Arrayed multi-satellite launch vehicle separation device and satellite launch vehicle locking and separation method

Abstract

The application relates to the field of aerospace technology, in particular to an array type multi-satellite and rocket separation device, which comprises a satellite, a locking and separating unit, a connecting rod mechanism, a pressing unit, a rotary pressure regulating unit and a satellite and rocket docking platform; a plurality of rotary pressure regulating units are fixed to the satellite and rocket docking platform, and the rotary pressure regulating units are arranged in two rows; the lower ends of one connecting rod mechanism and another connecting rod mechanism are hinged to one row of rotary pressure regulating units and another row of rotary pressure regulating units respectively; a plurality of satellites are stacked on the satellite and rocket docking platform; a plurality of locking and separating units connect the two connecting rod mechanisms together to form an integral frame which wraps the satellites; a plurality of pressing units are connected to the connecting rod mechanisms, and the pressing units can be adjusted up and down so that the lower ends of the pressing units are pressed against the upper surfaces of the uppermost layer of satellites. The application can reduce the satellite and rocket connecting interface, reduce the design difficulty, improve the space utilization, increase the number of carried satellites, and reduce space garbage.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to an array-type multi-satellite separation device and a method for locking and separating the satellite and rocket. Background Technology

[0002] Satellites are launched into space via launch vehicles. The launch vehicle delivers the satellite to its designated orbit, completing the separation of the satellite and the rocket, thus achieving a successful launch. With the continuous development of launch vehicle technology, multi-satellite launches have become routine, and the technology itself is highly mature. Meanwhile, the Starlink constellation has a huge demand for satellites, making the number of satellites launched by launch vehicles crucial and also a way to reduce launch vehicle costs.

[0003] Multiple satellite launch involves launching multiple satellites from a single rocket. Each satellite undergoes a separation process from the rocket. Each satellite is equipped with a separation mechanism. During launch, the satellite is secured to the multi-satellite distributor on the launch vehicle via the separation mechanism. During separation, the separation mechanism unlocks, providing a thrust to the satellite, which then leaves the multi-satellite distributor and enters its predetermined orbit, completing the separation process.

[0004] However, satellites at present come in all shapes and sizes, and their satellite-rocket connection interfaces are also different. Satellites launched in multiple launches have independent satellite-rocket connection interfaces. The more types of satellites launched, the more types and complex the satellite-rocket connection interfaces become. The satellite-rocket connection and separation sequence also becomes more complex, which increases the difficulty of the launch vehicle satellite-rocket separation design, increases separation cost, and reduces separation reliability.

[0005] Furthermore, conventional satellite-rocket connections involve mounting satellites on a multi-satellite distributor, which itself occupies space. In addition, the different shapes of satellites can significantly impact satellite layout, leading to reduced space utilization and limiting the number of satellites that a launch vehicle can carry.

[0006] In addition, each satellite has a separately designed satellite-rocket connection interface structure. The function of this interface structure for the satellite is solely to connect with the separation mechanism and increase the connection strength. However, the more satellites launched, the more satellite-rocket connection interfaces and separation mechanisms are required, leading to an increase in the satellite's design weight, reducing the weight of the launch vehicle's payload, and also reducing launch efficiency.

[0007] In addition, the global satellite launch missions are numerous, with tens of thousands of satellites already in orbit. This has also generated a large amount of space debris, thus polluting the space environment. At present, the protection of the space environment has begun to receive attention.

[0008] Therefore, how to reduce the number of satellite-rocket connection interfaces, lower the design complexity, improve space utilization, increase the number of satellites carried, and reduce space debris are technical problems that urgently need to be solved by those skilled in the art. Summary of the Invention

[0009] This application provides an array-type multi-satellite launcher separation device and a satellite-launcher locking and separation method, which reduces the number of satellite-launcher connection interfaces, lowers the design difficulty, improves space utilization, increases the number of satellites carried, and reduces space debris.

[0010] To solve the above-mentioned technical problems, this application provides the following technical solution: An array-type multi-satellite launcher separation device includes: multiple satellites, multiple locking and separation units, two linkage mechanisms, multiple clamping units, multiple rotary pressure regulating units, and a satellite-launcher docking platform; the multiple rotary pressure regulating units are fixed to the satellite-launcher docking platform and arranged in two rows; the lower end of one linkage mechanism is hinged to one row of rotary pressure regulating units, and the lower end of another linkage mechanism is hinged to the other row of rotary pressure regulating units; multiple satellites are stacked on the satellite-launcher docking platform, and the multiple locking and separation units connect the two linkage mechanisms together to form an integral frame that encloses the satellites; multiple clamping units are connected to the linkage mechanisms, and the clamping units can be adjusted up and down so that their lower end faces press against the upper surface of the uppermost satellite.

