Star-vessel adapter adapter and star-vessel adapter assembly

Abstract

The invention relates to the technical field of aerospace, in particular to a star-warship adapter adapter and a star-warship adapter assembly.The star-warship adapter adapter comprises a body and a driving bearing part which are connected with each other, the body comprises a satellite connecting face and an adapter connecting face, and the driving bearing part comprises a driving bearing face; the adapter connecting surface and the driving bearing surface are both perpendicular to the satellite connecting surface, the driving bearing surface and the adapter connecting surface face the same direction, and the driving bearing surface is used for bearing acting force perpendicular to the driving bearing surface. The purpose of the application is to provide a star-carrier adapter adapter and a star-carrier adapter assembly for at least one technical problem related in the background technology.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a starship adapter adapter and a starship adapter assembly. Background Art

[0002] The satellite is connected to the launch vehicle through a satellite-rocket adapter, and the satellite-rocket is reliably separated after the satellite-rocket enters orbit. The satellite-rocket adapter is designed to have a relatively large rigidity, which can prevent the satellite from colliding with the fairing due to large displacement during the launch process. Traditional satellites use docking rings as satellite-rocket adapters and use a wrapping belt to lock and separate them. The disadvantages of this satellite-rocket connection method are that the docking ring is heavy, occupies a large satellite docking area, and is not flexible enough to use. Now more and more commercial aerospace uses single-point satellite-rocket adapters, and each adapter is used separately. The advantages are that the single-point satellite-rocket adapter is light in weight, the corresponding number of adapters can be matched according to the size and weight of the satellite, and the position between the adapters can be adjusted - all adapters can be adjusted to the best installation position through mechanical analysis, so that the satellite as a whole has higher rigidity and lower mechanical environment. The way to separate the satellite through the satellite-rocket adapter after launch is generally to separate it perpendicular to the installation surface.

[0003] At present, both the traditional satellite-rocket docking ring and the increasingly common single-point satellite-rocket adapter are directly connected to the satellite through the adapter connecting screws. Commercial satellites are mostly launched by carpooling, and many satellites are hung on their sides on the carrier bracket. The longitudinal vibration environment of the carrier corresponds to the tangential direction of the adapter connecting screws. At this time, the vibration environment of the carrier reduces the safety margin of the adapter connecting screws for the satellite and increases the probability of failure of the adapter connecting screws. Summary of the invention

[0004] The purpose of the present application is to provide a starship adapter adapter and a starship adapter assembly in response to at least one technical problem involved in the background technology.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions: One aspect of the present application provides a starship adapter adapter, comprising a main body and a drive receiving portion connected to each other, the main body comprising a satellite connection surface and an adapter connection surface, the drive receiving portion comprising a drive receiving surface, the adapter connection surface and the drive receiving surface are both arranged perpendicular to the satellite connection surface, the drive receiving surface and the adapter connection surface have the same orientation, and the drive receiving surface is used to receive a force perpendicular to the drive receiving surface.

[0006] Optionally, the main body and the drive receiving portion are arranged in a first direction, and the first direction is perpendicular to the satellite connection surface.

[0007] The beneficial effect of this technical solution is that, when the adapter connection surface is connected to the adapter and the drive receiving surface is in contact with the drive member, mutual interference between the adapter and the drive member is unlikely to occur.

[0008] Optionally, the drive receiving surface and the adapter connecting surface are located in the same plane, and the drive receiving surface and the adapter connecting surface are connected as one body.

[0009] The beneficial effect of this technical solution is that in the embodiment of the present application, the parallelism between the drive receiving surface and the adapter connecting surface includes the situation that the drive receiving surface and the adapter connecting surface are located in the same plane, and the situation that the extension of the drive receiving surface and the extension of the adapter connecting surface do not intersect with each other.

[0010] Optionally, the drive receiving portion includes a straight line segment and a semicircular segment, and in the first direction, the main body, the straight line segment and the semicircular segment are sequentially connected, and the arc surface on the semicircular segment is arranged to face away from the main body.

