Starship Adapter Adapter Base and Starship Adapter Assembly

Abstract

This application relates to the field of aerospace technology. Specifically, it relates to a starship adapter adapter seat and a starship adapter assembly, including a main body and a drive receiving part that are connected to each other. The main body includes a satellite connection surface and an adapter connection surface, and the drive receiving part includes a drive receiving surface. The adapter connection surface and the drive receiving surface are both perpendicular to the satellite connection surface, the drive receiving surface faces the same direction as the adapter connection surface, and the drive receiving surface is used to receive a force perpendicular to the drive receiving surface. The purpose of this application is to provide a starship adapter adapter seat and a starship adapter assembly for at least one technical problem involved in the background technology.

Description

Technical Field

[0001] This application relates to the field of aerospace technology. Specifically, it relates to a starship adapter adapter seat and a starship adapter assembly. Background Art

[0002] The satellite is connected to the launch vehicle through a star-vehicle adapter and realizes reliable separation of the star-vehicle after the star-vehicle is in orbit. The star-vehicle adapter is designed with relatively high stiffness to prevent the satellite from colliding with the fairing due to large displacement during launch. Traditional satellites use a docking ring as the star-vehicle adapter and adopt strap locking for separation. The disadvantage of this star-vehicle connection method is that the docking ring is relatively heavy, occupies a large satellite docking area, and is not flexible enough to use. Now, more and more commercial space applications use single-point star-vehicle adapters, each adapter is used separately. The advantages of the single-point star-vehicle adapter are that it is relatively light in weight, the number of adapters can be matched according to the volume and weight of the satellite, and the positions of the adapters can be adjusted - through mechanical analysis, all adapters can be adjusted to the optimal installation positions, making the overall satellite have relatively high stiffness and a relatively low mechanical environment. After the satellite is launched, the separation method through the star-vehicle adapter is generally perpendicular to the installation surface.

[0003] Currently, whether it is the traditional star-vehicle docking ring or the increasingly common single-point star-vehicle adapter, they are directly connected to the satellite through adapter connection screws. Many commercial satellites are launched by sharing a vehicle, and many satellites are hung on the launch vehicle bracket. The longitudinal vibration environment of the launch vehicle corresponds to the tangential direction of the adapter connection screws. At this time, the vibration environment of the launch vehicle reduces the safety margin of the adapter connection screws for the satellite and increases the probability of failure of the adapter connection screws. Summary of the Invention

[0004] The purpose of this application is to provide a starship adapter adapter seat and a starship adapter assembly for at least one technical problem involved in the background art.

[0005] To achieve the above purpose, this application adopts the following technical solutions:

[0006] One aspect of this application provides a starship adapter adapter seat, including a body and a driving and receiving part connected to each other. The body includes a satellite connection surface and an adapter connection surface, and the driving and receiving part includes a driving and receiving surface. The adapter connection surface and the driving and receiving surface are both perpendicular to the satellite connection surface. The driving and receiving surface and the adapter connection surface face the same direction, and the driving and receiving surface is used to receive a force perpendicular to the driving and receiving surface.

[0007] Optionally, the body and the driving and receiving part are arranged in a first direction perpendicular to the satellite connection surface.

[0008] The beneficial effects of this technical solution are as follows: In this way, when the adapter connection surface is connected to the adapter and the driving bearing surface is in contact with the driving member, it is not easy for interference to occur between the adapter and the driving member.

[0009] Optionally, the driving bearing surface and the adapter connection surface are located in the same plane, and the driving bearing surface and the adapter connection surface are integrated.

[0010] The beneficial effects of this technical solution are as follows: In the embodiments of the present application, the parallelism between the driving bearing surface and the adapter connection surface includes the case where the driving bearing surface and the adapter connection surface are located in the same plane, and the case where the extension of the driving bearing surface and the extension of the adapter connection surface do not intersect with each other.

[0011] Optionally, the driving bearing portion includes a straight segment and a semicircular segment. In the first direction, the body, the straight segment, and the semicircular segment are connected in sequence, and the arc surface on the semicircular segment is arranged facing away from the body.

[0012] The beneficial effects of this technical solution are as follows: In this way, the part of the driving bearing surface corresponding to the semicircular segment is semicircular. Compared with making the entire driving bearing portion a square structure, making the driving bearing portion include a semicircular segment reduces the outward protruding edges and corners, making it not easy for the driving bearing portion to interfere with other external components. At the same time, when the driving member is a driving spring, the position of the center of the driving spring can correspond to the center position of the semicircular segment, making it not easy for problems that may have an adverse impact on the separation of the starship due to misalignment to occur between the driving spring and the driving bearing surface.

