A satellite and rocket

Abstract

This application discloses a satellite and a rocket, belonging to the technical field of aviation. The satellite provided in this application includes a satellite body and a satellite-rocket connection structure. The satellite-rocket connection structure includes a satellite-rocket docking support and an explosive bolt mounting module. The explosive bolt mounting module is provided with explosive bolt mounting holes for threaded connection with explosive bolts. Multiple first connecting structures are provided on the satellite-rocket docking support at intervals on a first circumference, and multiple second connecting structures are provided on the satellite body at intervals on a second circumference. The number of second connecting structures is greater than the number of first connecting structures. The second circumference and the first circumference are coaxial, and the axis of the explosive bolt mounting holes is offset from the axis of the first circumference.

Description

Technical Field

[0001] This application belongs to the field of aerospace technology, and in particular relates to a satellite and a rocket. Background Technology

[0002] Currently, satellites are generally mounted on adapters in rocket systems, which facilitate the connection between the satellite and the rocket and the transfer of payloads. Due to numerous limitations such as fairing envelope space, satellite structural dimensions, adapter structural form, and launch weight, most satellite launches in China still adopt a single-satellite or dual-satellite launch mode. The adapter structure of single-satellite or dual-satellite arrangements is relatively simple. When designing the structure, only the impact of one or two satellites on the envelope space and adapter structure needs to be considered. There are fewer influencing factors, and the structural space and form can be more flexible and varied, making the design less difficult.

[0003] In the fiercely competitive commercial space industry, fully utilizing envelope and carrying capacity to spread the launch cost of a single satellite and designing ingenious adapter structures suitable for multi-satellite launches is an inevitable trend in future structural design. Multi-satellite adapter structures are complex, with long development cycles, high development costs, and significant difficulties in adapter assembly and satellite installation. Sometimes, to meet installation process requirements, adapter structures must undergo complex structural designs and utilize lightweight, high-strength materials.

[0004] How to adapt the satellite to the confined space of the adapter for installation is a technical problem that those skilled in the art want to solve. Summary of the Invention

[0005] This application aims to at least partially solve the technical problem in related technologies where satellites are difficult to install within the confined space of an adapter. To this end, this application provides a satellite and a rocket.

[0006] In a first aspect, an embodiment of this application provides a satellite, comprising: a satellite body; and a satellite-rocket connection structure, including a satellite-rocket docking support and an explosive bolt mounting module. The explosive bolt mounting module is provided with explosive bolt mounting holes for threaded connection with explosive bolts, and the explosive bolt mounting module is fixedly connected to the satellite-rocket docking support. The satellite-rocket docking support has a plurality of first connecting structures spaced apart on a first circumference; the satellite body has a plurality of second connecting structures spaced apart on a second circumference, the number of second connecting structures being greater than the number of first connecting structures, and the second circumference and the first circumference are coaxial; the first connecting structures can be connected to the second connecting structures after rotating around the axis of the first circumference at different angles; the axis of the explosive bolt mounting hole is offset from the axis of the first circumference.

[0007] Secondly, an embodiment of this application provides a rocket, including an explosive bolt, a rocket body, an adapter, and a satellite provided in the first aspect of this application. The rocket body is connected to the adapter, one end of the explosive bolt is connected to the adapter, and the other end is connected to the explosive bolt mounting hole of the satellite.

[0008] This application has at least the following beneficial effects:

[0009] The satellite provided in this application includes a satellite body and a satellite-rocket connection structure. The satellite-rocket connection structure includes a satellite-rocket docking support and an explosive bolt mounting module. The explosive bolt mounting module has explosive bolt mounting holes for threaded connection with explosive bolts. The satellite-rocket docking support has multiple first connecting structures spaced apart on a first circumference, and the satellite body has multiple second connecting structures spaced apart on a second circumference. The number of second connecting structures is greater than the number of first connecting structures, and the second circumference and the first circumference are coaxial. The axis of the explosive bolt mounting holes is offset from the axis of the first circumference.

