A stacked satellite batch launch system

Abstract

This application relates to a stacked satellite mass launch system, belonging to the field of satellite technology. It includes a mounting base pressure rod and multiple satellites stacked on a mounting base. A positioning assembly is provided between adjacent satellites. The positioning assembly includes a positioning post and a sleeve. The positioning post is fixedly disposed on the bottom wall of the satellite, and the sleeve is fixedly disposed on the top wall of the satellite, for inserting the positioning post to define the position of adjacent satellites. A first elastic element is provided inside the sleeve for driving the positioning post out of the sleeve. The pressure rod is hinged to the mounting base and has a clamping assembly for applying clamping force to the satellites. When the satellites separate, the clamping assembly unlocks, and under the action of the first elastic element, the upper-layer satellite is pushed, causing the positioning post to disengage from the sleeve, at which point the upper-layer satellite can be unlocked and separated.

Description

Technical Field

[0001] This application relates to the field of satellite technology, and in particular to a satellite batch launch system based on a stacking method. Background Technology

[0002] For batch satellite launches, the safe separation of the satellite from the launch vehicle in orbit is a crucial issue. Currently, in multi-satellite launches, each satellite has an independent interface with the distributor, and the connection and separation methods are simple, widely used, and technologically mature. However, with the rapid development of satellite constellations and the increasing demand for satellites, reaching tens of thousands, the original independent launch method can no longer meet market needs.

[0003] Because the structure of stacked satellites differs greatly from that of traditional satellites, it would be difficult to meet the requirements of stable connection during launch and unlocking / separation during on-orbit if traditional unlocking devices were used. Summary of the Invention

[0004] To facilitate the separation of stacked satellites, this application provides a satellite batch launch system based on a stacking method.

[0005] This application provides a satellite batch launch system based on a stacking method, which adopts the following technical solution:

[0006] A satellite batch launch system based on stacking includes a mounting base support rod and multiple satellites, wherein the multiple satellites are stacked on the mounting base;

[0007] A positioning component is provided between two adjacent satellites. The positioning component includes a positioning post and a sleeve. The positioning post is fixedly installed on the bottom wall of the satellite, and the sleeve is fixedly installed on the top wall of the satellite. It is used for the positioning post to be inserted to limit the position of the two adjacent satellites. A first elastic element is provided inside the sleeve to drive the positioning post out of the sleeve.

[0008] The pressure rod is hinged to the mounting base, and the pressure rod is provided with a clamping assembly for applying clamping force to the satellite.

[0009] By adopting the above technical solution, after multiple layers of satellites are stacked on the mounting base, the positioning posts between adjacent satellites are inserted into the sleeve, restricting the degrees of freedom parallel to the satellite surface and thus defining the satellite's position. Then, the clamping assembly on the pressure rod applies a clamping force perpendicular to the satellite surface, thereby defining the overall position of the satellite. When the satellites separate, the clamping assembly unlocks, and under the action of the first elastic element, the upper-layer satellite is pushed, causing the positioning posts to disengage from the sleeve. At this point, the upper-layer satellite can be unlocked and separated.

[0010] Furthermore, the clamping assembly includes a telescopic rod and a clamping head. The telescopic rod includes a fixed rod and a movable rod. The fixed rod is fixedly mounted on the clamping rod, and a groove is formed inside the fixed rod along its length. The movable rod is slidably mounted in the groove. The clamping head is located at the end of the movable rod away from the fixed rod and is used to abut against the top wall of the satellite. The telescopic rod contains a second elastic element for driving the movable rod to slide inward into the fixed rod so that the clamping head disengages from the satellite. The telescopic rod also contains an unlocking element for limiting the position of the movable rod.

[0011] By adopting the above technical solution, when the satellite separates, the unlocking component releases the restriction on the movable rod. Under the action of the second elastic component, the movable rod slides inward into the fixed rod, causing the clamping head to slide outward along the top wall of the satellite until the clamping head detaches from the satellite, thus achieving unlocking.

[0012] Furthermore, the unlocking component is configured as a breakable explosive rod, one end of which abuts against the bottom wall of the chute, and the other end abuts against the movable rod.

[0013] By adopting the above technical solution, the explosive rod is located inside the fixed rod, which avoids the generation of space debris after the explosion and reduces pollution to the space environment.

[0014] Furthermore, the pressing head is configured as a pressure roller, which is rotatably located at the end of the movable rod away from the fixed rod, and the rotation axis of the pressure roller is perpendicular to the length direction of the telescopic rod.