[0013] Optionally, a whole-star reference pin hole is formed on the driving bearing portion, and the whole-star reference pin hole is located at the center of the semicircular segment.

[0014] The beneficial effects of this technical solution are as follows: In the later sub-assembly stage, the precision measurement pin is installed in the whole-star reference pin hole, and then the whole-star reference is measured using precision measurement equipment.

[0015] 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.

[0016] The beneficial effects of this technical solution are as follows: Since the adapter connection threaded hole is connected to the adapter through an adapter connection screw, the form and position accuracy requirements are relatively high. Since there are no accuracy requirements for the first weight-reducing groove, when the adapter connection threaded hole is finely machined, the possible deformation can be ignored for its impact on the first weight-reducing groove, making it easier for the adapter connection threaded hole to meet the accuracy requirements and reducing the mechanical processing difficulty; setting the first weight-reducing groove can also reduce the weight of the starship adapter adapter seat.

[0017] Optionally, a separation switch mounting surface is further formed on the body. Both the adapter connection surface and the satellite connection surface are perpendicular to the separation switch mounting surface, and a separation switch mounting interface is provided on the separation switch mounting surface; and / or, a reference prism mounting surface is further formed on the body, and the reference prism mounting surface and the adapter connection surface are two end faces of the body that are arranged away from each other.

[0018] The beneficial effects of this technical solution are as follows: It is thus convenient to mount the separation switch on the starship adapter adapter base; the starship adapter adapter base is the part with the highest stiffness of the entire satellite, so mounting the reference prism of the entire satellite on the adapter base is less affected by the deformation of the entire satellite.

[0019] Optionally, at least two sets of slot hole groups arranged in the second direction are formed on the satellite connection surface. Each slot hole group includes a second weight reduction slot, a positioning pin hole, and three stepped holes; in each slot hole group, the stepped holes are arranged in the third direction, and a second weight reduction slot is provided between one stepped hole and another stepped hole, and a positioning pin hole is provided between the other stepped hole and the third stepped hole; 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.

[0020] The beneficial effects of this technical solution are as follows: The starship adapter adapter base can be fixed to the satellite through the stepped holes and corresponding connecting parts. At least six stepped holes are connected to the satellite, and the form and position accuracy requirements are relatively high. The second weight reduction slot not only plays a role in reducing the weight of the starship adapter adapter base, but also makes it easier to machine stepped holes and / or positioning pin holes with higher precision; the positioning pin holes are used to ensure the installation accuracy during subsequent repeated disassembly and assembly.

[0021] Optionally, the starship adapter adapter base is a mirror-symmetrical structure, and the symmetry plane of the starship adapter adapter base is perpendicular to the satellite connection surface.

[0022] Another aspect of the present application provides a starship adapter assembly, including an adapter, a reference prism, a separation switch, a driving spring, and the starship adapter adapter base provided by the present application. The adapter, the reference prism, and the separation switch are all fixedly connected to the starship adapter adapter base, and the driving spring abuts against the starship adapter adapter base.

[0023] The technical solution provided by the present application can achieve at least one of the following beneficial effects:

[0024] When the starship adapter adapter base and the starship adapter assembly provided by this application are in use, the satellite is docked with the rocket through the starship adapter adapter base and the adapter. The driving bearing surface and the adapter connection surface are both perpendicular to the vertical direction. It can be connected to the side of the satellite through the satellite connection surface, connected to the adapter through the adapter connection surface and the adapter connection screws, and the driving bearing surface is in contact with the driving part to longitudinally send out the satellite when the satellite and the rocket are separated. At this time, the axial direction of the adapter connection screws used to connect the adapter connection surface and the adapter corresponds to the longitudinal vibration environment of the carrier. Since the mechanical environment during the carrier launch process is that the longitudinal vibration is harsher than the lateral vibration environment, and the mechanical property of the adapter connection screws is that the axial bearing tensile and compressive strength is greater than the bearing shear strength, so compared with making the tangential direction of the adapter connection screws correspond to the longitudinal vibration environment of the carrier, the vibration environment of the carrier is the most friendly to the satellite at this time, thereby reducing the risk of failure of the adapter connection screws.