[0011] The beneficial effect of this technical solution is that: in this way, the part of the driving receiving surface corresponding to the semicircular segment is semicircular. Compared with making the driving receiving part an entire square structure, making the driving receiving part include a semicircular segment reduces the outwardly protruding edges and corners, making it difficult for the driving bearing part to interfere with other external components. At the same time, when the driving part is a driving spring, the position of the center of the driving spring can correspond to the position of the center of the semicircular segment, so that it is not easy for the driving spring and the driving receiving surface to have an adverse effect on the separation of the starship due to misalignment.

[0012] Optionally, a whole star reference pin hole is formed on the drive receiving portion, and the whole star reference pin hole is located at the center of the semicircular segment.

[0013] The beneficial effect of this technical solution is that in the later assembly stage, the precision measuring pin is installed in the whole satellite reference pin hole, and then the precision measuring equipment is used to measure the whole satellite reference.

[0014] Optionally, an adapter connection threaded hole is formed on the adapter connection surface, and a first weight-reducing groove is also formed on the adapter connection surface.

[0015] The beneficial effects of this technical solution are: since the adapter connecting threaded hole is connected to the adapter through the adapter connecting screw, the shape and position accuracy requirements are relatively high. Since the first weight reduction groove has no accuracy requirements, when the adapter connecting threaded hole is fine-machined, the influence of possible deformation on the first weight reduction groove can be ignored, so that the adapter connecting threaded hole can be easily met with the accuracy requirements and the difficulty of mechanical processing is reduced; setting the first weight reduction groove can also reduce the weight of the starship adapter adapter.

[0016] Optionally, a separation switch mounting surface is also formed on the main body, the adapter connection surface and the satellite connection surface are both perpendicular to the separation switch mounting surface, and a separation switch mounting interface is arranged on the separation switch mounting surface; and / or, a reference prism mounting surface is also formed on the main body, and the reference prism mounting surface and the adapter connection surface are two end surfaces arranged opposite to each other on the main body.

[0017] The beneficial effects of this technical solution are: it makes it easier to install the separation switch on the starship adapter; the star-rocket adapter is the part with the highest rigidity in the entire satellite, so installing the entire satellite reference prism on the adapter is less affected by the deformation of the entire satellite.

[0018] Optionally, at least two groups of slot holes arranged in a second direction are formed on the satellite connection surface, and the slot hole groups include a second weight reducing slot, a positioning pin hole and three step holes; in the slot hole groups, each step hole is arranged in a third direction, and the second weight reducing slot is arranged between one step hole and another step hole, and the positioning pin hole is arranged between the other step hole and each of the third step holes; the third direction is perpendicular to the adapter connection surface, the second direction is perpendicular to the third direction and the second direction is parallel to the adapter connection surface.

[0019] The beneficial effect of this technical solution is that the starship adapter adapter can be fixed to the satellite through the step holes and corresponding connecting parts. At least six step holes are connected to the satellite, and the shape and position accuracy requirements are high. The provision of a second weight-reducing groove can not only reduce the weight of the starship adapter adapter, but also make it easier to process step holes and / or locating pin holes with higher precision; the locating pin holes are used for subsequent repeated disassembly and assembly to ensure installation accuracy.

[0020] Optionally, the starship adapter adapter is a mirror-symmetrical structure, and the symmetry plane of the starship adapter adapter is perpendicular to the satellite connection surface.

[0021] Another aspect of the present application provides a starship adapter assembly, including an adapter, a reference prism, a separation switch, a drive spring and a starship adapter adapter provided by the present application, the adapter, the reference prism and the separation switch are all fixedly connected to the starship adapter adapter, and the drive spring abuts against the starship adapter adapter.

[0022] The technical solution provided by this application can achieve at least one of the following beneficial effects: The starship adapter adapter and starship adapter assembly provided by the present application, when in use, are used to dock the satellite and the rocket through the starship adapter adapter and the adapter, with the drive receiving surface and the adapter connecting surface both perpendicular to the vertical direction, and can be connected to the side of the satellite through the satellite connecting surface, and connected to the adapter through the adapter connecting surface and the adapter connecting screws, and the drive receiving surface is in contact with the driving part so that the satellite can be sent out longitudinally when the satellite is separated from the rocket. At this time, the axial direction of the adapter connecting screw used to connect the adapter connecting surface and the adapter corresponds to the longitudinal vibration environment of the carrier. Since the mechanical environment during the launch process is longitudinal vibration, which is worse than the lateral vibration environment, and the mechanical property of the adapter connecting screw is that the axial tensile strength is greater than the shear strength. Therefore, relative to making the tangential direction of the adapter connecting screw correspond to the longitudinal vibration environment of the carrier, the vibration environment of the carrier is the most friendly to the satellite, thereby reducing the risk of failure of the adapter connecting screw.