[0010] With this design, the first connecting structure can connect with the second connecting structure after rotating around the axis of the first circumference at different angles, thus fixing the satellite-rocket connection structure to the satellite body. When the satellite-rocket docking support rotates around the axis of the first circumference at different angles and connects with the satellite body, the position of the satellite-rocket docking support does not change, but the relative position of the explosive bolt mounting holes to the satellite body changes. This allows the position of the explosive bolt mounting holes to be adaptively adjusted according to the position of the explosive bolts on the adapter, making satellite installation easier and eliminating, to some extent, installation errors of the explosive bolts and machining errors of the adapter.

[0011] Furthermore, since the relative position of the explosive bolt mounting holes and the satellite body can be changed, the relative position of the satellite body on the adapter will also differ depending on the position of the explosive bolt mounting holes and the connection hook via the explosive bolts. Therefore, by adjusting the position of the explosive bolt mounting holes, the position of the satellite body on the adapter can be adjusted to a certain extent, thus preventing interference between the satellite body and other satellite bodies, and to a certain extent, preventing interference between the satellite body and the adapter, allowing the satellite to be installed on adapters with limited installation space. Attached Figure Description

[0012] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1A schematic diagram of the satellite structure from a first-view perspective is shown in one or more embodiments of this application.

[0014] Figure 2 A schematic diagram of the satellite structure from a second perspective is shown in one or more embodiments of this application.

[0015] Figure 3 A schematic diagram of the satellite-rocket connection structure in one or more embodiments of this application is shown.

[0016] Figure 4 A schematic diagram of the satellite-rocket docking support in one or more embodiments of this application is shown.

[0017] Figure 5 It shows Figure 3 Top view.

[0018] Figure 6 It shows Figure 5 A sectional view along AA.

[0019] Reference numerals: 100, Satellite body; 100a, Second circumference; 110, Second connecting structure; 200, Satellite-rocket connecting structure; 210, Satellite-rocket docking support; 210a, First circumference; 210b, First mounting cavity; 210c, Clearance hole; 210d, Positioning hole; 2101, Second sidewall; 2102, Second skirt; 211, First connecting structure; 220, Explosive bolt mounting module; 220a, Explosive bolt mounting hole; 221, Protective cover; 2211, First sidewall; 2212, First skirt; 221a, Second mounting cavity; 222, Connector; 2221, Connector body; 2222, Limiting flange; 223, Buffer; 230, Second bolt; 240, Elastic washer; 250, Limiting plate; 260, Washer; 400, First bolt. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0021] It should be noted that all directional indications in the embodiments of the present invention are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0022] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0023] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0024] The adapter is a crucial component connecting the rocket body and the satellite. The adapter is fixedly attached to the rocket body, and the satellite is attached to the adapter. The satellite is equipped with a satellite-rocket connection structure, which connects to one end of an explosive bolt, and the other end of the bolt connects to the adapter. When the explosive bolt detonates and breaks, the ejection mechanism activates, and the satellite, along with the satellite-rocket connection structure, is ejected, separating from the adapter.

[0025] In related technologies, for multi-satellite launch operations, multiple satellites are installed on the adapter. The multi-satellite adapter has a complex structure, long development cycle, high development cost, and great difficulty in satellite installation.

[0026] The limited installation space for each satellite on a multi-satellite adapter, coupled with issues such as poor adapter design, manufacturing errors in the adapter itself, and errors in satellite manufacturing, can make it difficult or impossible to install satellites on the adapter. This is especially true for adapters with confined installation spaces, where interference between satellites and the adapter, as well as between satellites themselves, is a common problem that those skilled in the art seek to solve.

[0027] Therefore, in related technologies, satellites are difficult to install in confined spaces. This application provides a satellite and rocket that can at least partially solve the technical problem of satellites being difficult to install in confined spaces.