[0025] The additional technical features and their advantages of this application will be more clearly described in the following description content, or can be understood through the specific practice of this application. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the specific embodiments of this application, the drawings required for use in the description of the specific embodiments will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of this application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0027] Figure 1 It is a partial three-dimensional structure schematic diagram of an implementation manner in which the starship adapter assembly provided by an embodiment of this application is applied to a satellite;

[0028] Figure 2 It is a three-dimensional structure schematic diagram of an implementation manner of the starship adapter adapter base provided by an embodiment of this application from one angle;

[0029] Figure 3 It is a three-dimensional structure schematic diagram of an implementation manner of the starship adapter adapter base provided by an embodiment of this application from another angle.

[0030] Reference Numerals:

[0031] 01, reference prism; 02, satellite;

[0032] 03, lifting part; 04, body;

[0033] 05, separation switch; 06, adapter;

[0034] 07, drive spring; 08, reference prism mounting surface;

[0035] 09. Mounting threaded hole; 10. Step hole;

[0036] 11. Reinforcing connecting rib; 12. Driving receiving part;

[0037] 13. Disconnecting switch mounting interface; 14. Disconnecting switch mounting surface;

[0038] 15. Threaded through-hole; 16. Reinforcing rib;

[0039] 17. Second weight-reducing groove; 18. Whole satellite reference pin hole;

[0040] 19. Driving receiving surface; 20. Adapter connecting surface;

[0041] 21. First weight-reducing groove; 22. Adapter connecting threaded hole;

[0042] 24. Satellite connecting surface; 25. Positioning pin hole;

[0043] 26. Starship adapter adapter seat; 27. Straight section;

[0044] 28. Semi-circular section. Detailed implementation manner

[0045] The technical solutions of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the protection scope of the present application.

[0046] In the description of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is 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 should not be construed as a limitation to the present application. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0047] In the description of the present application, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "joined" 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0048] As Figures 1 to 3 shown, one aspect of the present application provides a starship adapter adapter 26, including a body 04 and a drive receiving portion 12 connected to each other. The body 04 includes a satellite connection surface 24 and an adapter connection surface 20. The drive receiving portion 12 includes a drive receiving surface 19. The adapter connection surface 20 and the drive receiving surface 19 are both perpendicularly arranged with respect to the satellite connection surface 24. The drive receiving surface 19 and the adapter connection surface 20 face the same direction, and the drive receiving surface 19 is used to receive a force perpendicular to the drive receiving surface 19.

[0049] It can be understood that the drive receiving portion 12 is used to receive the force exerted by the drive member on the satellite, so that the satellite obtains an initial separation velocity.

[0050] 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.

[0051] When the starship adapter adapter 26 provided by the present application is in use, the satellite 02 is docked with the rocket through the starship adapter adapter 26 and the adapter 06. The drive receiving surface 19 and the adapter connection surface 20 are both perpendicular to the vertical direction. The satellite 02 can be connected to the side surface of the satellite 02 through the satellite connection surface 24, connected to the adapter 06 through the adapter connection surface 20 and the adapter connection screw, and the drive receiving surface 19 is in contact with the drive member so that the satellite 02 can be longitudinally sent out when the satellite 02 is separated from the rocket. At this time, the axial direction of the adapter connection screw for connecting the adapter connection surface 20 and the adapter 06 corresponds to the longitudinal vibration environment of the carrier. Since the mechanical environment during the launch of the carrier is that the longitudinal vibration is more severe than the transverse vibration environment, and the mechanical property of the adapter connection screw is that the axial load-bearing tensile and compressive strength is greater than the shear strength, so compared with making the tangential direction of the adapter connection 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 connection screw.

[0052] Optionally, the body 04 and the drive receiving part 12 are arranged in a first direction perpendicular to the satellite connection surface 24. In this way, when the adapter connection surface 20 is connected to the adapter 06 and the drive receiving surface 19 contacts the driving member, interference between the adapter 06 and the driving member is not likely to occur.

[0053] Optionally, the drive receiving surface 19 and the adapter connection surface 20 are located in the same plane and are integrated. In the embodiments of the present application, the parallelism between the drive receiving surface 19 and the adapter connection surface 20 includes the case where the drive receiving surface 19 and the adapter connection surface 20 are located in the same plane, and the case where the extension of the drive receiving surface 19 and the extension of the adapter connection surface 20 do not intersect with each other.

