Modular low-impact star-rocket separation device

Abstract

The application relates to the technical field of rockets, in particular to a modular low-impact satellite-rocket separation device which comprises a satellite docking support, a satellite-rocket separation spring, a rocket docking support, a pyrotechnic satellite storage box, an explosive bolt and a pyrotechnic rocket storage box; the satellite docking support is provided with a first docking hole, and the opening of the pyrotechnic satellite storage box is fixed to the periphery of the first docking hole; the rocket docking support is provided with a second docking hole, and the opening of the pyrotechnic rocket storage box is fixed to the periphery of the second docking hole; the explosive bolt passes through the first docking hole and the second docking hole, and the satellite docking support and the rocket docking support are fixedly connected together; the lower end of the satellite-rocket separation spring is connected with the rocket docking support, the upper end of the satellite-rocket separation spring is in contact with the satellite docking support, and the rocket docking support and the satellite docking support compress the satellite-rocket separation spring. The application can avoid that the satellite-rocket separation mechanism is limited by the support of the docking interface of a spacecraft, and the reliability of satellite-rocket separation is improved.

Description

Technical Field

[0001] This application relates to the field of rocket technology, and in particular to a modular low-impact satellite-rocket separation device. Background Technology

[0002] The spacecraft-launch vehicle separation mechanism is a device that enables a secure connection between the spacecraft and the launch vehicle. Furthermore, the spacecraft-launch vehicle separation mechanism can unlock and separate the spacecraft and the launch vehicle in the operational orbit according to predetermined requirements.

[0003] Currently, it is common practice to integrate the support used for the docking interface between the spacecraft and the launch vehicle separation mechanism with the spacecraft. This results in a fixed separation point, and the spacecraft separation mechanism is also constrained by the spacecraft structure. Different spacecraft require the design of corresponding docking interface supports and matching spacecraft separation mechanisms. Furthermore, when the center of gravity of the finished spacecraft deviates, subsequent adjustments are difficult and require re-customization, thus increasing design and manufacturing costs.

[0004] In addition, traditional pyrotechnic separation products generate large impact loads (3000-5000)g during operation. Therefore, using pyrotechnics to drive the separation mechanism reduces the reliability of the separation and may even make it difficult for the spacecraft to accurately reach its orbit.

[0005] Therefore, how to avoid the limitations imposed by the spacecraft's docking interface on the spacecraft separation mechanism, and how to improve the reliability of spacecraft separation, are technical problems that urgently need to be solved by those skilled in the art. Summary of the Invention

[0006] This application provides a modular low-impact spacecraft separation device to avoid the spacecraft separation mechanism being limited by the support of the spacecraft docking interface, and also improves the reliability of spacecraft separation.

[0007] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0008] A modular, low-impact satellite-rocket separation device includes: a satellite docking support, a satellite-rocket separation spring, a rocket docking support, a pyrotechnic satellite storage box, explosive bolts, and a pyrotechnic rocket storage box. The satellite docking support has a first docking hole extending vertically in its middle portion. The pyrotechnic satellite storage box is located above the first docking hole, and its opening is fixed to the periphery of the first docking hole. The upper surface of the edge portion of the satellite docking support is used for fixed connection with a predetermined position on the docking end of the spacecraft. The rocket docking support has a second docking hole extending vertically in its middle portion. The pyrotechnic rocket storage box is located above the second docking hole. Below the second docking hole, and with its opening fixed to the periphery of the second docking hole, the lower surface of the edge portion of the rocket docking support is used for fixed connection with the predetermined position of the docking end of the rocket; the explosive bolt passes through the first docking hole and the second docking hole, with its tail located inside the pyrotechnic rocket storage box and its head located inside the pyrotechnic satellite storage box, and fixes the satellite docking support and the rocket docking support together; the lower end of the satellite-rocket separation spring is connected to the rocket docking support, the upper end of the satellite-rocket separation spring contacts the satellite docking support, and the rocket docking support and the satellite docking support press the satellite-rocket separation spring together.