[0023] The additional technical features and advantages of the present application will be more clearly explained in the following description, or can be understood through the specific practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions of the specific implementation methods of the present application, the following is a brief introduction to the drawings required for the description of the specific implementation methods. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0025] Figure 1 A partial three-dimensional structural schematic diagram of an implementation method of a starship adapter assembly provided in an embodiment of the present application applied to a satellite; Figure 2 A schematic diagram of a three-dimensional structure at one angle of an implementation method of a starship adapter adapter provided in an embodiment of the present application; Figure 3 A schematic diagram of the three-dimensional structure from another angle of an implementation manner of the starship adapter adapter provided in an embodiment of the present application.

[0026] Reference numerals: 01. Reference prism; 02. Satellite; 03. Hoisting part; 04. Main body; 05. Separation switch; 06. Adapter; 07. Driving spring; 08. Reference prism mounting surface; 09. Installation threaded hole; 10. Step hole; 11. Strengthen the connecting ribs; 12. Drive the receiving part; 13. Separation switch installation interface; 14. Separation switch installation surface; 15. Threaded through hole; 16. Reinforcement rib; 17. Second weight reduction groove; 18. Whole star reference pin hole; 19. Drive receiving surface; 20. Adapter connecting surface; 21. First weight-reducing groove; 22. Adapter connection threaded hole; 24. Satellite connection surface; 25. Positioning pin hole; 26. Starship adapter adapter; 27. Straight line segment; 28. Semicircle segment. DETAILED DESCRIPTION

[0027] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present application.

[0028] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0029] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0030] like Figures 1 to 3As shown, one aspect of the present application provides a starship adapter adapter 26, including a main body 04 and a drive receiving portion 12 that are connected to each other, the main body 04 including a satellite connection surface 24 and an adapter connection surface 20, the drive receiving portion 12 including a drive receiving surface 19, the adapter connection surface 20 and the drive receiving surface 19 are both arranged perpendicular to the satellite connection surface 24, the drive receiving surface 19 and the adapter connection surface 20 have the same orientation, and the drive receiving surface 19 is used to receive a force perpendicular to the drive receiving surface 19.

[0031] It can be understood that the drive receiving portion 12 is used to receive the force applied by the driving member to the satellite so that the satellite obtains the initial separation velocity.

[0032] In the embodiment of the present application, preferably, an adapter connection threaded hole 22 for installing an adapter connection screw of the adapter 06 is formed on the adapter connection surface 20 .

[0033] The starship adapter adapter 26 provided in the present application, when in use, is used to dock the satellite 02 with the rocket through the starship adapter adapter 26 and the adapter 06, and the drive receiving surface 19 and the adapter connecting surface 20 are both perpendicular to the vertical direction. It can be connected to the side of the satellite 02 through the satellite connecting surface 24, and connected to the adapter 06 through the adapter connecting surface 20 and the adapter connecting screws, and the drive receiving surface 19 is in contact with the driving part to achieve the satellite 02 being able to be sent out longitudinally when the satellite 02 is separated from the rocket. At this time, the axial direction of the adapter connecting screw used to connect the adapter connecting surface 20 and the adapter 06 corresponds to the longitudinal vibration environment of the carrier. Since the mechanical environment during the launch process is longitudinal vibration, which is worse than the lateral vibration environment, and the mechanical property of the adapter connecting screw is that the axial tensile strength is greater than the shear strength. Therefore, relative to making the tangential direction of the adapter connecting screw correspond to the longitudinal vibration environment of the carrier, the vibration environment of the carrier is the most friendly to the satellite 02 at this time, thereby reducing the risk of failure of the adapter connecting screw.

[0034] Optionally, the body 04 and the drive receiving portion 12 are arranged in a first direction, and the first direction is perpendicular to the satellite connection surface 24. In this way, when the adapter connection surface 20 is connected to the adapter 06, and when the drive receiving surface 19 is in contact with the driver, it is not easy for the adapter 06 and the driver to interfere with each other.