[0028] This application is described below with reference to the accompanying drawings and specific embodiments:

[0029] like Figure 1 , Figure 2 As shown, this application embodiment provides a satellite in which the axis of the explosive bolt mounting hole 220a on the satellite is misaligned with the axis of the first circumference 210a on the satellite-rocket docking support 210. The satellite-rocket docking support 210 can be connected to the satellite body 100 by rotating around the axis of the first circumference 210a at different angles. Due to the misaligned design, the relative position between the explosive bolt mounting hole 220a and the satellite body 100 can be changed, allowing the explosive bolt mounting hole 220a to be adaptively adjusted according to specific circumstances, enabling the satellite of this application to be installed on an adapter with limited installation space.

[0030] The satellite provided in this embodiment includes a satellite body 100 and a satellite-rocket connection structure 200. The satellite-rocket connection structure 200 includes a satellite-rocket docking support 210 and an explosive bolt mounting module 220. The explosive bolt mounting module 220 is provided with explosive bolt mounting holes 220a for threaded connection with explosive bolts. The explosive bolt mounting module 220 is fixedly connected to the satellite-rocket docking support 210. The satellite-rocket docking support 210 has multiple first connecting structures 211 spaced apart on a first circumference 210a. The satellite body 100 has multiple second connecting structures 110 spaced apart on a second circumference 100a. The number of second connecting structures 110 is greater than the number of first connecting structures 211. The second circumference 100a and the first circumference 210a are coaxial. The axis of the explosive bolt mounting hole 220a is offset from the axis of the first circumference 210a. With this design, the first connecting structure 211 can be connected to the second connecting structure 110 after rotating around the axis of the first circumference 210a at different angles.

[0031] In other words, after the satellite-rocket docking support 210 rotates around the first circumference 210a at different preset angles, the first connecting structure 211 can cooperate with and connect with the second connecting structure 110 on the satellite body 100, so that the satellite body 100 and the satellite-rocket docking structure 200 are fixedly connected.

[0032] Because the axis of the explosive bolt mounting hole 220a is misaligned with the axis of the first circumference 210a (meaning they are not coaxial), when the satellite docking support 210 rotates around the first circumference 210a by different preset angles, such as 30°, 60°, and 90°, and is connected to the satellite body 100, the relative position of the explosive bolt mounting hole 220a and the satellite body 100 will vary depending on the rotation angle of the satellite docking support 210. This allows the relative position of the explosive bolt mounting hole 220a and the satellite body 100 to change without moving the relative position of the satellite docking support 210 and the satellite body 100. This design allows the position of the explosive bolt mounting hole 220a to be adaptively adjusted according to the installation position of the explosive bolts on the adapter, which can, to some extent, eliminate installation errors of the explosive bolts or machining errors of the adapter, facilitating satellite installation.

[0033] More importantly, when the explosive bolt mounting hole 220a is in different positions, the relative position between the satellite and the adapter after the satellite is installed on the adapter is also different. Therefore, the position of the satellite relative to the adapter can be adjusted by adjusting the position of the explosive bolt mounting hole 220a, which enables the satellite of this application to avoid interference with the adapter or other satellites to a certain extent, and enables the satellite provided by this application to be installed smoothly in a confined space.

[0034] It should also be noted that a satellite is typically connected to multiple explosive bolts, therefore, multiple satellite-rocket connection structures 200 are usually installed on the satellite. By adjusting the mounting holes 220a of each explosive bolt simultaneously or individually, multiple different relative positions can be achieved between the same satellite and the adapter. Furthermore, in multi-satellite launch missions, multiple satellites may be mounted on a single adapter. If the satellite provided in this application is used in a multi-satellite launch mission, the relative positions of these satellites and the adapter, as well as the relative positions among these satellites, can be adjusted, avoiding interference between satellites and between satellites and the adapter.

[0035] The size and structure of the satellite body 100 are related to the specific launch mission and are not limited in this application.