[0009] In the modular low-impact satellite-rocket separation device described above, preferably, the middle portion of the satellite docking support is concave from top to bottom to form a first mounting cavity for accommodating a pyrotechnic satellite storage box; and the middle portion of the rocket docking support is concave from bottom to top to form a second mounting cavity for accommodating a pyrotechnic rocket storage box.

[0010] In the modular low-impact satellite-rocket separation device described above, preferably, the satellite docking support has multiple first fixing holes surrounding the first docking hole, and the lower end of the pyrotechnic satellite storage box has multiple second fixing holes; bolts are passed through the first and second fixing holes to fix the opening of the pyrotechnic satellite storage box to the area surrounding the first docking hole; the rocket docking support has multiple third fixing holes surrounding the second docking hole, and the upper end of the pyrotechnic rocket storage box has multiple fourth fixing holes; bolts are passed through the third and fourth fixing holes to fix the opening of the pyrotechnic rocket storage box to the area surrounding the second docking hole.

[0011] In the modular low-impact satellite-rocket separation device described above, preferably, the tail of the explosive bolt is thicker than the head of the explosive bolt to form a limiting step between the tail and the head of the explosive bolt; the limiting step is engaged below the second connecting hole to confine the tail of the explosive bolt within the pyrotechnic rocket storage box, and the head of the explosive bolt extends into the pyrotechnic satellite storage box after passing through the second docking hole and the first docking hole; a tapered sleeve is threaded onto the head of the explosive bolt, and the tapered sleeve is engaged above the first connecting hole to confine the head of the explosive bolt within the pyrotechnic satellite storage box.

[0012] In the modular low-impact star-rocket separation device described above, preferably, the cone sleeve has an internal thread, the head of the explosive bolt has an external thread, and the cone sleeve is screwed onto the head of the explosive bolt.

[0013] In the modular low-impact satellite-rocket separation device described above, preferably, the sidewall of the rocket docking support extends outward with a fixed wing, and the lower end of the satellite-rocket separation spring is connected to the upper surface of the fixed wing; the sidewall of the satellite docking support extends outward with a clamping wing, and the upper end of the satellite-rocket separation spring contacts the lower surface of the clamping wing.

[0014] In the modular low-impact satellite-rocket separation device described above, preferably, the upper surface of the fixed wing is fixedly connected to the lower end of the spring sleeve, and the spring sleeve has a cavity extending from top to bottom; the lower end of the separation spring connecting rod is inserted into the cavity of the spring sleeve from top to bottom, and the upper end of the separation spring connecting rod has an outwardly extending limiting wing, the upper surface of which contacts the lower surface of the clamping wing of the satellite docking support; the satellite-rocket separation spring is fitted onto the spring sleeve, and the upper end of the satellite-rocket separation spring contacts the lower surface of the limiting wing of the separation spring connecting rod.

[0015] In the modular low-impact star-rocket separation device described above, preferably, the lower end of the separation spring connecting rod has a limiting protrusion, which restricts the lower end of the separation spring connecting rod within the cavity of the spring sleeve.

[0016] In the modular low-impact satellite-rocket separation device described above, preferably, a vibration damping pad is fixed to the top inner surface of the pyrotechnic satellite storage box; and a vibration damping pad is fixed to the bottom inner surface of the pyrotechnic rocket storage box.

[0017] In the modular low-impact satellite-rocket separation device described above, preferably, an open-hole vibration damping pad is fixed on the lower surface of the vibration damping pad inside the pyrotechnic satellite storage box, and the middle part of the open-hole vibration damping pad has an energy-absorbing and vibration-damping hole that runs through it from top to bottom.

[0018] Compared with the aforementioned background technology, the modular low-impact spacecraft separation device provided in this application can avoid the spacecraft separation mechanism being limited by the support of the docking interface of the spacecraft, and also improves the reliability of spacecraft separation. Attached Figure Description

[0019] 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.

[0020] Figure 1This is a perspective view of the modular low-impact spacecraft separation device provided in the embodiments of this application;

[0021] Figure 2 This is a cross-sectional view of the modular low-impact spacecraft separation device provided in the embodiments of this application;

[0022] Figure 3 yes Figure 2 Enlarged view of part A in the image. Detailed Implementation

[0023] The embodiments of this application 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. Additionally, spatial relationship terms such as "upper," "lower," "left," "right," "front," and "rear" are used for ease of description to explain the positional relationship between two components. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application.