[0011] In the array-type multi-star rocket separation device described above, preferably, the locking separation unit includes: an explosive bolt and a reverse-thrust separation spring mechanism, wherein the explosive bolt connects two linkage mechanisms together, and the reverse-thrust separation spring mechanism is pressed between the two linkage mechanisms.

[0012] As described above, the array-type multi-star rocket separation device preferably includes a linkage mechanism comprising: a horizontal tie rod A, a horizontal connecting rod assembly, a straight connecting rod, a horizontal tie rod B, and an oblique connecting rod assembly; one end of the horizontal tie rod A is fixedly connected to one end of the horizontal connecting rod assembly, and the horizontal tie rod A and the horizontal connecting rod assembly are at a certain angle; the other end of the horizontal tie rod A is connected to a locking separation unit; both ends of the horizontal connecting rod assembly are also fixedly connected to the upper end of an oblique connecting rod assembly, the lower end of each oblique connecting rod assembly is hinged to a rotary pressure adjusting unit, and the oblique connecting rod assembly is inclined inward from bottom to top; the middle of the horizontal connecting rod assembly is connected to one or more pressing units, the upper end of each straight connecting rod is connected to a pressing unit, the lower end of each straight connecting rod is hinged to a rotary pressure adjusting unit, and the straight connecting rod extends vertically from bottom to top; a pressing unit is also connected to the horizontal connecting rod assembly near both ends; the middle of the oblique connecting rod assembly is fixedly connected to one end of one or more horizontal tie rods B, and the other end of the horizontal tie rod B is connected to a locking separation unit.

[0013] In the array-type multi-star rocket separation device described above, preferably, the linkage mechanism further includes: multiple adapters A and multiple adapters B; one end of the horizontal tie rod A, one end of the horizontal connecting rod assembly, and the upper end of the diagonal connecting rod assembly are fixedly connected via adapter A; one end of the horizontal tie rod B and the middle of the diagonal connecting rod assembly are fixedly connected via adapter B.

[0014] In the array-type multi-star rocket separation device described above, preferably, the cross link assembly includes: cross link A, cross link B, and adapter C; adapter C is installed at both ends of cross link B, and adapter C is connected to cross link A.

[0015] In the array-type multi-star arrow separation device described above, preferably, a limiting device is provided at the position where the clamping unit is installed on the cross link A to restrict the movement of the clamping unit.

[0016] In the array-type multi-star rocket separation device described above, preferably, the clamping unit includes: clamping block A unit and clamping block B unit; clamping block A unit is connected to the horizontal connecting rod assembly near both ends; clamping block B unit is connected to the middle position of the horizontal connecting rod assembly and is connected to the upper end of the straight connecting rod.

[0017] As described above, in the array-type multi-star-rocket separation device, preferably, the rotary pressure regulating unit includes: a recovery unit, a rotary shaft assembly, and a mounting base; the lower end of the mounting base is fixed to the star-rocket docking platform, the upper end of the mounting base has a downward-opening mounting groove that extends through both the inner and outer sides, and the mounting base has mounting holes on the left and right sides, the extension direction of the mounting holes being perpendicular to the extension direction of the mounting groove; the rotary shaft assembly is inserted into the mounting hole and hinged to the mounting base, and the lower end of the linkage mechanism is inserted into the mounting groove and connected to the portion of the rotary shaft assembly located within the mounting groove; the recovery unit is located at the upper end of the mounting base near the outer side, covering the mounting groove, and is located outside the linkage mechanism; the recovery unit is a one-way mechanism, during the rotational opening process of the linkage mechanism located inside the recovery unit, the recovery unit moves outward to open, and after the linkage mechanism rotates to the outside of the recovery unit, the recovery unit returns to its original position, restricting the return of the linkage mechanism.

[0018] In the array-type multi-star rocket separation device described above, it is preferable that the length of the linkage mechanism can be adjusted before the lower end of the linkage mechanism is fixed to the rotary shaft assembly.