[0036] In some launch missions, two explosive bolts are installed between the adapter and the satellite, while in others, four explosive bolts are used. The number of satellite-rocket connection structures 200 on the satellite is related to the number of explosive bolts. Therefore, the number of satellite-rocket connection structures 200 is not limited in this application; users can make adaptive designs based on actual conditions.

[0037] The first connecting structure 211 and the second connecting structure 110 can take various forms, as illustrated below:

[0038] In some embodiments, the first connecting structure 211 is a pin, and the second connecting structure 110 is a pin hole. A plunger is installed in the pin hole, with the plunger head located within the pin hole. A plunger positioning hole adapted to the plunger head is formed on the peripheral wall of the pin. The pin is inserted into the pin hole, and the plunger head pops out and engages in the plunger positioning hole, thereby connecting the satellite body 100 and the satellite-rocket connection structure 200. Pulling the pin outward forcefully causes the plunger head to retract, disengaging the pin from the pin hole and thus disconnecting the satellite body 100 from the satellite-rocket connection structure 200.

[0039] In some embodiments, the first connecting structure 211 and the second connecting structure 110 are connected by a snap-fit ​​mechanism. The first connecting structure 211 and the second connecting structure 110 are male and female snap-fits to each other. The male snap-fit ​​is located inside the female snap-fit, which connects the satellite body 100 and the satellite-rocket connection structure 200. The male snap-fit ​​is located outside the female snap-fit, which disconnects the satellite body 100 and the satellite-rocket connection structure 200.

[0040] In some embodiments, such as Figure 2 As shown, to ensure the reliability of the connection between the satellite body 100 and the satellite-rocket connection structure 200, the first connection structure 211 has a first bolt connection hole, and the second connection structure 110 has a second bolt connection hole. The diameters of the first circumference 210a and the second circumference 100a are the same. The satellite also includes a number of first bolts 400 that are the same as the number of first bolt connection holes. Multiple first bolts 400 are respectively installed in the corresponding first bolt mounting holes and second bolt mounting holes to fix the satellite-rocket docking support 210 and the connection structure.

[0041] With this design, when the first bolt connection hole and the second bolt connection hole are aligned, the first bolt 400 extends into the first bolt mounting hole and the second bolt mounting hole, and the star-rocket docking support 210 and the satellite body 100 are connected by threads.

[0042] In some embodiments, three first bolt connection holes are provided, evenly distributed on the first circumference 210a, with a central angle of 120° between adjacent first bolt connection holes. Nine second bolt connection holes are provided, evenly distributed on the first circumference 210a, with a central angle of 40° between adjacent second bolt connection holes. The axes of both the first and second bolt connection holes are parallel to the axis of the first circumference 210a, with both axes located on the first circumference 210a. The second bolt connection holes are internally threaded holes, while the first bolt connection holes are through holes and are smooth holes. Three first bolts 400 are provided, each inserted into a corresponding first bolt connection hole and threadedly connected to a second bolt connection hole. With this configuration, the satellite docking support 210 can be connected to the satellite body 100 via the first bolt 400 every 40° rotation around the axis of the first circumference 210a, and the satellite docking support 210 and the satellite body 100 have 9 different relative positions.

[0043] The number of first bolt connection holes and second bolt connection holes is not limited in this application.

[0044] The connection between the satellite-rocket docking support 210 and the satellite body 100 via the first bolt 400, the first bolt connection hole, and the second bolt connection hole helps to ensure the connection strength between the satellite-rocket docking support 210 and the satellite body 100, so that the satellite-rocket docking support 210 is firmly installed on the satellite body 100, preventing the satellite-rocket docking support 210 and the satellite body 100 from separating due to vibration or other reasons, and ensuring the smooth launch of the satellite.