[0024] like Figure 1 , Figure 2 and Figure 3 As shown, this application provides a modular low-impact satellite-rocket separation device, including: a satellite docking support 1, a satellite-rocket separation spring 2, a rocket docking support 3, a pyrotechnic satellite storage box 4, explosive bolts 12 (selected and used according to the satellite weight), and a pyrotechnic rocket storage box 14.

[0025] The satellite docking support 1 has a first docking hole that runs through the top and bottom in the middle part. The pyrotechnic satellite storage box 4 is located above the first docking hole, and the opening of the pyrotechnic satellite storage box 4 is fixed to the periphery of the first docking hole. The upper surface of the edge part of the satellite docking support 1 is used to fix and connect to the predetermined position of the docking end of the spacecraft (e.g., satellite).

[0026] Optionally, the middle portion of the satellite docking support 1 is recessed from top to bottom to form a first mounting cavity, which is used to accommodate the pyrotechnic satellite storage box 4. That is, the pyrotechnic satellite storage box 4 is located within the first mounting cavity, and the opening of the pyrotechnic satellite storage box 4 is fixed to the periphery of the first docking hole. Alternatively, the satellite docking support 1 has multiple first fixing holes surrounding the first docking hole; the lower end of the pyrotechnic satellite storage box 4 has multiple second fixing holes; bolts pass through the first and second fixing holes to fix the opening of the pyrotechnic satellite storage box 4 to the periphery of the first docking hole. Still alternatively, a buffer pad 9 is provided above the second fixing holes. The bolt passes through the first and second fixing holes and then through the buffer pad 9, thereby absorbing energy and mitigating the impact of the broken portion on the satellite when collecting the broken head of the explosive bolt 12.

[0027] Optionally, a portion of the sidewall of the satellite docking support 1 is hollowed out, thereby reducing the weight of the satellite docking support 1. Alternatively, the edge portion of the satellite docking support 1 has multiple first connection holes running vertically through it, through which bolts pass to fix it to a predetermined position on the docking end of the spacecraft (e.g., a satellite). Still optional, the edge portion of the satellite docking support 1 has four first connection holes evenly distributed.

[0028] The middle part of the rocket docking support 3 has a second docking hole that runs through the top and bottom. The pyrotechnic rocket storage box 14 is located below the second docking hole, and the opening of the pyrotechnic rocket storage box 14 is fixed to the periphery of the second docking hole. The lower surface of the edge part of the rocket docking support 3 is used to fix and connect with the predetermined position of the docking end of the rocket.

[0029] Optionally, the middle portion of the rocket docking support 3 is recessed from bottom to top to form a second mounting cavity, which is used to accommodate the pyrotechnic rocket storage box 14. That is, the pyrotechnic rocket storage box 14 is located within the second mounting cavity, and the opening of the pyrotechnic rocket storage box 14 is fixed to the periphery of the second docking hole. Alternatively, the rocket docking support 3 has multiple third fixing holes surrounding the second docking hole; the upper end of the pyrotechnic rocket storage box 14 has multiple fourth fixing holes; bolts are passed through the third and fourth fixing holes to fix the opening of the pyrotechnic rocket storage box 14 to the periphery of the second docking hole. Still alternatively, washers 11 are provided below the third fixing holes and above the fourth fixing holes; bolts pass through the third fixing holes, washers 11, and fourth fixing holes to fix the pyrotechnic rocket storage box 14 to the rocket docking support 3.

[0030] Optionally, a portion of the sidewall of the rocket docking support 3 is hollowed out, thereby reducing the weight of the rocket docking support 3. Alternatively, the edge portion of the rocket docking support 3 has multiple second connecting holes running vertically through it, through which bolts pass to fix it to a predetermined position at the docking end of the rocket. Still optional, the edge portion of the rocket docking support 3 has eight first connecting holes evenly distributed.