[0035] Optionally, the drive receiving surface 19 and the adapter connecting surface 20 are located in the same plane, and the drive receiving surface 19 and the adapter connecting surface 20 are connected as a whole. In the embodiment of the present application, the drive receiving surface 19 and the adapter connecting surface 20 are parallel, including the situation that the drive receiving surface 19 and the adapter connecting surface 20 are located in the same plane, and the extension of the drive receiving surface 19 and the extension of the adapter connecting surface 20 do not intersect each other.

[0036] Optionally, the drive receiving portion 12 includes a straight segment 27 and a semicircular segment 28. In the first direction, the body 04, the straight segment 27 and the semicircular segment 28 are connected in sequence, and the arc surface on the semicircular segment 28 is arranged to face away from the body 04. In this way, the portion of the drive receiving surface 19 corresponding to the semicircular segment 28 is semicircular. Compared with making the drive receiving portion 12 an entire block-shaped structure, making the drive receiving portion 12 include the semicircular segment 28 reduces the outwardly protruding edges and corners, making it difficult for the drive bearing portion to interfere with other external components. At the same time, when the driving member is a drive spring 07, the position of the center of the drive spring 07 can correspond to the position of the center of the semicircular segment 28, so that it is not easy for the drive spring 07 and the drive receiving surface 19 to have a problem of adversely affecting the separation of the starship due to misalignment. In the embodiment of the present application, the size of the straight line segment 27 in the direction perpendicular to the first direction and parallel to the driving receiving surface 19 can be the same as the diameter of the semicircular segment 28. The size of the straight line segment 27 in the first direction can be the same as the diameter of the semicircular segment 28 or slightly smaller than the diameter of the semicircular segment 28. When the size of the straight line segment 27 in the first direction is slightly smaller than the diameter of the semicircular segment 28, part of the adapter connecting surface 20 can contact part of the driving spring 07.

[0037] Optionally, a whole star reference pin hole 18 is formed on the drive receiving portion 12, and the whole star reference pin hole 18 is located at the center of the semicircular segment 28. In the later assembly stage, the precision measuring pin is installed in the whole star reference pin hole 18, and then the precision measuring equipment is used to measure the whole star reference.

[0038] Optionally, an adapter connection threaded hole 22 is formed on the adapter connection surface 20, and a first weight-reducing groove 21 is also formed on the adapter connection surface 20. Since the adapter connection threaded hole 22 is connected to the adapter 06 through the adapter connection screw, the shape and position accuracy requirements are relatively high. Since there is no accuracy requirement for the first weight-reducing groove 21, when the adapter connection threaded hole 22 is finely machined, the influence of possible deformation on the first weight-reducing groove 21 can be ignored, so that the adapter connection threaded hole 22 can easily meet the accuracy requirements and reduce the difficulty of mechanical processing; the first weight-reducing groove 21 can also reduce the weight of the starship adapter adapter 26.

[0039] Preferably, the adapter connection surface 20 is a square surface, and at least four adapter connection threaded holes 22 and at least four first weight-reducing grooves 21 are formed on the adapter connection surface 20. The four adapter connection threaded holes 22 are arranged one-to-one at the four corners of the adapter connection surface 20, and the four first weight-reducing grooves 21 are arranged one-to-one at the four sides of the adapter connection surface 20. In this way, the four first weight-reducing grooves 21 are arranged one-to-one at the positions between each two adjacent corners on the adapter connection surface 20. The multiple first weight-reducing grooves 21 can reduce the weight of the starship adapter adapter 26 to a certain extent. At the same time, since the first weight-reducing grooves 21 are arranged on both sides of the adapter connection threaded hole 22, it is more convenient for the adapter connection threaded hole 22 to obtain a higher processing accuracy.