[0054] Optionally, the drive receiving part 12 includes a straight segment 27 and a semi-circular segment 28. In the first direction, the body 04, the straight segment 27, and the semi-circular segment 28 are connected in sequence, and the arc surface on the semi-circular segment 28 faces away from the body 04. In this way, the part of the drive receiving surface 19 corresponding to the semi-circular segment 28 is semi-circular. Compared with making the drive receiving part 12 have a whole square structure, making the drive receiving part 12 include the semi-circular segment 28 reduces the outward protruding edges and corners, making it less likely for the drive bearing part to interfere with other external components. At the same time, when the driving member is the driving spring 07, the position of the center of the driving spring 07 can correspond to the center position of the semi-circular segment 28, making it less likely for problems unfavorable to the separation of the starship to occur due to misalignment between the driving spring 07 and the drive receiving surface 19. In the embodiments of the present application, the dimension of the straight segment 27 in the direction perpendicular to the first direction and parallel to the drive receiving surface 19 can be the same as the diameter of the semi-circular segment 28, and the dimension of the straight segment 27 in the first direction can be the same as or slightly smaller than the diameter of the semi-circular segment 28. When the dimension of the straight segment 27 in the first direction is slightly smaller than the diameter of the semi-circular segment 28, part of the adapter connection surface 20 can be in contact with part of the driving spring 07.

[0055] Optionally, a whole-star reference pin hole 18 is formed on the drive receiving part 12, and the whole-star reference pin hole 18 is located at the center of the semi-circular segment 28. In the later sub-assembly stage, the fine measurement pin is installed in the whole-star reference pin hole 18, and then the whole-star reference is measured using fine measurement equipment.

[0056] 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.

[0057] 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.

[0058] 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.

[0059] Optionally, at least two sets of slot groups arranged in the second direction are formed on the satellite connection surface 24. Each slot group includes a second weight reduction slot 17, a positioning pin hole 25, and three stepped holes 10. In each slot group, the stepped holes 10 are arranged in the third direction. A second weight reduction slot 17 is provided between one stepped hole 10 and another stepped hole 10, and a positioning pin hole 25 is provided between the other stepped hole 10 and the third stepped hole 10. The third direction is perpendicular to the adapter connection surface 20, the second direction is perpendicular to the third direction and parallel to the adapter connection surface 20. The starship adapter adapter 26 can be fixed to the satellite 02 through the stepped holes 10 and corresponding connecting pieces. At least six stepped holes 10 are connected to the satellite 02, and the requirements for form and position accuracy are relatively high. The second weight reduction slot 17 not only plays a role in reducing the weight of the starship adapter adapter 26, but also makes it easier to machine the stepped holes 10 and / or positioning pin holes 25 with higher precision. The positioning pin hole 25 is used to ensure the installation accuracy during subsequent repeated disassembly and assembly. In the embodiment of the present application, the positioning pin hole 25 is machined after the starship adapter adapter and the satellite 02 platform are assembled, debugged, and the connecting pieces are fixed. In the embodiment of the present application, preferably, a plurality of strengthening connecting ribs 11 are designed between each stepped hole 10, between each adapter connection threaded hole 22, and / or between the stepped hole 10 and the adapter connection threaded hole 22. The strengthening connecting ribs 11 have the same thickness, and connect and strengthen the main load-bearing connecting holes, namely the adapter connection threaded holes 22 and the stepped holes 10. Each adapter connection threaded hole 22 and stepped hole 10 corresponds to a plurality of strengthening connecting ribs 11. The strengthening connecting ribs 11 are distributed in the three directions of length, width, and height to ensure that the effective transmission of force can be achieved in all three directions. A plurality of lifting parts 03 are provided on the outer side of the body 04. Each lifting part 03 has a lifting surface, and threaded through holes 15 for lifting are provided on the lifting surface. Each lifting part 03 has at least five strengthening ribs 16 for improving the connection strength of the threaded through holes 15 to improve the reliability of lifting.

[0060] Optionally, the starship adapter adapter 26 has a mirror-symmetrical structure, and the symmetry plane of the starship adapter adapter 26 is perpendicular to the satellite connection surface 24.

[0061] The starship adapter adapter base 26 provided by the present application uses two mutually perpendicular surfaces to connect the satellite 02 and the adapter 06, which is more suitable for launching when the satellite 02 is side-mounted on the carrier bracket; the starship adapter adapter base 26 provided by the present application is installed on the side of the satellite 02 platform, without excessively increasing the height of the satellite 02, which conforms to the design concept of the flat-panel satellite 02. At the same time, the height difference between the star-ship docking surface and each unit of the satellite 02 is reduced, weakening the amplification factor of the launch vibration environment; the starship adapter adapter base 26 provided by the present application has greater stiffness in all directions and has multiple interfaces on the outside, integrating interfaces such as separation switch interfaces, satellite reference prism interfaces, and satellite hoisting interfaces, thereby simplifying the number of docking interfaces of the satellite 02 platform structure; the starship adapter adapter base 26 provided by the present application weakens the impact force transmitted to the satellite 02 when the star and the rocket are separated to a certain extent.