[0031] The explosive bolt 12 passes through the first and second docking holes, with its tail inside the pyrotechnic rocket storage box 14 and its head inside the pyrotechnic satellite storage box 4, thus fixing the satellite docking support 1 and the rocket docking support 3 together. After the explosive bolt 12 detonates, the docking surfaces of the satellite docking support 1 and the rocket docking support 3 (i.e., the lower surface of the satellite docking support 1 and the upper surface of the rocket docking support 3) are unlocked and separated. After separation, the satellite docking support 1 remains on the satellite, and the rocket docking support 3 remains on the rocket. The upper broken portion of the explosive bolt 12 is collected and captured by the pyrotechnic satellite storage box 4 to prevent contamination of the satellite, and the lower broken portion of the explosive bolt 12 is collected and captured by the pyrotechnic rocket storage box 14 to prevent contamination of the rocket and other satellites.

[0032] Optionally, the tail of the explosive bolt 12 is thicker than its head, forming a limiting step between them. This limiting step is positioned below the second connecting hole, confining the tail of the explosive bolt 12 within the pyrotechnic rocket storage box 14. The head of the explosive bolt 12 passes through the second and first mating holes and extends into the pyrotechnic satellite storage box 4. To further confine the head of the explosive bolt 12 within the pyrotechnic satellite storage box 4, a tapered sleeve 8 is threaded onto the head of the explosive bolt 12. This tapered sleeve 8 is positioned above the first connecting hole, confining the head of the explosive bolt 12 within the pyrotechnic satellite storage box 4. Furthermore, the tapered sleeve 8 has internal threads, and the head of the explosive bolt 12 has external threads. The tapered sleeve 8 is screwed onto the head of the explosive bolt 12. After ignition, the tapered sleeve 8 secures the broken portion of the head of the explosive bolt 12, preventing it from splattering.

[0033] The lower end of the satellite-rocket separation spring 2 is connected to the rocket docking support 3, and the upper end of the satellite-rocket separation spring 2 is in contact with the satellite docking support 1. The rocket docking support 3 and the satellite docking support 1 press the satellite-rocket separation spring 2 together, so that after the explosive bolt 12 is unlocked, the separation energy is provided by the satellite-rocket separation spring 2 to push the satellite into the predetermined orbit.

[0034] Optionally, the sidewall of the rocket docking support 3 extends outward with a fixed wing, and the lower end of the rocket-satellite separation spring 2 is connected to the upper surface of the fixed wing; the sidewall of the satellite docking support 1 extends outward with a clamping wing 15, and the upper end of the rocket-satellite separation spring 2 contacts the lower surface of the clamping wing 15, thereby clamping the rocket-satellite separation spring 2. When the explosive bolt 12 is ignited, the rocket-satellite separation spring 2 acts on the lower surface of the clamping wing 15 to provide separation energy. Alternatively, the fixed wing extends outward from the sidewall of the rocket docking support 3 located on its lower surface, and the clamping wing 15 extends outward from the sidewall of the satellite docking support 1 located in its middle section. Still alternatively, to increase the strength of the clamping wing 15, the sidewall of the satellite docking support 1 also extends outward with a reinforcing rib, and the outer end of the reinforcing rib is fixed to the upper surface of the clamping wing 15, thereby increasing the strength of the clamping wing 15 through the reinforcing rib.

[0035] Furthermore, by adjusting the fixed position of the lower end of the satellite-rocket separation spring 2 relative to the upper surface of the fixed wing, the contact position between the upper end of the satellite-rocket separation spring 2 and the lower surface of the clamping wing 15 also changes. This alters the point of action of the satellite-rocket separation spring 2 on the satellite during unlocking and separation. Therefore, by adjusting the position of the satellite-rocket separation spring 2, the center of gravity can be balanced, achieving precise satellite orbit insertion. In addition, customized modifications can be made to a single satellite docking support 1 or rocket docking support 3, and different stiffness and model of satellite-rocket separation spring 2 (with different spring forces) can be selected to adjust for satellite eccentricity issues.