[0015] Furthermore, the pressure bar includes multiple rods, each of which is provided with a clamping assembly.

[0016] By adopting the above technical solution, the pressure bar is divided into multiple segments, each equipped with a separate clamping component, which facilitates the separation of multiple satellites in batches.

[0017] Furthermore, adjacent rods are hinged together by a hinge shaft, which is provided with a third elastic element for driving the rods to rotate away from the satellite; a locking element is provided between adjacent rods to keep the two rods coaxial.

[0018] By adopting the above technical solution, when it is necessary to separate the satellite at intervals, the locking component is unlocked, and under the action of the third elastic component, the rod deflects outward and moves away from the satellite, preventing the rod from interfering with the normal separation of the satellite.

[0019] Furthermore, the locking component is configured as a pyrotechnic locking rod, with locking grooves provided on both the top and bottom walls of the rod along its length. The two ends of the pyrotechnic locking rod are respectively inserted into the positioning grooves of two adjacent rods.

[0020] Furthermore, the rod body is equipped with an initiator for controlling the explosion of the pyrotechnic locking rod. The initiator includes a contact switch, which is located inside the fixed rod. When the movable rod slides into the fixed rod and contacts the contact switch, the clamping head disengages from the satellite. When the movable rod touches the contact switch, the initiator controls the pyrotechnic locking rod to explode.

[0021] By adopting the above technical solution, when the satellite separates, the movable rod first moves into the fixed rod, and the clamping head on the movable rod gradually detaches from the satellite. When the end of the movable rod contacts the contact switch, the contact switch connects to the detonator, and the detonator controls the pyrotechnic locking rod to explode. At this time, the rod can deflect outward, and after unlocking the clamping force on the top of the satellite, the rod is automatically controlled to deflect outward. There is no need to control the detonator action through a separate control element, which simplifies the structure and improves reliability.

[0022] Furthermore, a push block is slidably disposed inside the sleeve, and the first elastic element is configured as a first spring, with one end of the first spring abutting against the bottom of the sleeve and the other end abutting against the push block.

[0023] Furthermore, the top wall of the sleeve is provided with a locking block for abutting against the push block, and the top wall of the push block is provided with a locking groove for the insertion of the limiting block. When the locking block abuts against the locking groove, the top wall of the push block is not lower than the top wall of the sleeve.

[0024] In summary, this application includes at least one of the following beneficial technical effects:

[0025] 1. After multiple satellites are stacked on the mounting base, the positioning pins between adjacent satellites are inserted into the sleeve, restricting the degrees of freedom parallel to the satellite surface and thus defining the satellite's position. Then, the clamping assembly on the pressure rod applies a clamping force perpendicular to the satellite surface, thereby defining the overall position of the satellite. When the satellites separate, the clamping assembly unlocks, and under the action of the first elastic element, the upper-layer satellite is pushed, causing the positioning pins to disengage from the sleeve. At this point, the upper-layer satellite can be unlocked and separated.

[0026] 2. The explosive rod is located inside the fixed rod, which avoids the generation of space debris after the explosion and reduces pollution to the space environment.

[0027] 3. When the satellite separates, the movable rod first moves inward toward the fixed rod, and the clamping head on the movable rod gradually detaches from the satellite. When the end of the movable rod contacts the contact switch, the contact switch connects to the detonator. The detonator controls the pyrotechnic locking rod to detonate. At this time, the rod body can deflect outward, thereby unlocking the clamping force on the top of the satellite. The rod body is automatically controlled to deflect outward, eliminating the need for a separate control element to control the detonator's action, simplifying the structure and improving reliability. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application;

[0029] Figure 2 This is a schematic diagram illustrating the structure of the positioning component, which is the main feature of this application embodiment;

[0030] Figure 3 This is a schematic diagram illustrating the structure of the pressure bar and the clamping assembly, which are the main embodiments of this application.

[0031] Figure 4 This is a cross-sectional view of an embodiment of this application, mainly illustrating the structure of the clamping component.

