Spacecraft four-spring parallel guide satellite-rocket separation device

Abstract

This application relates to a spacecraft four-spring parallel-connected guiding satellite-rocket separation device, including compression springs, a guide frame, piston rods, locking pins, limiting cover plates, and a pusher frame. The guide frame has a square frame structure, with guide sleeves at its four corners. The piston rods are slidably assembled within the guide sleeves, with limiting holes at their bottom. The locking pins penetrate the bottom of the guide sleeves and the limiting holes. The piston rods have piston sections, and the bottom of the piston rods passes through the compression springs, which are located inside the guide sleeves. The four limiting cover plates and the guide sleeves are connected and fixed by a first fixing member. The four corners of the pusher frame are connected and fixed to the four piston rods by second fixing members. This application has the following foreseeable technical effects: the four compression springs are connected in parallel to form the separation energy source, and the four piston rods are connected in parallel to the pusher frame as a whole, ensuring that the piston rods always drive the pusher frame to propel the satellite for separation.

Description

Technical Field

[0001] This application relates to the field of spacecraft star-rocket separation technology, and in particular to a spacecraft four-spring parallel guide star-rocket separation device. Background Technology

[0002] With the rapid development of commercial spaceflight, the demand for low-cost, rapid, and reliable satellite launches is constantly increasing, and dual-satellite and multi-satellite launches are gradually becoming the norm. Reliable separation of the satellite and launch vehicle after orbit insertion is crucial, making the design of the separation scheme paramount. The satellite-launcher separation device is an important component of the satellite-launcher separation system, and its separation performance directly affects the satellite-launcher separation parameters and separation safety.

[0003] Traditional single-spring separation devices typically consist of a compression spring, spring housing, piston, cover, and process screw, mounted on the upper web of the adapter. The piston, under the action of the compression spring, presses against the satellite's base plate. When the satellite and launch vehicle unlock, the piston pushes the satellite apart using the potential energy stored in the compression spring, achieving separation by giving the satellite a relative separation velocity. During satellite research and design, satellite models undergo multiple iterations. Furthermore, during manufacturing, due to process deviations and assembly errors, the satellite's mass characteristics (including mass, center of mass, and moment of inertia) are constantly updated and changed.

[0004] The traditional single-spring push-through-satellite separation scheme has the disadvantage of poor adaptability. The launch vehicle adapter needs to constantly adjust the separation scheme to adapt to changes in the satellite's mass characteristics. This process brings great design difficulty and unnecessary workload to the launch vehicle, and seriously affects the design and manufacturing cycle of the launch vehicle adapter. In fact, the uncertainty of the satellite's center of mass deviation may lead to the risk of excessive separation attitude angular velocity and separation insecurity, which cannot meet the needs of commercial space launch. Summary of the Invention

[0005] To address the poor adaptability of single-spring separation devices, this application provides a spacecraft four-spring parallel guide star-rocket separation device.

[0006] This application provides a spacecraft four-spring parallel guide star-rocket separation device, which adopts the following technical solution:

[0007] A spacecraft four-spring parallel guide star-rocket separation device includes a compression spring, a guide frame, a piston rod, a locking pin, a limit cover, a pusher frame, a first fixing component, and a second fixing component.

[0008] The guide frame has a square frame structure, and guide sleeves are provided at the four corners of the guide frame along its height direction. There are four piston push rods, which are respectively installed in the four guide sleeves.

[0009] The piston push rod is slidably assembled inside the guide sleeve and slides in the height direction of the guide frame. A limit hole is provided at the bottom of the piston push rod. The locking pin passes through the bottom of the guide sleeve and the limit hole to prevent the piston push rod from sliding. A piston part is provided in the middle of the piston push rod. The bottom of the piston push rod passes through the compression spring. The compression spring is located inside the guide sleeve. The bottom of the compression spring abuts against the inner bottom wall of the guide sleeve, and the top of the compression spring abuts against the piston part.

[0010] The limiting cover plate is provided in four pieces. The four limiting cover plates and the top of the guide sleeve are connected and fixed by a number of first fixing members. The limiting cover plate is provided with a hole in the middle. The top of the piston push rod can pass through the hole, but the piston part cannot pass through the hole.

[0011] The push frame is rectangular, and its four corners are connected and fixed to the tops of the four piston rods by a number of second fasteners.

[0012] Furthermore, the first fixing component is an M5 screw, and the limiting cover plate is rectangular. Each limiting cover plate corresponds to four M5 screws, and the four M5 screws are respectively arranged at the four corners of the limiting cover plate.

[0013] Furthermore, the second fixing member is an M3 screw, with each piston push rod corresponding to two M3 screws.

[0014] Furthermore, the piston part is a cylindrical structure and forms a guide section. The piston part and the inner wall of the guide sleeve are slidably assembled. The top surface of the piston push rod is provided with a threaded hole that matches the M3 screw.