[0036] Optionally, the upper surface of the fixed wing is fixedly connected to the lower end of the spring sleeve 17, which has a cavity extending from top to bottom. The lower end of the separation spring connecting rod 16 is inserted into the cavity of the spring sleeve 17 from top to bottom. The upper end of the separation spring connecting rod 16 has an outwardly extending limiting wing, the upper surface of which contacts the lower surface of the clamping wing 15 of the satellite docking support 1. The satellite-rocket separation spring 2 is fitted onto the spring sleeve 17, and the upper end of the satellite-rocket separation spring 2 contacts the lower surface of the limiting wing of the separation spring connecting rod 16. After the explosive bolt 12 is unlocked, the separation spring connecting rod 16 moves upward under the action of the satellite-rocket separation spring 2, thereby pushing the clamping wing 15 of the satellite docking support 1 through the limiting wing of the separation spring connecting rod 16, providing separation energy for separation. Through the cooperation of the separation spring connecting rod 16 and the separation sleeve 17, the satellite-rocket separation spring 2 is guided, allowing it to provide separation energy along the direction of the separation spring connecting rod 16.

[0037] Optionally, to prevent the separation spring connecting rod 16 from detaching, the lower end of the separation spring connecting rod 16 has a limiting protrusion. The diameter of the middle portion of the separation spring connecting rod 16 is smaller than the diameter of the limiting protrusion. The lower end of the separation spring connecting rod 16 is restricted within the cavity of the spring sleeve 17 by the limiting protrusion, preventing the satellite-rocket separation spring 2 from detaching and contaminating the satellite. Alternatively, the outer circumferential surface of the limiting protrusion of the separation spring connecting rod 16 has external threads, the middle portion of the separation spring connecting rod 16 is a smooth rod, and the upper opening of the cavity of the spring sleeve 17 has internal threads. After the limiting protrusion of the separation spring connecting rod 16 is screwed into the upper opening of the cavity of the spring sleeve 17, the middle portion of the separation spring connecting rod 16 also extends into the cavity of the spring sleeve 17. During separation, the limiting protrusion with external threads at the lower end of the separation spring connecting rod 16 cannot pass through the spring sleeve 17. The limiting protrusion at the lower end of the separation spring connecting rod 16 is restricted within the cavity of the spring sleeve 17, thus preventing the star-rocket separation spring 2 from detaching from the contaminated satellite.

[0038] Based on the above, to facilitate satellite docking, the fixed wing of the rocket docking support 3 has a through-hole for mounting and limiting, the diameter of which is larger than the diameter of the lower opening of the cavity of the spring sleeve 17; the lower end face of the separation spring connecting rod 16 has an upwardly concave threaded connection cavity; when the satellite-rocket separation spring 2 is installed, after the separation spring 2 is compressed to its working stroke, the hexagon socket bolt 18 passes through the pad 19 and is screwed into the threaded connection cavity of the separation spring connecting rod 16; the diameter of the pad 19 is larger than the diameter of the lower opening of the cavity of the spring sleeve 17 and smaller than the diameter of the mounting and limiting hole of the fixed wing, so that the pad 19 is located inside the mounting and limiting hole and is locked outside the lower opening of the cavity of the spring sleeve 17, thus limiting the movement of the hexagon socket bolt 18 with the satellite-rocket separation spring 2. The separation spring connecting rod 16 is limited and locked in place by the hexagon socket bolt 18 and the pad 19. Optionally, a washer 20 is provided between the head of the socket head cap screw 18 and the spacer 19 to increase the bearing area of ​​the socket head cap screw 18. After the satellite docking support 1 and the rocket docking support 3 are connected by the explosive bolts 12, the socket head cap screw 18, spacer 19 and washer 20 are removed.

[0039] In addition, to absorb energy and mitigate the impact of the broken portion of the explosive bolt 12 on the satellite structure, a vibration damping pad 5 is fixed to the top inner surface of the pyrotechnic satellite storage box 4. After the explosive bolt 12 is ignited, the broken portion of its head impacts upwards, and the vibration damping pad 5 absorbs and reduces vibration. Furthermore, a perforated vibration damping pad 6 is fixed to the lower surface of the vibration damping pad 5. The perforated vibration damping pad 6 has a vertically penetrating energy-absorbing and vibration-damping hole in its middle portion. The broken portion of the head of the explosive bolt 12 impacts upwards into the energy-absorbing and vibration-damping hole, where the perforated vibration damping pad 6 absorbs and reduces vibration. Moreover, a storage pad 7 is fixed inside the energy-absorbing and vibration-damping hole of the perforated vibration damping pad 6. The storage pad 7 forms a conical storage hole within the energy-absorbing and vibration-damping hole, with the larger opening facing downwards, to accommodate the broken portion of the head of the explosive bolt 12 and absorb energy to reduce impact. Optionally, the storage pad 7 extends outwards from its storage opening to cover the lower surface of the perforated vibration damping pad 6.