[0032] Explanation of reference numerals in the attached drawings: 1. Mounting base; 11. Ear plate; 12. Mounting shaft; 121. First torsion spring; 13. Limiting strip; 2. Pressure rod; 21. Rod body; 211. Hinge shaft; 212. Third elastic element; 213. Locking groove; 2131. Locking element; 3. Satellite; 4. Positioning assembly; 41. Positioning post; 42. Sleeve; 421. First elastic element; 422. Push block; 423. Locking block; 5. Pressing assembly; 51. Telescopic rod; 511. Fixed rod; 5111. Slide groove; 5112. Contact switch; 512. Movable rod; 513. Second elastic element; 514. Unlocking element; 52. Pressing head. Detailed Implementation

[0033] The following is in conjunction with the appendix Figure 1-4 This application will be described in further detail.

[0034] This application discloses a satellite batch launch system based on a stacking method.

[0035] Reference Figure 1 A satellite batch launch system based on stacking includes a mounting base 1, a pressure rod 2, and multiple satellites 3. The multiple satellites 3 are stacked on the mounting base 1. In this embodiment, the satellites 3 are large-sized flat-panel satellites 3. The satellites 3 are arranged in two rows along a direction perpendicular to the mounting base 1, and each row includes multiple satellites 3. The satellites 3 in each row are arranged alternately.

[0036] Reference Figure 1 and Figure 2A positioning component 4 is provided between two adjacent satellites 3. Each satellite 3 has at least two sets of positioning components 4. For large-sized flat-panel satellites 3, to improve stability, this embodiment provides three sets of positioning components 4 for each satellite 3. The positioning component 4 includes a positioning post 41 and a sleeve 42. Both the sleeve 42 and the positioning post 41 are cylindrical; in other embodiments, they can be rectangular or other shapes. The positioning post 41 is fixedly installed on the bottom wall of the satellite 3, and the sleeve 42 is fixedly installed on the top wall of the satellite 3, used for inserting the positioning post 41 to define the position of adjacent satellites 3. It should be noted that the top wall of the satellite 3 refers to the side wall of the satellite 3 away from the mounting base 1, and the bottom wall of the satellite 3 refers to the side wall close to the mounting base 1. To minimize the installation gap between the satellites 3, a portion of the sleeve 42 can be embedded within the satellite 3.

[0037] Reference Figure 2 A push block 422 is slidably disposed inside the sleeve 42. A first elastic element 421 for driving the positioning pin 41 out of the sleeve 42 is provided inside the sleeve 42. The first elastic element 421 is a first spring, one end of which abuts against the bottom of the sleeve 42, and the other end abuts against the push block 422. To prevent the push block 422 from detaching from the sleeve 42, a locking block 423 for abutting against the push block 422 is provided on the top wall of the sleeve 42. A locking groove for the insertion of the limiting block is opened on the top wall of the push block 422. When the locking block 423 abuts against the slot, the top wall of the push block 422 is not lower than the top wall of the sleeve 42. In this embodiment, when the locking block 423 abuts against the slot, the top wall of the push block 422 is flush with the top wall of the sleeve 42. During the separation of the satellite 3, the push block 422 pushes the positioning post 41 upward under the action of the first spring, and after the push block 422 stops moving, the positioning post 41 can just disengage from the sleeve 42, so that the satellite 3 can be separated smoothly.

[0038] Reference Figure 1 and Figure 3 The pressure rod 2 is hinged to the mounting base 1. In this embodiment, to ensure that the satellite 3 is subjected to uniform and stable force, each column of satellites 3 is provided with three pressure rods 2. An ear plate 11 is fixedly installed on the top wall of the mounting base 1. A mounting shaft 12 is rotatably inserted through the ear plate 11. The bottom of the pressure rod 2 is fixedly installed on the mounting shaft 12, allowing the pressure rod 2 to deflect relative to the satellite 3, either closer to or further away from it. A first torsion spring 121 is sleeved on the mounting shaft 12. One end of the first torsion spring 121 is fixedly connected to the pressure rod 2, and the other end is fixedly connected to the ear plate 11. The elastic force of the first torsion spring 121 drives the pressure rod 2 to deflect away from the satellite 3, preventing the pressure rod 2 from interfering with the separation of the satellite 3.

[0039] A limiting strip 13 is fixedly installed on the mounting base 1. The limiting strip 13 is used to abut against the side wall of the pressure rod 2 away from the satellite 3 to prevent the pressure rod 2 from deflecting outward under the action of the first torsion spring 121 before the satellite 3 separates, thus keeping the pressure rod 2 in a vertical state. The limiting strip 13 is made of pyrotechnic material. When the pressure rod 2 needs to deflect outward due to the separation of the satellite 3, the limiting strip 13 can be controlled to explode.