[0019] In the array-type multi-satellite launcher separation device described above, preferably, the lower surface of the satellite has a downwardly convex shear pin, the upper surface of the satellite has a downwardly concave shear hole, and the upper surface of the satellite-launcher docking platform has a downwardly concave shear hole. When stacking satellites, the shear pin of the satellite located at the bottom layer is inserted into the shear hole of the satellite-launcher docking platform, and the shear pin of the satellite located at the top layer is inserted into the shear hole of the satellite located at the bottom layer.

[0020] A satellite-rocket locking method, applied to any of the above-described array-type multi-satellite-rocket separation devices, includes the following steps: Step S1110: Connecting the linkage mechanism to the rotary pressure regulating unit, wherein the length of the linkage mechanism is not fixed; Step S1120: Stacking multiple satellites onto the satellite-rocket docking platform; Step S1130: Rotating the linkage mechanisms on both sides until the lower end face of the pressing unit is in contact with the satellite docking surface and then stopping; Step S1140: Connecting the linkage mechanisms on both sides together with multiple locking and separation units to form an integral frame; Step S1150: Shortening the length of the linkage mechanism until the pressing unit presses the satellite, fixing the length of the linkage mechanism, and completing the locking process.

[0021] A satellite-rocket separation method, applied to any of the above-described array-type multi-satellite-rocket separation devices, includes the following steps: Step S1210, all locking separation units are unlocked, and the clamping force on the satellite disappears; Step S1220, the linkage mechanism rotates around the rotary pressure regulating unit, causing the linkage mechanism to open; Step S1230, multiple satellites are released from the satellite-rocket docking platform, completing the satellite-rocket separation.

[0022] Compared to the aforementioned background technologies, the array-type multi-satellite launcher separation device in this application features satellites with standardized external interfaces. These interfaces do not require independent structural design; the satellite's own skeletal structure suffices. The launcher docking platform also features corresponding interfaces, enabling the satellites to be arranged in an array. This design is simple, highly operable, low-cost, and highly reliable. The array arrangement allows for close-fitting placement of satellites without gaps, maximizing space utilization and significantly improving space efficiency. The array arrangement offers high flexibility in terms of satellite quantity and width variations. The array-type multi-satellite launcher separation device is easy to adjust. The locking separation unit provides rapid separation, quickly opening to complete the launcher-satellite separation. Furthermore, the array-type multi-satellite launcher separation device includes a rod assembly recovery function, allowing the rods to leave space together with the upper stage after separation, thus avoiding the creation of space debris. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0024] Figure 1 This is a perspective view of the array-type multi-star rocket separation device provided in the embodiments of this application; Figure 2 This is a perspective view of the linkage mechanism of the array-type multi-star rocket separation device provided in the embodiments of this application; Figure 3 This is a front view of the linkage mechanism of the array-type multi-star rocket separation device provided in the embodiments of this application; Figure 4 This is a perspective view of the horizontal link assembly and the diagonal link assembly of the linkage mechanism provided in the embodiments of this application; Figure 5 This is a schematic diagram of the clamping unit of the array-type multi-star rocket separation device provided in the embodiments of this application; Figure 6 This is a schematic diagram of the rotary voltage regulating unit of the array-type multi-star rocket separation device provided in the embodiments of this application; Figure 7 This is a schematic diagram of the lower surface of a satellite of the array-type multi-satellite launcher separation device provided in the embodiments of this application; Figure 8 This is a schematic diagram of the upper surface of a satellite of the array-type multi-satellite launcher separation device provided in the embodiments of this application; Figure 9 This is a cross-sectional view of a satellite of the array-type multi-satellite launcher separation device provided in the embodiments of this application; Figure 10 This is a schematic diagram of the stacked satellites of the array-type multi-satellite launcher separation device provided in the embodiments of this application; Figure 11 This is a flowchart of the star-arrow locking method provided in the embodiments of this application; Figure 12 This is a flowchart of the star-rocket separation method provided in the embodiments of this application. Detailed Implementation

[0025] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0026] Example 1 like Figure 1 As shown, this application provides an array-type multi-satellite launcher separation device, including: multiple satellites 1, multiple locking and separation units 2, two linkage mechanisms 3, multiple pressing units 4, multiple rotary pressure regulating units 5, and a satellite-launcher docking platform 6.

[0027] Multiple rotary pressure regulating units 5 are fixed to the satellite-rocket docking platform 6, and these rotary pressure regulating units 5 are arranged in two rows; the lower end of one linkage mechanism 3 is hinged to one row of rotary pressure regulating units 5, and the lower end of another linkage mechanism 3 is hinged to another row of rotary pressure regulating units 5; multiple satellites 1 are stacked on the satellite-rocket docking platform 6, and multiple locking and separating units 2 connect the two linkage mechanisms 3 together to form an integral frame that encloses these satellites 1; multiple pressing units 4 are connected to the linkage mechanisms 3, and the pressing units 4 can be adjusted up and down so that their lower end faces press against the upper surface of the uppermost satellite 1.