[0040] In addition, in order to absorb energy and reduce the impact of the broken part of the explosive bolt 12 on the rocket structure, a vibration damping pad 13 is fixed on the bottom inner surface of the pyrotechnic rocket storage box 14. After the explosive bolt 12 is ignited, the broken part at its tail impacts downwards, and the vibration damping pad 13 absorbs energy and reduces vibration.

[0041] Since this application connects the satellite docking support 1 and the rocket docking support 3 together using explosive bolts 12, the portion of the explosive bolts 12 near the contact surface between the satellite docking support 1 and the rocket docking support 3 will bear shear force. Therefore, the head of the explosive bolts 12 is also fitted with a shear-resistant cone sleeve 10, which is located near the tail of the explosive bolts 12, to increase the shear resistance of the explosive bolts 12 after the satellite docking support 1 and the rocket docking support 3 are connected together.

[0042] This application allows for the selection of modular low-impact satellite-launcher separation devices of varying sizes and quantities based on the satellite's structural dimensions. This reduces the limitations imposed by the spacecraft structure on the separation device, improves compatibility and adaptability, and allows for optimized layout adjustments during later assembly. Furthermore, the modularly designed low-impact satellite-launcher separation device is highly versatile and can be quickly adapted to various spacecraft, significantly reducing design and manufacturing costs. Additionally, by capturing the explosive bolts after ignition, contamination of the spacecraft is avoided, effectively controlling the spacecraft's operating environment. Moreover, multiple impact reduction mechanisms significantly reduce impact loads, improving orbital insertion accuracy. Furthermore, by adjusting the position of the satellite-launcher separation springs, rapid adaptation to the center of gravity for use is achieved, further reducing design and manufacturing costs.

[0043] 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.

[0044] 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. A modular low-impact satellite-rocket separation device, characterized in that, include: Satellite docking support, satellite-rocket separation spring, rocket docking support, satellite storage box for pyrotechnics, explosive bolts, and rocket storage box for pyrotechnics; The satellite docking support has a first docking hole that runs through the top and bottom in the middle part. The pyrotechnic satellite storage box is located above the first docking hole, and its opening is fixed to the periphery of the first docking hole. The upper surface of the edge part of the satellite docking support is used to fix and connect with the predetermined position of the docking end of the spacecraft. The middle part of the rocket docking support has a second docking hole that runs through the top and bottom. The pyrotechnic rocket storage box is located below the second docking hole, and its opening is fixed to the periphery of the second docking hole. The lower surface of the edge part of the rocket docking support is used to fix and connect with the predetermined position of the docking end of the rocket. The explosive bolt passes through the first docking hole and the second docking hole, with its tail inside the pyrotechnic rocket storage box and its head inside the pyrotechnic satellite storage box, and fixes the satellite docking support and the rocket docking support together. The rocket docking support has fixed wings extending outward from its sidewall. The lower end of the rocket-satellite separation spring is connected to the upper surface of the fixed wings. The satellite docking support has clamping wings extending outward from its sidewall. The upper end of the rocket-satellite separation spring is in contact with the lower surface of the clamping wings. The rocket docking support and the satellite docking support clamp the rocket-satellite separation spring. By adjusting the fixed position of the lower end of the satellite-rocket separation spring and the upper surface of the fixed wing, the contact position between the upper end of the satellite-rocket separation spring and the lower surface of the pressure wing changes. When the satellite is unlocked and separated, the point of action of the satellite-rocket separation spring on the satellite changes, thereby balancing the center of mass. The upper surface of the fixed wing is fixedly connected to the lower end of the spring sleeve, which has a cavity running from top to bottom; the lower end of the separation spring connecting rod is inserted into the cavity of the spring sleeve from top to bottom, and the upper end of the separation spring connecting rod has an outwardly extending limiting wing, the upper surface of which contacts the lower surface of the clamping wing of the satellite docking support; the satellite-rocket separation spring is fitted onto the spring sleeve, and the upper end of the satellite-rocket separation spring contacts the lower surface of the limiting wing of the separation spring connecting rod; The lower end of the separating spring connecting rod has a limiting protrusion, which restricts the lower end of the separating spring connecting rod within the cavity of the spring sleeve. The fixed wing of the rocket docking support has a through-hole for mounting and limiting, the diameter of which is larger than the diameter of the lower opening of the cavity of the spring sleeve. The lower end face of the separation spring connecting rod has an upwardly concave threaded connection cavity. When the satellite-rocket separation spring is installed, after the separation spring is compressed to its working stroke, the hexagon socket head cap screw passes through the pad and is screwed into the threaded connection cavity of the separation spring connecting rod. The diameter of the pad is larger than the diameter of the lower opening of the cavity of the spring sleeve and smaller than the diameter of the mounting and limiting hole of the fixed wing. Thus, the pad is located inside the mounting and limiting hole and is locked outside the lower opening of the cavity of the spring sleeve. The pad restricts the movement of the hexagon socket head cap screw with the satellite-rocket separation spring. The hexagon socket head cap screw and the pad limit and lock the travel of the separation spring connecting rod. After the satellite docking support and the rocket docking support are connected by the explosive bolts, the hexagon socket head cap screw and the pad are removed.

