness extending to the external space has its end electrically connected to the rotating part of the spacecraft, and the structural form of the harness is a plurality of strands of conductors in the form of scattered wires, so as to adapt to the complex movement requirements of the spacecraft and ensure the continuity and reliability of signal and power transmission.

[0034] In addition, a strip-shaped wire groove 7 extending axially and communicating with the external space is provided on the cylindrical wall surface of the stator end bearing portion 1. Figure 2 As shown, the length of the strip wire groove 7 is not less than the wiring width of the conductive cable part 3. After the second end of the conductive cable part 3 radially passes through the corresponding strip wire groove 7, it first passes through a wire pressing plate 8 and is clamped and fixed on the outer wall surface of the stator end bearing part 1 in an axially flat manner with the help of fasteners, and then continues to extend to the external space to form a stator cable bundle 4.

[0035] Further preferably, the wire pressing plate 8 is made of high-strength insulating material, so as to provide the necessary electrical insulation while ensuring the stability of the conductive cable part 3. The fasteners can be selected in the form of bolts or snaps to facilitate installation and disassembly operations. In addition, in order to enhance the tensile strength of the conductive cable part 3 at its second end, a stress buffer gasket is provided on the outer wall surface of the wire pressing plate 8 and / or the stator end bearing part 1 to absorb the slight vibration and impact of the cable during operation, thereby extending the service life of the conductive cable part 3 and ensuring the stability and reliability of electrical transmission. At the same time, the side edges of the inner and outer walls of the strip wire groove 8 are processed to form a curved structure to reduce the wear and stress concentration at the strip wire groove 8 at the second end of the conductive cable part 3 during the curling and resetting movement.

[0036] In some preferred embodiments, according to the number of channels of power and / or signals to be transmitted by the line connector, the rotation angle, and the geometric shape and size of the annular space area between the stator end bearing part 1 and the rotor end bearing part 2, one or more groups of independent wiring cables are arranged in the annular space area, and each group of wiring cables is arranged according to the preset number of cable layers and spiral coils to ensure the stability and reliability of the power and / or signal transmission required for each channel, achieve the best performance of the conductive cable part 3 under different task conditions, and ensure that each group of wiring cables is uniformly stressed during the retraction and reset movement to avoid wear and stress concentration, thereby extending the service life of the wiring cables and ensuring their long-term reliability. Further preferably, for the wiring cable group for high power and / or signal current transmission, the number of cable layers is increased to improve its transmission capacity and anti-interference ability; for the wiring cable group for low power and / or signal current transmission, the number of cable layers is reduced to reduce the space occupation.

[0037] In addition, the spiral line pitch and number of turns of the wiring cable are determined based on the rotation angle range required by the line connector, the number of wiring cable groups, and the space requirements, and taking into account the mechanical stress and thermal stress that the conductive cable part 3 may be subjected to during the rotation process, so as to avoid cable wear and fatigue failure caused by excessive tightness or looseness, so as to ensure the best electrical transmission performance in a limited space.

[0038] Specifically, when a larger rotation angle range is required, the number of spiral coils is increased and the spacing is appropriately reduced to disperse stress and improve the flexibility and resilience of the cable, ensuring that the cable will not bend excessively at the maximum rotation angle; when space is limited and the rotation angle is small, the number of spiral coils is reduced and the spacing is increased to save space and materials; at the same time, when the number of cable groups is large, the spiral spacing needs to be appropriately increased to avoid interference between coils of different groups. Therefore, by comprehensively considering the above factors and rationally designing the spiral spacing and number of coils of the cable, the optimized performance of the line connector in different application scenarios can be achieved.

[0039] In some preferred embodiments, in the rotor end bearing portion 2, as Figure 2 As shown, the circumferential gap between two adjacent columnar petal bodies 6 forms a wire installation groove 9 at the first end of the conductive cable part, and the length of the wire installation groove 9 extending in the axial direction is not less than the wiring width of the conductive cable part 3. After the first end passes through a wire pressing cover component 10 and is clamped and fixed to the outer wall surface of a columnar petal body 6 in an axially flat manner with the help of a fastener, it passes through the corresponding wire installation groove 9 in the radial direction and bends into the central hole area, and then is divided into strands of scattered wires and extends axially to the external space to form a rotor cable bundle 5. Such a structural design enables the first end of the conductive cable part 3 to be effectively fixed and supported in a limited space, thereby ensuring the stable transmission of power and / or signal current.