[0040] Optionally, a separation switch installation surface 14 is also formed on the body 04, the adapter connection surface 20 and the satellite connection surface 24 are both perpendicular to the separation switch installation surface 14, and a separation switch installation interface 13 is provided on the separation switch installation surface 14, so as to facilitate the installation of the separation switch 05 on the starship adapter adapter 26, and the separation switch 05 is also connected to the adapter 06. The function of the separation switch 05 is to change the state of the separation switch 05 after the adapter 06 is separated from the star-rocket adapter adapter, and the satellite 02 can be separated. After power is turned on, the separation switch mounting surfaces 14 are preferably provided on two opposite sides of the main body 04; and / or, a reference prism mounting surface 08 is also formed on the main body 04, and the reference prism mounting surface 08 and the adapter connecting surface 20 are two end surfaces arranged opposite to each other on the main body 04. Preferably, four mounting threaded holes 09 for mounting the reference prism are provided on the reference prism mounting surface 08. The star-rocket adapter adapter is the part with the highest rigidity of the entire satellite, so installing the entire reference prism on the adapter is less affected by the deformation of the entire satellite.

[0041] Optionally, at least two groups of slots arranged in the second direction are formed on the satellite connection surface 24, and the slot group includes a second weight-reducing slot 17, a positioning pin hole 25 and three step holes 10; each of the step holes 10 in the slot group is arranged in the third direction, and the second weight-reducing slot 17 is provided between one step hole 10 and another step hole 10, and the positioning pin hole 25 is provided between the other step hole 10 and each of the third step holes 10; the third direction is perpendicular to the adapter connection surface 20, the second direction is perpendicular to the third direction and the second direction is parallel to the adapter connection surface 20. The starship adapter adapter 26 can be fixed to the satellite 02 through the step holes 10 and the corresponding connectors. At least six step holes 10 are connected to the satellite 02, and the shape and position accuracy requirements are relatively high. The second weight-reducing slot 17 can not only reduce the weight of the starship adapter adapter 26, but also facilitate the processing of step holes 10 and / or positioning pin holes 25 with higher accuracy; the positioning pin holes 25 are used for subsequent repeated disassembly and assembly to ensure installation accuracy. In the embodiment of the present application, the positioning pin hole 25 is punched after the star-rocket adapter adapter and the satellite 02 platform are assembled and debugged and the various connecting parts are fixed. In the embodiment of the present application, preferably, a plurality of reinforcing connecting ribs 11 are designed between each step hole 10, between each adapter connection threaded hole 22 and / or between the step hole 10 and the adapter connection threaded hole 22. The reinforcing connecting ribs 11 are of the same thickness, and the main load-bearing connection holes-adapter connection threaded holes 22 and step holes 10 are connected and reinforced. Each adapter connection threaded hole 22 and step hole 10 correspond to a plurality of reinforcing connecting ribs 11, and the reinforcing connecting ribs 11 are distributed in the three directions of length, width and height to ensure that effective force transmission can be achieved in all three directions; a plurality of hoisting parts 03 are arranged on the outside of the body 04, and the hoisting part 03 has a hoisting surface, and a threaded through hole 15 for hoisting is arranged on the hoisting surface, and each hoisting part 03 has at least five reinforcing ribs 16 for improving the connection strength of the threaded through hole 15 to improve the hoisting reliability.

[0042] Optionally, the starship adapter adapter 26 is a mirror-symmetrical structure, and the symmetry plane of the starship adapter adapter 26 is perpendicular to the satellite connection surface 24.

[0043] The starship adapter 26 provided in the present application uses two perpendicular surfaces to connect the satellite 02 and the adapter 06, and is more suitable for launching when the satellite 02 is hung on its side on the carrier bracket; the starship adapter 26 provided in the present application is installed on the side of the satellite 02 platform, but does not increase the height of the satellite 02 too much, which is in line with the design concept of the flat-panel satellite 02, while reducing the height difference between the satellite-rocket docking surface and each single satellite 02, weakening the amplification factor of the launch vibration environment; the starship adapter 26 provided in the present application has greater rigidity in all directions, and has multiple interfaces left to the outside, integrating separation switch interfaces, satellite reference prism interfaces, and whole-satellite hoisting interfaces, thereby simplifying the number of docking interfaces of the satellite 02 platform structure; the starship adapter 26 provided in the present application weakens the impact force transmitted to the satellite 02 during the separation of the satellite and the rocket to a certain extent.

[0044] Another aspect of the present application provides a starship adapter assembly, including an adapter 06, a reference prism 01, a separation switch 05, a drive spring 07 and a starship adapter adapter 26 provided in the present application, wherein the adapter 06, the reference prism 01 and the separation switch 05 are all fixedly connected to the starship adapter adapter 26, and the drive spring 07 abuts against the starship adapter adapter 26.