2. The modular low-impact spacecraft separation device according to claim 1, characterized in that, The middle part of the satellite docking support is concave from top to bottom to form a first mounting cavity for accommodating the pyrotechnic satellite storage box; The middle part of the rocket docking support is concave from bottom to top to form a second mounting cavity for accommodating the rocket storage box for pyrotechnic components.

3. The modular low-impact spacecraft separation device according to claim 1 or 2, characterized in that, The satellite docking support has multiple first fixing holes, and the multiple first fixing holes surround the first docking hole. The lower end of the pyrotechnic satellite storage box has multiple second fixing holes. The opening of the pyrotechnic satellite storage box is fixed to the area around the first docking hole by bolts passing through the first and second fixing holes. The rocket docking support has multiple third fixing holes, which surround the second docking hole. The upper end of the pyrotechnic rocket storage box has multiple fourth fixing holes. The opening of the pyrotechnic rocket storage box is secured to the area around the second docking hole by bolts passing through the third and fourth fixing holes.

4. The modular low-impact spacecraft separation device according to claim 1 or 2, characterized in that, The tail of the explosive bolt is thicker than the head of the explosive bolt to form a limiting step between the tail and the head of the explosive bolt. The limiting step is used to lock the lower part of the second connecting hole so that the tail of the explosive bolt is confined inside the pyrotechnic rocket storage box, and the head of the explosive bolt extends into the pyrotechnic satellite storage box after passing through the second docking hole and the first docking hole. A tapered sleeve is threaded onto the head of the explosive bolt. The tapered sleeve is secured above the first connecting hole, thus confining the head of the explosive bolt within the pyrotechnic satellite storage box.

5. The modular low-impact spacecraft separation device according to claim 4, characterized in that, The tapered sleeve has internal threads, and the head of the explosion bolt has external threads. The tapered sleeve is screwed onto the head of the explosion bolt.

6. The modular low-impact spacecraft separation device according to claim 1 or 2, characterized in that, Vibration damping pads are fixed to the inner top surface of the pyrotechnic satellite storage box; vibration damping pads are fixed to the inner bottom surface of the pyrotechnic rocket storage box.

7. The modular low-impact spacecraft separation device according to claim 6, characterized in that, An open-hole vibration damping pad is fixed on the lower surface of the vibration damping pad inside the pyrotechnic satellite storage box. The middle part of the open-hole vibration damping pad has an energy-absorbing and vibration-damping hole that runs through it from top to bottom.

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