[0045] In some embodiments, such as Figure 3 , Figure 4 and Figure 5 As shown, to protect the explosive bolt mounting module 220, the satellite-rocket docking support 210 has a first mounting cavity 210b, within which the explosive bolt mounting module 220 is located. The side wall of the satellite-rocket docking support 210 away from the satellite body 100 has a clearance hole 210c for avoiding the explosive bolt. The clearance hole 210c connects to the first mounting cavity 210b, and is positioned opposite to the explosive bolt mounting hole 220a. With this design, the end of the explosive bolt connected to the satellite passes through the clearance hole 210c and is threaded into the explosive bolt mounting hole 220a. Since the explosive bolt mounting module 220 is located within the first mounting cavity 210b, the satellite-rocket docking support 210 not only connects the explosive bolt mounting module 220 to the satellite but also provides protection for the explosive bolt mounting module 220 to a certain extent, preventing damage to the satellite from impacting other components during transportation and installation.

[0046] Precision optical equipment and electronic components on satellites are highly sensitive to impacts; the powerful impact of exploding explosive bolts can easily damage these devices. For example... Figure 6 As shown, in some embodiments, in order to reduce the impact force on the satellite when the explosive bolt explodes, the explosive bolt mounting module 220 includes a protective cover 221, a connector 222, and a buffer 223. The protective cover 221 is provided with a second mounting cavity 221a for mounting the connector 222 and the buffer 223. The connector 222 and the buffer 223 are located in the second mounting cavity 221a. The explosive bolt mounting hole 220a is provided on the connector 222. Along the axial direction of the explosive bolt mounting hole 220a, the two ends of the buffer 223 abut against the protective cover 221 and the connector 222, respectively. The buffer 223 is located on the side of the connector 222 away from the explosive bolt. The protective cover 221 is connected to the satellite-rocket docking support 210.

[0047] The buffer 223 absorbs or dissipates energy through elastic and plastic deformation, prolonging the impact time of the exploding bolt head to achieve a better buffering effect, significantly reducing impact and vibration, and protecting surrounding components from impact forces as much as possible. The impact force generated by the fracture of the exploding bolt is transmitted through the connector 222, and then through the connector 222 to the buffer 223. The buffer 223 absorbs or dissipates most of the impact force through force deformation, and the remaining impact force is transmitted through the protective cover 221, and then to the satellite body 100. In some experiments, after the buffer 223 was installed, the impact load generated by the exploding bolt was reduced from over 5000g to below 1000g. The installation of the buffer 223 greatly reduces the impact force transmitted to the satellite body 100, and to a certain extent avoids damage to the satellite's precision optical equipment or electronic components from large impacts. The material of the buffer 223 is diverse, and it can be a rubber buffer, a metal buffer (such as a metal spring), etc. The number of buffers 223 can be one or more. The protective cover 221 serves as the foundation for the installation of the connector 222 and the buffer 223, providing support and positioning for them. The protective cover 221 abuts against the buffer 223, allowing the buffer 223 to function smoothly. The protective cover 221 also prevents components from flying out of the first mounting cavity 210b, especially at the moment the explosive bolt breaks.

[0048] In some embodiments, to facilitate the installation of the rocket docking support 210 and the explosive bolt mounting module 220, the protective cover 221 includes a first sidewall 2211 and a first skirt 2212, with the first sidewall 2211 forming a second mounting cavity 221a; the rocket docking support 210 includes a second sidewall 2101 and a second skirt 2102, with the second sidewall 2101 forming a first mounting cavity 210b, and a clearance hole 210c disposed on the second sidewall 2101; the first skirt 2212 of the protective cover 221 is fixedly connected to the second sidewall 2101 of the rocket docking support 210 by a plurality of second bolts 230; the second connecting structure (110) is disposed on the second skirt (2102). Both the protective cover 221 and the rocket docking support 210 include skirts and sidewalls. The sidewall forming the mounting cavity means that the sidewall encloses and forms the mounting cavity. The design of the skirt and sidewalls allows the protective cover 221 and the rocket docking support 210 to be integrally formed by processes such as stamping and casting, which is convenient for processing. After setting the first skirt 2212, mounting holes can be made on the first skirt 2212, and the protective cover 221 and the satellite docking support 210 can be connected by bolts and other connectors; after setting the second skirt 2102, the second connecting structure 110 can be set on the second skirt 2102 to realize the connection between the satellite docking support 210 and the satellite body 100, making the installation of the satellite docking support 210 and the explosive bolt mounting module 220 more convenient.