[0040] Reference Figure 3 and Figure 4 The pressure bar 2 is equipped with a clamping component 5 for applying clamping force to the satellites 3. The pressure bar 2 includes multiple bars 21, the number of which corresponds to the number of satellites 3 in a single row. Each bar 21 is equipped with a clamping component 5. The pressure bar 2 is divided into multiple segments, each equipped with a separate clamping component 5, so that multiple satellites 3 can be separated in batches.

[0041] Reference Figure 3 and Figure 4 The pressing assembly 5 includes a telescopic rod 51 and a pressing head 52. The telescopic rod 51 includes a fixed rod 511 and a movable rod 512. The fixed rod 511 is fixedly mounted on the pressing rod 2. A groove 5111 is provided in the fixed rod 511 along the length direction of the fixed rod 511. The movable rod 512 is slidably mounted in the groove 5111.

[0042] Reference Figure 3 and Figure 4 The clamping head 52 is located at the end of the movable rod 512 away from the fixed rod 511. The clamping head 52 is used to abut against the top wall of the satellite 3. The clamping head 52 is configured as a pressure roller, which is rotatably located at the end of the movable rod 512 away from the fixed rod 511. The rotation axis of the pressure roller is perpendicular to the length direction of the telescopic rod 51. During the process of releasing the clamping force on the satellite 3, the movable rod 512 slides inward into the fixed rod 511, and the pressure roller rolls along the top wall of the satellite 3, reducing friction and damage to the surface of the satellite 3.

[0043] Reference Figure 4 The telescopic rod 51 is provided with a second elastic element 513 for driving the movable rod 512 to slide into the fixed rod 511 so that the pressing head 52 is disengaged from the satellite 3. The second elastic element 513 is a tension spring, one end of which is fixedly connected to the bottom wall of the slide groove 5111, and the other end is fixedly connected to the end of the movable rod 512.

[0044] Reference Figure 4 The telescopic rod 51 is provided with an unlocking component 514 for limiting the position of the movable rod 512. The unlocking component 514 is a detonating rod that can break. The detonating rod is made of pyrotechnic material. One end of the detonating rod abuts against the bottom wall of the slide 5111, and the other end abuts against the movable rod 512.

[0045] Among them, reference Figure 3 and Figure 4The two adjacent rods 21 are hinged together by a hinge shaft 211. A third elastic element 212 is provided on the hinge shaft 211 to drive the rods 21 to rotate away from the satellite 3. The third elastic element 212 is a third torsion spring, and the two ends of the third torsion spring are fixedly connected to the two rods 21 respectively.

[0046] Reference Figure 3 and Figure 4 A locking element 2131 is provided between two adjacent rods 21 to keep the two rods 21 in a coaxial state. The locking element 2131 is a pyrotechnic locking rod. The pyrotechnic locking rod is a pyrotechnic product. The top and bottom walls of the rods 21 are provided with locking grooves 213 along the length of the rods 21. The two ends of the pyrotechnic locking rod are respectively inserted into the positioning grooves of the two adjacent rods 21.

[0047] Among them, reference Figure 3 and Figure 4 The rod body 21 is equipped with an initiator for controlling the explosion of the pyrotechnic locking rod. The initiator includes a contact switch 5112, which is located inside the fixed rod 511. When the movable rod 512 slides into the fixed rod 511 and contacts the contact switch 5112, the clamping head 52 disengages from the satellite 3. When the movable rod 512 touches the contact switch 5112, the initiator controls the explosion of the pyrotechnic locking rod.

[0048] When satellite 3 separates, the movable rod 512 first moves into the fixed rod 511, and the clamping head 52 on the movable rod 512 gradually disengages from satellite 3. When the end of the movable rod 512 contacts the contact switch 5112, the contact switch 5112 connects to the detonator, and the detonator controls the pyrotechnic locking rod to detonate. At this time, the rod body 21 can deflect outward, and after unlocking the clamping force on the top of satellite 3, the rod body 21 is automatically controlled to deflect outward. There is no need to control the detonator action through a separate control element, which simplifies the structure and improves reliability.