[0028] The clamping force of satellite 1 is adjusted by the cooperation of linkage mechanism 3, clamping unit 4 and rotary pressure regulating unit 5. The length of the rod of linkage mechanism 3 is adjusted by the rotary pressure regulating unit 5 installed on the satellite docking platform 6 so that the clamping force of satellite 1 reaches the required value.

[0029] During separation, the two linkage mechanisms 3 are separated by locking the separation unit 2. The linkage mechanism 3 rotates outward until it is fully opened, completing the unlocking process. In this way, the multiple satellites 1 stacked on the star-rocket docking platform 6 can be released.

[0030] Based on the above, the locking and separating unit 2 includes an explosive bolt and a reverse-push separating spring mechanism. The explosive bolt connects the two linkage mechanisms 3 together, providing a locking effect. The reverse-push separating spring mechanism is pressed between the two linkage mechanisms 3. After unlocking, the reverse-push separating spring mechanism provides a reverse force to the two linkage mechanisms 3, causing them to rotate in the opposite direction until they are fully open, completing the unlocking process. The reverse thrust provided by the top locking and separating unit 2 during unlocking, since its radius of rotation is approximately the length of the linkage mechanism 3, generates a large torque, which can give the linkage mechanism 3 a large reverse rotational angular velocity, achieving rapid unlocking and separation.

[0031] like Figure 2 and Figure 3As shown, the linkage mechanism 3 includes: a horizontal tie rod A31, a horizontal connecting rod assembly 32, a straight connecting rod 33, a horizontal tie rod B34, and a diagonal connecting rod assembly 35; one end of the horizontal tie rod A31 is fixedly connected to one end of the horizontal connecting rod assembly 32, and the horizontal tie rod A31 and the horizontal connecting rod assembly 32 are at a certain angle, and the other end of the horizontal tie rod A31 is connected to the locking and separating unit 2; both ends of the horizontal connecting rod assembly 32 are also fixedly connected to the upper end of a diagonal connecting rod assembly 35, and the lower end of each diagonal connecting rod assembly 35 is hinged to a rotary pressure adjusting unit 5, and the diagonal connecting rod assembly 35 is inclined inward from bottom to top, that is, towards satellite 1. The direction is tilted, which is beneficial for restricting satellite 1; the middle of the horizontal link assembly 32 is also connected to one or more clamping units 4, the upper end of each straight link 33 is connected to a clamping unit 4, the lower end of each straight link 33 is also hinged to a rotary pressure regulating unit 5, and the straight link 33 extends from bottom to top, that is, in a vertical state; in addition, a clamping unit 4 is also connected to each of the two ends of the horizontal link assembly 32; the middle of the diagonal link assembly 35 is fixedly connected to one end of one or more horizontal tie rods B34, and the other end of the horizontal tie rod B34 is connected to the locking separation unit 2.

[0032] In addition, the linkage mechanism 3 also includes: multiple adapters A36 and multiple adapters B37; one end of the horizontal tie rod A31, one end of the horizontal connecting rod assembly 32, and the upper end of the diagonal connecting rod assembly 35 are fixedly connected via adapter A36; one end of the horizontal tie rod B34 and the middle of the diagonal connecting rod assembly 35 are fixedly connected via adapter B37. During installation, the horizontal tie rod A31, the horizontal connecting rod assembly 32, and the diagonal connecting rod assembly 35 are connected together via adapter A36. The middle of the horizontal connecting rod assembly 32 is connected to the clamping unit 4, and the upper end of the straight connecting rod 33 is connected to the clamping unit 4. Then, the horizontal tie rod B34 and the diagonal connecting rod assembly 35 are connected together via adapter B37. The lower ends of the straight connecting rod 33 and the diagonal connecting rod assembly 35 are connected to the rotary pressure adjusting unit 5. After adjusting the installation position via the rotary pressure adjusting unit 5, the connection mechanism is fixed. Then, the position of the straight connecting rod 33 on the clamping unit 4 is fixed, thus forming the linkage mechanism 3.