[0049] In some embodiments, to further reduce the impact force when the explosive bolt breaks, the explosive bolt mounting module 220 also includes an elastic washer 240. The elastic washer 240 is sleeved on the threaded part of the second bolt 230 and located between the head of the second bolt 230 and the first skirt 2212 of the protective cover 221. With this design, the impact force of the explosive bolt is transmitted to the protective cover 221 and then to the satellite-rocket docking support 210 through the second bolt 230. The design of the elastic washer 240 effectively prevents the second bolt 230 from loosening due to vibration. On the other hand, it can further absorb or dissipate the impact force of the explosive bolt through elastic deformation and plastic deformation. The impact force of the explosive bolt is further reduced, thus greatly avoiding damage to the precision optical equipment or electronic components on the satellite from large impacts. The elastic washer 240 can be made of various materials, such as rubber.

[0050] In some embodiments, the explosion bolt mounting module 220 further includes a washer 260, which is sleeved on the threaded part of the second bolt 230 and located between the head of the second bolt 230 and the elastic washer 240. The washer 260 prevents the head of the second bolt 230 from directly contacting the spring washer 260, preventing damage to the elastic washer 240 after the second bolt 230 is tightened, and ensuring that the elastic washer 240 can perform its cushioning function. Simultaneously, the washer 260 ensures that the force exerted by the head of the second bolt 230 is evenly transmitted to the elastic washer 240, allowing the elastic washer 240 to better perform its cushioning function. The washer 260 is generally a rigid washer made of metal.

[0051] In some embodiments, to facilitate the installation of the protective cover 221 within the first mounting cavity 210b of the star-rocket docking support 210, the cross-section of the first mounting cavity 210b matches the first skirt 2212 of the protective cover 221 along the axial direction perpendicular to the clearance hole 210c. That is, the shape of the cross-section of the first mounting cavity 210b is the same as the shape of the edge of the first skirt 2212, and the size of the cross-section of the first mounting cavity 210b is slightly smaller than the size of the edge of the first skirt 2212, thus limiting the protective cover 221 within the first mounting cavity 210b. Simultaneously, the first skirt 2212 of the protective cover 221 and the star-rocket docking support 210 are respectively provided with opposing first and second positioning structures, which are connected to position the protective cover 221. By providing the first and second positioning structures, the limiting of the protective cover 221 is strengthened, ensuring accurate alignment of the screw mounting holes on the first skirt 2212 of the protective cover 221 and the bolt mounting holes on the second sidewall 2101 of the star-rocket docking support, facilitating the installation of the second bolt 230. In some embodiments, the second positioning structure on the star-rocket docking support 210 is a positioning pin, and the first positioning structure on the first skirt 2212 of the protective cover 221 is a positioning pin hole.

[0052] In some embodiments, in order to facilitate the connection between the star-rocket docking support 210 and the adapter, a positioning hole 210d for positioning with the adapter is provided on the second side wall 2101 of the star-rocket docking support 210.