[0062] Another aspect of the present application provides a starship adapter assembly, including an adapter 06, a reference prism 01, a separation switch 05, a driving spring 07, and the starship adapter adapter base 26 provided by the present application. The adapter 06, the reference prism 01, and the separation switch 05 are all fixedly connected to the starship adapter adapter base 26, and the driving spring 07 abuts against the starship adapter adapter base 26.

[0063] The starship adapter assembly provided by the present application adopts the starship adapter adapter base 26 provided by the present application. When in use, the satellite 02 is docked with the rocket through the starship adapter adapter base 26 and the adapter 06. The driving bearing surface 19 and the adapter connection surface 20 are both perpendicular to the vertical direction. It can be connected to the side of the satellite 02 through the satellite connection surface 24, connected to the adapter 06 through the adapter connection surface 20 and the adapter connection screw, and the driving bearing surface 19 is in contact with the driving member to longitudinally send out the satellite 02 when the satellite 02 and the rocket are separated. At this time, the axial direction of the adapter connection screw for connecting the adapter connection surface 20 and the adapter 06 corresponds to the longitudinal vibration environment of the carrier. Since the mechanical environment during the carrier launch process is that the longitudinal vibration is more severe than the lateral vibration environment, and the mechanical property of the adapter connection screw is that the axial bearing tensile and compressive strength is greater than the bearing shear strength, so compared with making the tangential direction of the adapter connection 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 connection screw.

[0064] 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 them; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and 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 seat, characterized in that, It includes a mutually connected body and a drive receiving part. The body includes a satellite connection surface and an adapter connection surface. The drive receiving part includes a drive receiving surface. The adapter connection surface and the drive receiving surface are both perpendicular to the satellite connection surface. The drive receiving surface and the adapter connection surface face the same direction, and the drive receiving surface is used to receive a force perpendicular to the drive receiving surface. The adapter connection surface is used to connect to a rocket through an adapter, and then the satellite is docked with the rocket through this starship adapter adapter seat and the adapter. The body and the drive receiving part are arranged in a first direction, and the first direction is perpendicular to the satellite connection surface. The drive receiving surface and the adapter connection surface are in the same plane, and the drive receiving surface and the adapter connection surface are integrated. The drive receiving part includes a straight segment and a semi-circular segment. In the first direction, the body, the straight segment, and the semi-circular segment are connected in sequence. The arc surface on the semi-circular segment faces away from the body. The starship adapter adapter seat is a mirror-symmetrical structure, and the symmetry plane of the starship adapter adapter seat is perpendicular to the satellite connection surface.

2. The starship adapter adapter seat according to claim 1, characterized in that, An overall satellite reference pin hole is formed on the drive receiving part, and the overall satellite reference pin hole is located at the center of the semi-circular segment.

3. The starship adapter adapter seat according to claim 1 or 2, characterized in that, Adapter connection threaded holes are formed on the adapter connection surface, and a first weight-reducing groove is also formed on the adapter connection surface.

4. The starship adapter adapter seat according to claim 1 or 2, characterized in that A separation switch mounting surface is further formed on the body. The adapter connection surface and the satellite connection surface are both perpendicular to the separation switch mounting surface, and separation switch mounting interfaces are provided on the separation switch mounting surface; and / or, a reference prism mounting surface is further formed on the body. The reference prism mounting surface and the adapter connection surface are two end faces of the body that face away from each other.

5. The starship adapter adapter according to claim 1 or 2, characterized in that, At least two groups of slot hole groups arranged in a second direction are formed on the satellite connection surface. The slot hole group includes a second weight-reducing groove, a positioning pin hole, and three stepped holes; in the slot hole group, the stepped holes are arranged in a third direction, and a second weight-reducing groove is provided between one stepped hole and another stepped hole, and the positioning pin hole is provided between the other stepped hole and the third stepped hole; 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.

6. Starship adapter assembly, characterized in that, It includes an adapter, a reference prism, a separation switch, a drive spring, and the starship adapter adapter seat according to any one of claims 1 to 5. The adapter, the reference prism, and the separation switch are all fixedly connected to the starship adapter adapter seat, and the drive spring abuts against the starship adapter adapter seat.

Images