[0033] The tilt angle of the diagonal linkage assembly 35 needs to be determined based on the actual satellite height to ensure the clamping state of the clamping unit 4 during locking, while minimizing the rotation angle during unlocking and separation to prevent collision with satellite 1. Furthermore, after the rotation pressure adjustment unit 5 adjusts the reserved length of the diagonal linkage assembly 35 to control the clamping force on satellite 1, the middle height of the horizontal linkage assembly 32 increases after the forces are applied to both ends of the horizontal linkage assembly 32. This reduces the clamping force exerted on satellite 1 by the clamping unit 4 located in the middle. Adjusting the reserved length of the straight connecting rod 33 by the rotation pressure adjustment unit 5 decreases the reserved length, increasing the tension of the straight connecting rod 33 and lowering the height of the middle of the horizontal linkage assembly 32 back down, thus increasing the clamping force of the clamping unit 4. In addition, the number of locking / separating units 2 connected to the horizontal tie rod B34 increases or decreases with the change in satellite 1's height. This is achieved by increasing the number of adapters B37 in the diagonal linkage assembly 35, increasing the direction of multi-dimensional forces, improving the tension of the linkage mechanism 3, and enhancing the system's stability.

[0034] Based on the above, such as Figure 4 As shown, the horizontal linkage assembly 32 includes: a horizontal linkage A321, a horizontal linkage B322, and an adapter C323. Adapters C323 are installed at both ends of the horizontal linkage B322, and the adapters C323 are connected to the horizontal linkage A321. The horizontal linkage A321 and the horizontal linkage B322 are connected via the adapters C323, thus forming a relatively long horizontal linkage assembly 32. The length of the horizontal linkage assembly 32 can be customized according to different satellite 1 specifications. By replacing horizontal linkages A321 with different lengths, the length of the horizontal linkage assembly 32 can be adjusted. Simultaneously, a limiting device is set at the position where the clamping unit 4 is installed on the horizontal linkage A321 to restrict the movement of the clamping unit 4 and ensure the stability of the satellite 1's locking.

[0035] like Figure 5 As shown, the clamping unit 4 includes: clamping block A unit 41 and clamping block B unit 42; clamping block A unit 41 is connected to the horizontal connecting rod assembly 32 near both ends, that is, connected to the horizontal connecting rod A321; clamping block B unit 42 is connected to the middle position of the horizontal connecting rod assembly 32, that is, connected to the horizontal connecting rod B322, and clamping block B unit 42 is also connected to the upper end of the straight connecting rod 33; clamping block A unit 41 and clamping block B unit 42 can rotate on the horizontal connecting rod assembly 32, thereby moving downward / upward to adjust the squeezing angle of clamping block A unit 41 and clamping block B unit 42 on satellite 1, and clamping block B unit 42 is also connected to the straight connecting rod 33 to ensure the clamping force of the clamping unit 4. The horizontal connecting rod assembly 32 is provided with a limit device to restrict the movement of the clamping unit 4 and ensure the stability of the locking of satellite 1. As an example, both clamping block A unit 41 and clamping block B unit 42 have adjusting bolts, which can be used to adjust the length of the satellite 1 by adjusting the downward / upward movement of the adjusting bolts.

[0036] like Figure 6 As shown, the rotary pressure regulating unit 5 includes: a recovery unit 51, a rotary shaft assembly 52, and a mounting base 53; the lower end of the mounting base 53 is fixed to the satellite docking platform 6, and the upper end of the mounting base 53 has a downward-facing mounting groove that runs through both the inner and outer sides. Here, "outer side" refers to the side away from the satellite, and "inner side" refers to the side closer to the satellite. The mounting base 53 also has mounting holes on the left and right sides, and the extension direction of the mounting holes is perpendicular to the extension direction of the mounting groove.

[0037] The rotary shaft assembly 52 is inserted into the mounting hole and hinged to the mounting base 53. The lower end of the linkage mechanism 3 (straight linkage 33 or oblique linkage assembly 35) is inserted into the mounting groove and connected to the part of the rotary shaft assembly 52 located in the mounting groove, thereby achieving the hinge connection between the lower end of the linkage mechanism 3 and the rotary pressure regulating unit 5. Before the lower end of the linkage mechanism 3 is fixed to the rotary shaft assembly 52, the length of the linkage mechanism 3 can be adjusted. As an example, the part of the rotary shaft assembly 52 located in the mounting groove has a connecting hole with a certain depth. The lower end of the linkage mechanism 3 is inserted into the connecting hole, and the depth of insertion into the connecting hole can be adjusted. After adjustment, the lower end of the linkage mechanism 3 is fixed to the rotary shaft assembly 52 by fixing screws. In this way, the rotary shaft assembly 52 not only provides a rotation support point for the linkage mechanism 3, but also adjusts the length of the linkage mechanism 3 connection, and provides clamping force to the satellite 1 through the linkage mechanism 3. After the length adjustment is completed, the rotary shaft assembly 52 is fixed to the linkage mechanism 3, completing the locking process.