[0053] In some embodiments, in order for the connector 222 to move within the second mounting cavity 221a and along the explosive bolt mounting hole 220a when the explosive bolt breaks, the connector 222 includes a connector body 2221 and a limiting flange 2222 disposed circumferentially on the connector body 2221. A buffer 223 is sleeved on the connector body 2221 and contacts the limiting flange 2222. The explosive bolt mounting hole 220a is disposed on the connector body 2221, and the limiting flange 2222 is slidably connected to the protective cover 221 along the axial direction of the explosive bolt mounting hole 220a. In these embodiments, the buffer member 223 has a hole through which it is fitted onto the connector 222. The limiting flange 2222 on the connector 222 limits the buffer member 223. The impact force generated by the explosive bolt is transmitted to the buffer member 223 through the limiting flange 2222. The buffer member 223 and the protective cover 221 are slidably connected along the axial direction of the explosive bolt mounting hole 220a to ensure that when the explosive bolt breaks, the connector 222 can move along the explosive bolt mounting hole 220a in the second mounting cavity 221a to press the buffer member 223, so that the impact force applied to the connector 222 by the explosive bolt is evenly transmitted to the buffer member 223, resulting in uniform deformation of all parts of the buffer member 223 and achieving a better buffering effect.

[0054] In some embodiments, to improve the stability of the explosive bolt mounting module 220 structure, the explosive bolt mounting module 220 further includes a limiting plate 250. The limiting plate 250 is sleeved outside the connector body 2221 and is located between the protective cover 221 and the star-rocket docking support 210. A limiting flange 2222 is located between the buffer 223 and the limiting plate 250. In these embodiments, a limiting hole is formed on the limiting plate 250, and one end of the connector body 2221 near the limiting plate 250 extends through the limiting hole, so that the limiting plate 250 is sleeved on the connector body 2221. The limiting plate 250 is located between the protective cover 221 and the star-rocket docking support 210. When the protective cover 221 and the star-rocket docking support 210 are connected, the limiting plate 250 is pressed tightly by the protective cover 221 and the star-rocket docking support 210. The limiting plate 250 is designed to limit the movement of the connector 222. After the limiting plate 250 is fitted onto the connector body 2221, the limiting flange 2222 is located between the buffer 223 and the limiting plate 250. This means the size of the limiting flange 2222 is larger than the size of the limiting hole, preventing the limiting flange 2222 from passing through the limiting hole. With this design, the connector 222 will not detach from the second mounting cavity 221a under the action of the limiting plate 250, improving the stability of the explosive bolt mounting module 220 and ensuring its smooth operation when the satellite and adapter are separated.

[0055] Based on the same inventive concept, this application also provides a rocket, including an explosive bolt, a rocket body, an adapter, and a satellite provided in the first aspect of this application. The rocket body is connected to the adapter, one end of the explosive bolt is connected to the adapter, and the other end is connected to the explosive bolt mounting hole 220a of the satellite.

[0056] The connection between the rocket body and the adapter can be either detachable or non-detachable. The structure of the adapter connected to the explosive bolt, and the specific connection method between the explosive bolt and the adapter, are known to those skilled in the art and will not be described in detail here. Typically, the adapter is also equipped with a mechanism that can eject the satellite, such as a spring separation mechanism, etc., and these structures are also known to those skilled in the art.

[0057] Since the rocket uses the satellite provided in the first aspect of this application, it naturally possesses all the beneficial effects of the satellite in the first aspect of this application, which will not be elaborated here.

[0058] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0059] Furthermore, the technical solutions of the various embodiments can be combined with each other, but only if they are based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0060] Although embodiments of this application have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the claims and their equivalents.

Claims

1. A satellite, characterized by, include: Satellite body (100); The star-rocket connection structure (200) includes a star-rocket docking support (210) and an explosive bolt mounting module (220). The explosive bolt mounting module (220) is provided with an explosive bolt mounting hole (220a) for threaded connection with an explosive bolt. The explosive bolt mounting module (220) is fixedly connected to the star-rocket docking support (210). The satellite docking support (210) is provided with a plurality of first connecting structures (211) spaced apart on a first circumference (210a); the satellite body (100) is provided with a plurality of second connecting structures (110) spaced apart on a second circumference (100a), the number of second connecting structures (110) being greater than the number of first connecting structures (211), and the second circumference (100a) and the first circumference (210a) being coaxial; the first connecting structures (211) can be connected to the second connecting structures (110) after rotating around the axis of the first circumference (210a) at different angles; The axis of the explosive bolt mounting hole (220a) is offset from the axis of the first circumference (210a); The star-rocket docking support (210) is provided with a first mounting cavity (210b), and the explosive bolt mounting module (220) is located in the first mounting cavity (210b); The satellite docking support (210) is provided with a clearance hole (210c) on the side wall away from the satellite body (100) for avoiding explosive bolts. The clearance hole (210c) is connected to the first mounting cavity (210b), and the clearance hole (210c) is arranged opposite to the explosive bolt mounting hole (220a).