[0040] In a further preferred embodiment, the outer wall surface of the columnar petal body 6 is processed to form a step portion that matches the shape and size of the wire pressing cover component 10 and has smooth transitions on each edge, such as Figure 2 As shown, after the wire pressing cover component 10 clamps the first end of the conductive cable part 3 and is fixedly arranged on the step part by means of fasteners, its outer wall surface is flush with the outer wall surface of the main part of the columnar lobed body 6. The structural design of the step portion on the columnar lobed body 6 not only ensures the stable installation of the conductive cable part 3 on the rotor end bearing part 2, but also ensures the flatness of the entire outer wall surface of the columnar lobed body 6 after the step portion structure is set, thereby reducing the mechanical interference and wear risk caused by the uneven surface to the conductive cable part 3 during the repeated retraction and resetting rotation process. Through this optimized design, it can be ensured that the conductive cable part 3 always maintains a good working state during the rotation process, thereby achieving efficient and stable current and signal transmission.

[0041] In a further preferred embodiment, the structure of the wire crimping cover component 10 can be designed as a plate-like component, and the wire outlet position away from the wire installation groove 9 is set as a curved surface feature, and the outer curvature radius of the wire crimping cover component 10 at this position is consistent with the minimum radius of the wire arrangement spiral line, and the inner curvature radius is greater than the limit curvature radius when the wire arrangement is bent. In order to achieve the maximum range of the wire arrangement rotation angle, during the rotation process, the wire arrangement cable of the conductive cable part 3 may bend at the wire outlet position. Such a structural design can prevent the bending radius of the wire arrangement from being less than the curvature radius of the wire arrangement, limit the minimum bending radius of the wire arrangement, thereby effectively avoiding damage and wear of the wire arrangement cable due to excessive bending, and ensure that during the rotation and resetting of the wire arrangement, the conductive cable part 3 can maintain a smooth and stable movement path, avoiding the concentration of mechanical stress caused by excessive bending, thereby extending the service life of the cable.

[0042] In a further preferred embodiment, the wire pressing cover component 10 can also be designed as a component structure, such as Figure 4 As shown, the assembly structure includes a cover body 11, a limit plate 12 and a return spring 13. The limit plate 12 is rotatably connected to the cover body 11 through pins arranged at both ends thereof, and the inner surface of the limit plate 12 is set as a curved surface feature. The two ends of the return spring 13 are respectively installed on the cover body 11 and the limit plate 12. When the return spring 13 is in an untightened free state, the limit plate 12 and the outer wall surface of the cover body 11 have the same and consistent curved surface radius, and the two are in a concentric state; when the radius of the cable is enlarged, if the cable is compressed The outlet position of the wire cover component 10 is bent back, which drives the limit plate 12 to flip in the direction of the bend. The reset spring 13 will be tightened to generate a reset elastic force, thereby driving the inner curved surface of the limit plate 12 to reset and limit the curvature radius of the cable bend, so that it will not be broken due to excessive bending; when the rotation direction of the line connector changes, the cable is gradually tightened under the rotation of the rotor end bearing part 2, and the limit plate 12 is restored to a free state under the elastic force of the reset spring 13. The limit plate 12 does not affect the minimum radius of the cable after tightening. It should be noted that the design of the reset spring 13 in the component structure can be adjusted according to the specific application scenario, such as using springs of different materials or specifications to meet different mechanical requirements. The reset spring 13 can also be replaced by other forms of reset elastic elements, as long as these elements can provide similar reset functions, such as using torsion springs, elastic gaskets or elements made of other elastic materials, so that the appropriate reset device can be flexibly selected according to actual needs to ensure that a stable and reliable reset function can be provided in various working environments.

[0043] Through the above embodiments, the purpose of the present invention is fully and effectively achieved. Those skilled in the art can understand that the present invention includes but is not limited to the contents described in the drawings and the above specific embodiments. Although the present invention has been described with respect to the most practical and preferred embodiments currently considered, it should be understood that the present invention is not limited to the disclosed embodiments, and any modification that does not deviate from the functional and structural principles of the present invention will be included in the scope of the claims.