[0038] The recovery unit 51 is located on the upper part of the mounting base 53 near the outer side, covering the mounting groove, and is located outside the linkage mechanism 3. In addition, the recovery unit 51 is a one-way mechanism, which can only move outward in one direction. Thus, when the linkage mechanism 3 located inside the recovery unit 51 rotates to open, the recovery unit 51 moves outward to open. After the linkage mechanism 3 rotates to the outside of the recovery unit 51, the recovery unit 51 returns to its original position, and the recovery unit 51 will not move inward from its original position. Therefore, after the linkage mechanism 3 passes through the recovery unit 51, the recovery unit 51 will restrict the linkage mechanism 3 from returning, fully opening the linkage mechanisms 3 on both sides, providing space guarantee for the separation of satellite 1.

[0039] Based on the above, the mounting base 53 can be divided into two types, the difference being the rotation trajectory of the linkage mechanism 3. One type is the mounting base 53 connected to the inclined linkage assembly 35, with the mounting base 53 serving as the rotation center and the mounting hole being circular, which can ensure the stability of the rotation of the inclined linkage assembly 35. The other type is the mounting base 53 connected to the straight linkage 33, with the mounting hole being linear (i.e., the cross-sectional shape of the mounting hole is non-circular, such as curved), so that the trajectory avoids the movement trajectory of the straight linkage 33, preventing the straight linkage 33 and the inclined linkage assembly 35 from rotating simultaneously, and the rotation center and rotation radius being different, thus preventing jamming.

[0040] like Figures 7 to 10 As shown, the lower surface of satellite 1 has a downwardly protruding shear pin 11, and the upper surface of satellite 1 has a downwardly recessed shear hole 12. The upper surface of the satellite-rocket docking platform 6 also has a downwardly recessed shear hole 61. When stacking satellite 1, the shear pin 11 of the satellite 1 located at the bottom layer is inserted into the shear hole 61 of the satellite-rocket docking platform 6, and the shear pin 11 of the satellite 1 located at the top layer is inserted into the shear hole 12 of the satellite 1 located at the bottom layer. Furthermore, the shear pin 11, shear hole 12, and shear hole 61 are all conical structures. Since the conical structure has a guiding effect, it simplifies the docking process. The shear pin 11 of satellite 1 also has the function of restricting its lateral movement. After satellite 1 is installed, the linkage mechanism 3 is tightened to fix satellite 1 on the satellite-rocket docking platform 6.

[0041] Example 2 like Figure 11 As shown, this application provides a star-rocket locking method, which is applied to the array-type multi-star-rocket separation device in Embodiment 1, and includes the following steps: Step S1110: Connect the linkage mechanism 3 to the rotary pressure regulating unit 5, and the length of the linkage mechanism 3 is not fixed; After the lower end of the linkage mechanism 3 is installed to the rotary pressure regulating unit 5, the straight connecting rod 33 of the linkage mechanism 3 and the oblique connecting rod assembly 35 of the linkage structure 3 are reserved for a certain length in the rotary pressure regulating unit 5, and are connected but not fixed.

[0042] Step S1120: Stack multiple satellites in two layers onto the satellite-rocket docking platform 6; When the first layer of satellite 1 docks with the satellite-rocket docking platform 6, the protruding shear pin 11 on satellite 1 is inserted into the shear hole 61 of the satellite-rocket docking platform. Subsequent satellites 1 are stacked on top of each other using the same method until all satellites 1 are stacked.

[0043] Step S1130: Rotate the linkage mechanism 3 on both sides until the lower end face of the clamping unit 4 is in contact with the docking surface of the satellite 1 and then stop. Rotate the two connecting rod mechanisms 3 around the rotary pressure regulating unit 5, and stop the rotation of the connecting rod mechanism 3 after the lower end face of the clamping unit 4 on the connecting rod structure 3 is in contact with the docking surface of the satellite 1.

[0044] Step S1140: Connect the multiple locking and separating units 2 to the linkage mechanisms 3 on both sides to form an integral frame. Multiple locking and separating units 2 connect two linkage mechanisms 3 together to form an integral frame that encloses the satellites 1. The number of horizontal tie rods B34 connected to the locking and separating units 2 increases with the stacking height of the satellites 1.