[0049] The implementation principle of this application embodiment is as follows: After multiple layers of satellites 3 are stacked on the mounting base 1, the positioning pins 41 between adjacent satellites 3 are inserted into the sleeve 42, restricting the degree of freedom parallel to the surface of the satellite 3, thereby limiting the position of the satellite 3; then, the clamping assembly 5 on the pressure rod 2 applies a clamping force perpendicular to the surface of the satellite 3 to the satellite 3, thereby limiting the position of the entire satellite 3. When the satellite 3 separates, the explosive rod breaks off, releasing the restriction on the movable rod 512. Under the action of the second elastic member 513, the movable rod 512 slides into the fixed rod 511, causing the clamping head 52 to slide outward along the top wall of the satellite 3 until the clamping head 52 disengages from the satellite 3, thus unlocking. Under the action of the first elastic member 421, the upper satellite 3 is pushed and the positioning pins 41 disengage from the sleeve, at which point the upper satellite 3 can be unlocked and separated.

[0050] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A satellite batch launch system based on stacking, comprising a mounting base (1), a pressure rod (2), and multiple satellites (3), wherein the multiple satellites (3) are stacked on the mounting base (1), characterized in that: A positioning assembly (4) is provided between two adjacent satellites (3). The positioning assembly (4) includes a positioning post (41) and a sleeve (42). The positioning post (41) is fixedly installed on the bottom wall of the satellite (3), and the sleeve (42) is fixedly installed on the top wall of the satellite (3). The positioning post (41) is inserted to limit the position of the two adjacent satellites (3). A first elastic element (421) is provided inside the sleeve (42) to drive the positioning post (41) out of the sleeve (42). The pressure rod (2) is hinged to the mounting base (1), and a clamping assembly (5) is provided on the pressure rod (2) to apply a clamping force to the satellite (3). The clamping assembly (5) includes a telescopic rod (51) and a clamping head (52). The telescopic rod (51) includes a fixed rod (511) and a movable rod (512). The fixed rod (511) is fixedly mounted on the pressure rod (2). A groove (5111) is provided in the fixed rod (511) along the length direction of the fixed rod (511). The movable rod (512) is slidably mounted in the groove (5111). The clamping head (52) is located at the end of the movable rod (512) away from the fixed rod (511). The clamping head (52) is used to abut against the top wall of the satellite (3). A second elastic element (513) is provided in the telescopic rod (51) to drive the movable rod (512) to slide into the fixed rod (511) so that the clamping head (52) is disengaged from the satellite (3). An unlocking element (514) is provided in the telescopic rod (51) to limit the position of the movable rod (512). The unlocking component (514) is configured as a breakable explosive rod, one end of which abuts against the bottom wall of the slide groove (5111) and the other end abuts against the movable rod (512); the pressure rod (2) includes multiple rods (21), each of which is provided with a pressing component (5); adjacent rods (21) are hinged together by a hinge shaft (211), and the hinge shaft (211) is provided with a third elastic element (212) for driving the rod (21) to rotate away from the satellite (3); a locking component (2131) is provided between adjacent rods (21) for keeping the two rods (21) coaxial.

2. The satellite batch launch system based on stacking as described in claim 1, characterized in that: The pressing head (52) is configured as a pressure roller, which is rotatably located at the end of the movable rod (512) away from the fixed rod (511), and the rotation axis of the pressure roller is perpendicular to the length direction of the telescopic rod (51).

3. The satellite batch launch system based on stacking as described in claim 1, characterized in that: The locking component (2131) is configured as a pyrotechnic locking rod. The top and bottom walls of the rod body (21) are provided with locking grooves (213) along the length of the rod body (21). The two ends of the pyrotechnic locking rod are respectively inserted into the positioning grooves of two adjacent rod bodies (21).

4. A satellite batch launch system based on stacking as described in claim 3, characterized in that: The rod body (21) is provided with an initiator for controlling the explosion of the pyrotechnic locking rod. The initiator includes a contact switch (5112) which is located inside the fixed rod (511). When the movable rod (512) slides into the fixed rod (511) and contacts the contact switch (5112), the clamping head (52) disengages from the satellite (3). When the movable rod (512) touches the contact switch (5112), the initiator controls the explosion of the pyrotechnic locking rod.

5. A satellite batch launch system based on stacking as described in claim 1, characterized in that: A push block (422) is slidably disposed inside the sleeve (42), and the first elastic element (421) is configured as a first spring, with one end of the first spring abutting against the bottom of the sleeve (42) and the other end abutting against the push block (422).

6. A satellite batch launch system based on stacking as described in claim 5, characterized in that: The top wall of the sleeve (42) is provided with a locking block (423) for abutting against the push block (422). The top wall of the push block (422) is provided with a slot for the insertion of the limiting block. When the locking block (423) abuts against the slot, the top wall of the push block (422) is not lower than the top wall of the sleeve (42).

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