[0045] The starship adapter assembly provided by the present application adopts the starship adapter adapter 26 provided by the present application. When in use, the satellite 02 is docked with the rocket through the starship adapter adapter 26 and the adapter 06, and the drive receiving surface 19 and the adapter connecting surface 20 are both perpendicular to the vertical direction. It can be connected to the side of the satellite 02 through the satellite connecting surface 24, and connected to the adapter 06 through the adapter connecting surface 20 and the adapter connecting screw, and the drive receiving surface 19 is in contact with the driving part to achieve the satellite 02 being able to be sent out longitudinally when the satellite 02 is separated from the rocket. At this time, the axial direction of the adapter connecting screw used to connect the adapter connecting surface 20 and the adapter 06 corresponds to the longitudinal vibration environment of the carrier. Since the mechanical environment during the launch process is longitudinal vibration, which is worse than the lateral vibration environment, and the mechanical property of the adapter connecting screw is that the axial tensile strength is greater than the shear strength. Therefore, relative to making the tangential direction of the adapter connecting screw correspond to the longitudinal vibration environment of the carrier, the vibration environment of the carrier is the most friendly to the satellite 02 at this time, thereby reducing the risk of failure of the adapter connecting screw.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. Starship adapter adapter, characterized in that: It includes a main body and a drive receiving part that are interconnected, the main body includes a satellite connecting surface and an adapter connecting surface, the drive receiving part includes a drive receiving surface, the adapter connecting surface and the drive receiving surface are both arranged perpendicular to the satellite connecting surface, the drive receiving surface and the adapter connecting surface have the same orientation, and the drive receiving surface is used to receive the force perpendicular to the drive receiving surface.

2. The starship adapter according to claim 1, characterized in that: The main body and the driving receiving portion are arranged in a first direction, and the first direction is perpendicular to the satellite connection surface.

3. The starship adapter according to claim 2, characterized in that: The drive receiving surface and the adapter connecting surface are located in the same plane, and the drive receiving surface and the adapter connecting surface are connected as one body.

4. The starship adapter according to claim 3, characterized in that: The drive receiving portion includes a straight line segment and a semicircular segment. In the first direction, the body, the straight line segment and the semicircular segment are sequentially connected, and the arc surface on the semicircular segment is arranged to face away from the body.

5. The starship adapter according to claim 4, characterized in that: A whole star reference pin hole is formed on the driving receiving portion, and the whole star reference pin hole is located at the center of the semicircular segment.

6. The starship adapter according to any one of claims 1 to 5, characterized in that: An adapter connection threaded hole is formed on the adapter connection surface, and a first weight-reducing groove is also formed on the adapter connection surface.

7. The starship adapter according to any one of claims 1 to 5, characterized in that: A separation switch mounting surface is also formed on the main body, the adapter connection surface and the satellite connection surface are both perpendicular to the separation switch mounting surface, and a separation switch mounting interface is arranged on the separation switch mounting surface; and / or a reference prism mounting surface is also formed on the main body, the reference prism mounting surface and the adapter connection surface are two end surfaces arranged opposite to each other on the main body.

8. The starship adapter according to any one of claims 1 to 5, characterized in that: At least two groups of slot holes are formed on the satellite connection surface and are arranged in the second direction, and the slot hole groups include a second weight-reducing slot, a positioning pin hole and three step holes; in the slot hole groups, each step hole is arranged in a third direction, and the second weight-reducing slot is arranged between one step hole and another step hole, and the positioning pin hole is arranged between the other step hole and each of the third step holes; the third direction is perpendicular to the adapter connection surface, the second direction is perpendicular to the third direction and the second direction is parallel to the adapter connection surface.

9. The starship adapter according to any one of claims 1 to 5, characterized in that: The starship adapter adapter is a mirror-symmetrical structure, and the symmetry plane of the starship adapter adapter is perpendicular to the satellite connection plane.

10. A starship adapter assembly, characterized in that It includes an adapter, a reference prism, a separation switch, a drive spring and a starship adapter adapter as described in any one of claims 1 to 9, the adapter, the reference prism and the separation switch are all fixedly connected to the starship adapter adapter, and the drive spring abuts against the starship adapter adapter.

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