[0045] Step S1150: Shorten the length of the linkage mechanism 3 until the clamping unit 4 clamps the satellite 1, fix the length of the linkage mechanism 3, and complete the locking process; At the rotary pressure regulating unit 5, reduce the reserved length of the inclined connecting rod assembly 35 until the clamping unit 4 clamps the satellite 1, thus fixing the length of the inclined connecting rod assembly 35. At the rotary pressure regulating unit 5, reduce the reserved length of the straight connecting rod 33, and apply secondary pressure to the clamping unit 4 connected to the straight connecting rod 33 to ensure the clamping force on the satellite 1. Wait for the inclined connecting rod assembly 35 and the straight connecting rod to complete the locking process.

[0046] Example 3 like Figure 12 As shown, this application provides a star-rocket separation method, which is applied to the array-type multi-star-rocket separation device in Embodiment 1, and includes the following steps: Step S1210: All locking and separating units 2 are unlocked, and the clamping force on satellite 1 disappears; During separation, all locking separation units 2 receive a separation signal, their explosive bolts ignite, locking separation units 2 unlock, and the clamping force on satellite 1 disappears.

[0047] Step S1220: The linkage mechanism 3 rotates around the rotary pressure regulating unit 5, causing the linkage mechanism 3 to open; After the explosive bolt of the locking and separating unit 2 is ignited, the reverse thrust spring mechanism of the locking and separating unit 2 provides a reverse thrust to the linkage mechanism 3, pushing the linkage mechanism 3 to rotate around the rotary pressure regulating unit 5, thereby opening the two linkage mechanisms 3 and completing the unlocking of the locking and separating unit 2.

[0048] Step S1230: Release multiple satellites 1 from the satellite-rocket docking platform 6 to complete the satellite-rocket separation; After the linkage mechanism 3 is opened, the attitude is adjusted according to the flight sequence. After stabilization, the satellite release mechanism of the satellite-rocket docking platform 6 is unlocked to release multiple satellites 1, completing the separation of the satellite and rocket.

[0049] The array-type multi-satellite launch vehicle separation device provided in this application has a simple structure, is easy to operate, has a simple processing technology, and low manufacturing cost. It also utilizes the satellite's own skeleton structure and designs a unified satellite and launch vehicle docking structure, reducing the satellite's own weight and increasing the number of satellites that the launch vehicle can carry. Furthermore, the standardized interface structure makes the interface form simple and easy to operate, reducing workload and manufacturing costs. The unitized and modular satellites can flexibly adjust their number to form a universal standard and reduce development costs. In addition, the array-type arrangement of satellites reduces the gaps between satellites, making full use of space and greatly improving the utilization rate of space. Moreover, the rod component recovery mechanism also avoids the generation of space debris and protects the space environment.

[0050] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0051] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An array-type multi-star rocket separation device, characterized in that, include: Multiple satellites, multiple locking and separation units, two linkage mechanisms, multiple clamping units, multiple rotary pressure regulating units, and a satellite-rocket docking platform; Multiple rotary pressure regulating units are fixed to the satellite-rocket docking platform, and the rotary pressure regulating units are arranged in two rows; the lower end of one linkage mechanism is hinged to one row of rotary pressure regulating units, and the lower end of another linkage mechanism is hinged to the other row of rotary pressure regulating units; multiple satellites are stacked on the satellite-rocket docking platform, and multiple locking and separating units connect the two linkage mechanisms together to form an integral frame that encloses the satellites; multiple pressing units are connected to the linkage mechanisms, and the pressing units can be adjusted up and down so that their lower end faces press against the upper surface of the uppermost satellite; The rotary pressure regulating unit includes: a recovery unit, a rotary shaft assembly, and a mounting base; The lower end of the mounting base is fixed to the star-rocket docking platform. The upper end of the mounting base has a downward-facing mounting groove that runs through both the inner and outer sides. The mounting base also has mounting holes on the left and right sides, with the extension direction of the mounting holes perpendicular to the extension direction of the mounting groove. The rotary shaft assembly is inserted into the mounting hole and hinged to the mounting base, and the lower end of the linkage mechanism is inserted into the mounting groove and connected to the part of the rotary shaft assembly located in the mounting groove. The recovery unit is located on the upper part of the mounting base near the outer side, covering the mounting groove, and the recovery unit is located on the outside of the linkage mechanism; The recovery unit is a one-way mechanism. During the rotation and opening process, the linkage mechanism located inside the recovery unit moves the recovery unit outward and opens. After the linkage mechanism rotates to the outside of the recovery unit, the recovery unit returns to its original position, preventing the linkage mechanism from returning.