Claims

1. An integrated cable space line connector for use in spacecraft, comprising a stator end bearing portion, a rotor end bearing portion and a conductive cable portion, characterized in that: The stator end bearing part is installed and connected to the fixed part of the spacecraft and provides fixation and support for the stator cable harness, wherein the hollow interior thereof is formed into a cylindrical space extending along the central axis; The rotor end bearing part is installed and connected to the rotating part of the spacecraft, and is arranged in the stator end bearing part in a coaxial manner with both ends rotatingly supported, and includes a plurality of columnar petal bodies discretely arranged along the circumferential direction and extending along the central axis, and a central hole area extending along the axial direction and used for clamping and supporting the rotor cable bundle is formed between the inner side walls of each columnar petal body; The conductive cable portion is integrally processed to form a spiral curved integrated wiring cable with a rebound characteristic and subjected to insulation treatment, and is spatially distributed in the annular space area between the stator end bearing portion and the rotor end bearing portion, wherein the first end portion is fixedly arranged on the columnar petal body of the rotor end bearing portion in an axially flat manner and is bent in the central hole area and then divided into strands of scattered wire cables, which extend axially to the external space to form a rotor cable bundle, and the second end portion is fixedly arranged on the wall surface of the stator end bearing portion in an axially flat manner and extends radially outward to the external space to form a stator cable bundle; And among them, A strip wire groove extending axially and communicating with the external space is provided on the cylindrical wall surface of the stator end bearing part, the length of the strip wire groove is not less than the wire arrangement width of the conductive cable part, and the second end of the conductive cable part first passes through a wire pressing plate after radially passing through the corresponding strip wire groove and is clamped and fixed on the outer wall surface of the stator end bearing part in an axially flat manner by means of a fastener, and then continues to extend to the external space to form a stator cable bundle; In the rotor end bearing part, the circumferential gap between the two adjacent cylindrical lobed bodies forms a wire installation groove at the first end of the conductive cable part, and the length of the wire installation groove extending in the axial direction is not less than the wire arrangement width of the conductive cable part. The first end is clamped and fixed to the outer wall surface of a cylindrical lobed body in an axially flat manner through a wire pressing cover component and with the help of fasteners. Then, the first end radially passes through the corresponding wire installation groove and is bent into the center hole area to be divided into strands of discrete cables that extend axially to the external space to form a rotor cable bundle.

2. The integrated cable space line connector for use in spacecraft according to claim 1, characterized in that: The stator cable harness extending to the external space has its end electrically connected to a fixed part of the spacecraft, and the structural form of the harness is selected as an integrated wiring cable or multiple cables in the form of loose wires according to the application scenario and space layout requirements; the rotor cable harness extending to the external space has its end electrically connected to the rotating part of the spacecraft, and the structural form of the harness is multiple cables in the form of loose wires.

3. The integrated cable space line connector for use in spacecraft according to claim 1, characterized in that: According to the number of channels of power and / or signals that the line connector needs to transmit, the rotation angle and the geometric shape and size of the annular space area between the stator end bearing part and the rotor end bearing part, one or several groups of independent wiring cables are arranged in the annular space area, and each group of wiring cables is arranged according to a preset number of cable layers and spiral coils.

4. The integrated cable space line connector for use in a spacecraft according to claim 3, characterized in that: For high power and / or signal current transmission cable groups, the transmission capacity and anti-interference ability are improved by increasing the number of cable layers. Otherwise, the number of cable layers needs to be reduced. The spiral line pitch and number of turns of the cable are determined according to the rotation angle range required by the line connector, the number of cable groups and space requirements, and taking into account the mechanical stress and thermal stress that the conductive cable part may withstand during the rotation process.

5. The integrated cable space line connector for use in a spacecraft according to claim 4, characterized in that: When a larger rotation angle range is required, the number of spiral coils is increased and the spacing is appropriately reduced to disperse the stress and improve the flexibility and resilience of the cable. Conversely, the number of spiral coils needs to be reduced and the spacing needs to be increased. At the same time, when the number of cable groups is large, the spiral wire spacing needs to be appropriately increased to avoid interference between different groups of coils.

6. The integrated cable space line connector for use in a spacecraft according to claim 1, characterized in that: A step portion is formed on the outer wall surface of the columnar lobed body, which is adapted to the shape and size of the wire pressing cover component and has smooth transitions on each edge. After the wire pressing cover component clamps the first end of the conductive cable part and is fixed to the step portion by means of fasteners, its outer wall surface is basically flush with the outer wall surface of the main body of the columnar lobed body.

7. The integrated cable space line connector for use in a spacecraft according to claim 6, characterized in that: The wire crimping cover component is designed as a plate-shaped component, and a curved surface feature is set at the wire outlet position away from the wire installation groove. At this position, the outer curved surface radius of the wire crimping cover component is consistent with the minimum radius of the wire spiral line, and the inner curved surface radius is greater than the limit curvature radius when the wire is bent back.

8. The integrated cable space line connector for use in a spacecraft according to claim 6, characterized in that: The wire pressing cover component is designed as a component structure, which at least includes a cover body, a limit plate and a reset elastic element. The limit plate is rotatably connected to the cover body by pins arranged at both ends thereof, and its inner surface is set as a curved surface feature. The two ends of the reset elastic element are respectively installed on the cover body and the limit plate, and when the reset elastic element is in an untightened free state, the limit plate and the outer wall surface of the cover body have the same and consistent curved surface radius.

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