2. The satellite according to claim 1, characterized in that, The first connecting structure (211) is a first bolt connection hole, and the second connecting structure (110) is a second bolt connection hole. The diameters of the first circumference (210a) and the second circumference (100a) are the same. The satellite also includes a number of first bolts (400) that are the same as the number of first bolt connection holes. Multiple first bolts (400) are respectively installed in the corresponding first bolt connection holes and second bolt mounting holes to fix the satellite docking support (210) and the satellite body (100).

3. The satellite according to claim 1, characterized in that, The explosive bolt mounting module (220) includes: a protective cover (221), a connector (222), and a buffer (223). The protective cover (221) is provided with a second mounting cavity (221a) for mounting the connector (222) and the buffer (223). The connector (222) and the buffer (223) are located in the second mounting cavity (221a). The explosive bolt mounting hole (220a) is provided on the connector (222). Along the axial direction of the explosive bolt mounting hole (220a), the two ends of the buffer (223) abut against the protective cover (221) and the connector (222) respectively. The buffer (223) is located on the side of the connector (222) away from the explosive bolt. The protective cover (221) is connected to the star-rocket docking support (210).

4. The satellite according to claim 3, characterized in that, The protective cover (221) includes a first sidewall (2211) and a first skirt (2212), wherein the first sidewall (2211) forms the second mounting cavity (221a); The star-rocket docking support (210) includes a second sidewall (2101) and a second skirt (2102), the second sidewall (2101) forms the first mounting cavity (210b), and the clearance hole (210c) is provided in the second sidewall (2101). The first skirt (2212) of the protective cover (221) is fixedly connected to the second side wall (2101) of the star-rocket docking support (210) by a plurality of second bolts (230); the second connection structure (110) is provided on the second skirt (2102).

5. The satellite according to claim 4, characterized in that, The explosive bolt mounting module (220) also includes an elastic washer (240), which is sleeved on the thread of the second bolt (230) and located between the head of the second bolt (230) and the first skirt (2212) of the protective cover (221).

6. The satellite according to claim 4, characterized in that, The second sidewall (2101) of the star-rocket docking support (210) is provided with a positioning hole (210d) for positioning with the adapter.

7. The connection structure according to claim 3, characterized in that, The connector (222) includes a connector body (2221) and a limiting flange (2222) disposed circumferentially on the connector body (2221). The buffer (223) is sleeved on the connector body (2221) and contacts the limiting flange (2222). The explosive bolt mounting hole (220a) is disposed on the connector body (2221). The limiting flange (2222) is slidably connected to the protective cover (221) along the axial direction of the explosive bolt mounting hole (220a).

8. The connection structure according to claim 7, characterized in that, The explosive bolt installation module (220) also includes a limiting plate (250), which is sleeved on the outside of the connector body (2221). The limiting plate (250) is located between the protective cover (221) and the star-rocket docking support (210). The limiting flange (2222) is located between the buffer (223) and the limiting plate (250).

9. A rocket, characterized in that, The system includes an explosive bolt, a rocket body, an adapter, and a satellite according to any one of claims 1-8, wherein the rocket body is connected to the adapter, one end of the explosive bolt is connected to the adapter, and the other end is connected to the explosive bolt mounting hole (220a) of the satellite.

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