2. The array-type multi-star rocket separation device according to claim 1, characterized in that, The locking and separating unit includes an explosive bolt and a reverse-thrust separating spring mechanism. The explosive bolt connects two linkage mechanisms together, and the reverse-thrust separating spring mechanism is pressed between the two linkage mechanisms.

3. The array-type multi-star rocket separation device according to claim 1 or 2, characterized in that, The linkage mechanism includes: tie rod A, a horizontal linkage assembly, a straight linkage, tie rod B, and a diagonal linkage assembly; One end of the horizontal tie rod A is fixedly connected to one end of the horizontal connecting rod assembly, and the horizontal tie rod A and the horizontal connecting rod assembly are at a certain angle. The other end of the horizontal tie rod A is connected to the locking and separating unit. Both ends of the horizontal connecting rod assembly are fixedly connected to the upper end of a diagonal connecting rod assembly, and the lower end of each diagonal connecting rod assembly is hinged to a rotary pressure regulating unit. The diagonal connecting rod assembly is inclined inward from bottom to top. The middle of the horizontal connecting rod assembly is connected to one or more clamping units, the upper end of each straight connecting rod is connected to a clamping unit, the lower end of each straight connecting rod is hinged to a rotary pressure adjusting unit, and the straight connecting rods extend from bottom to top in a vertical state. Near each end of the crossbar assembly, a clamping unit is also connected; The middle of the diagonal linkage assembly is fixedly connected to one end of one or more horizontal tie rods B, and the other end of the horizontal tie rod B is connected to the locking and releasing unit.

4. The array-type multi-star rocket separation device according to claim 3, characterized in that, The linkage mechanism also includes: multiple adapters A and multiple adapters B; one end of the horizontal tie rod A, one end of the horizontal connecting rod assembly, and the upper end of the diagonal connecting rod assembly are fixedly connected via adapter A; one end of the horizontal tie rod B and the middle of the diagonal connecting rod assembly are fixedly connected via adapter B.

5. The array-type multi-star rocket separation device according to claim 3, characterized in that, The cross link assembly includes: cross link A, cross link B, and adapter C; adapter C is installed at both ends of cross link B, and adapter C is connected to cross link A.

6. The array-type multi-star rocket separation device according to claim 1 or 2, characterized in that, The clamping unit includes: clamping block A unit and clamping block B unit; clamping block A unit is connected to the cross link assembly near both ends; clamping block B unit is connected to the cross link assembly at the middle position and is connected to the upper end of the straight link.

7. The array-type multi-star rocket separation device according to claim 1 or 2, characterized in that, The satellite has a downward-convex shear pin on its lower surface and a downward-concave shear hole on its upper surface. The satellite-rocket docking platform also has a downward-concave shear hole on its upper surface. When stacking satellites, the shear pin of the satellite at the bottom layer is inserted into the shear hole of the satellite-rocket docking platform, and the shear pin of the satellite at the top layer is inserted into the shear hole of the satellite at the bottom layer.

8. A method for locking a star-and-arrow, characterized in that, The locking method, when applied to the array-type multi-star rocket separation device according to any one of claims 1 to 7, includes the following steps: Step S1110: Connect the linkage mechanism to the rotary pressure regulating unit, and the length of the linkage mechanism is not fixed; Step S1120: Stack multiple satellites onto the satellite-rocket docking platform; Step S1130: Rotate the linkage mechanism on both sides until the lower end face of the clamping unit is in contact with the satellite docking surface; Step S1140: Connect the linkage mechanisms on both sides together using multiple locking and separating units to form a complete frame. Step S1150: Shorten the length of the linkage mechanism until the clamping unit clamps the satellite, fix the length of the linkage mechanism, and complete the locking process.

9. A method for separating a satellite from a rocket, characterized in that, The separation method, when applied to the array-type multi-star rocket separation device according to any one of claims 1 to 7, includes the following steps: Step S1210: All locking and separating units are unlocked, and the clamping force on the satellite disappears; Step S1220: The linkage mechanism rotates around the rotary pressure regulating unit, causing the linkage mechanism to open; Step S1230: Release multiple satellites from the satellite-rocket docking platform to complete the satellite-rocket separation.

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