[0015] Furthermore, the outer peripheral wall of the piston push rod is provided with a plurality of first weight reduction grooves and a plurality of second weight reduction grooves. The first weight reduction grooves are located between the top surface of the piston push rod and the piston portion, and the second weight reduction grooves are located between the piston portion and the limiting hole. The plurality of first weight reduction grooves and the plurality of second weight reduction grooves are all uniformly and symmetrically arranged along the central axis of the piston push rod.

[0016] Furthermore, the limiting hole, the first weight-reducing groove, and the second weight-reducing groove are all oval in shape and are all arranged along the central axis of the piston push rod.

[0017] Furthermore, a ring is provided in the middle of the push frame to avoid contact with the satellite protrusion, and reinforcing ribs are provided between the ring and the four corners of the push frame, with the four reinforcing ribs arranged in an X shape.

[0018] Furthermore, each of the four corners of the push frame is provided with a rectangular protrusion for pushing the satellite to cause it to separate along the pushing direction.

[0019] Furthermore, a circular boss for limiting the pushing point is provided at the center of the upper surface of the rectangular protrusion, and two countersunk holes are also provided on the rectangular protrusion for the nuts of the two M3 screws to be accommodated respectively.

[0020] Furthermore, each of the four side plates of the guide frame is provided with four weight-reducing holes and forms an X-shaped support rib.

[0021] In summary, this application includes at least one of the following beneficial technical effects:

[0022] 1. The use of a four-spring parallel guiding separation design increases the satellite's pushing area and effectively improves the satellite's adaptability to center of mass deviation;

[0023] 2. The push-up frame design avoids the risk of push-up tilting caused by the spring force deviation between different springs, effectively reduces the satellite separation attitude angular velocity, and improves the safety of satellite-rocket separation;

[0024] 3. It has a certain degree of versatility and good adaptability, which greatly shortens the design cycle of the carrier adapter and significantly reduces the design cost. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure of the spacecraft's four-spring parallel guide star-rocket separation device in the embodiments of this application.

[0027] Figure 2 This is a cross-sectional view of the spacecraft's four-spring parallel guide star-rocket separation device in the embodiments of this application.

[0028] Figure 3 This is a schematic diagram of the guide frame structure in an embodiment of this application.

[0029] Figure 4 This is a schematic diagram of the pusher frame in an embodiment of this application.

[0030] Figure 5 This is a schematic diagram of the piston push rod in an embodiment of this application.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1. Compression spring; 2. Guide frame; 21. Guide sleeve; 22. Weight reduction hole; 23. X-shaped support rib; 3. Piston push rod; 31. Limiting hole; 32. Piston part; 34. Threaded hole; 35. First weight reduction groove; 36. Second weight reduction groove; 4. Locking pin; 5. Limiting cover plate; 6. Push frame; 61. Ring; 62. Reinforcing rib; 63. Rectangular protrusion; 64. Circular boss; 65. Countersunk hole; 7. M5 screw; 8. M3 screw. Detailed Implementation

[0033] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0034] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0035] It should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0036] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0037] The following is in conjunction with the appendix Figure 1-5 This application will be described in further detail.

[0038] This application discloses a spacecraft four-spring parallel guide satellite-rocket separation device. (Refer to...) Figure 1 and Figure 2 The spacecraft's four-spring parallel guide star-rocket separation device includes a compression spring 1, a guide frame 2, a piston push rod 3, a locking pin 4, a limit cover plate 5, a push frame 6, a first fixing component, and a second fixing component.

[0039] The guide frame 2 has a square frame structure. Guide sleeves 21 are arranged along its height direction at the four corners of the guide frame 2. Four piston push rods 3 are provided and installed in the four guide sleeves 21 respectively. The piston push rods 3 are slidably assembled in the guide sleeves 21 and the sliding direction is the height direction of the guide frame 2. The bottom of the piston push rod 3 is provided with a limit hole 31. The locking pin 4 passes through the bottom of the guide sleeve 21 and the limit hole 31 to prevent the piston push rod 3 from sliding. The piston part 32 is provided in the middle of the piston push rod 3. The diameter of the piston part 32 is significantly larger than the diameter of other parts of the piston push rod 3. The bottom of the piston push rod 3 passes through a compression spring 1. The compression spring 1 is located inside the guide sleeve 21. The bottom of the compression spring 1 abuts against the inner bottom wall of the guide sleeve 21, and the top of the compression spring 1 abuts against the piston part 32.

[0040] Four limiting cover plates 5 are provided. The four limiting cover plates 5 and the top of the guide sleeve 21 are connected and fixed by several first fixing members. A hole is provided in the middle of the limiting cover plate 5. The top of the piston push rod 3 can pass through the hole, but the piston part 32 cannot pass through the hole. The limiting cover plate 5 is used to limit the movement stroke of the piston push rod 3. The push frame 6 is rectangular. The four corners of the push frame 6 are connected and fixed to the top of the four piston push rods 3 by several second fixing members.

[0041] To solve the problems of insecure and inconvenient installation of the limiting cover plate 5, the first fixing component is an M5 screw 7. The limiting cover plate 5 is rectangular, and each limiting cover plate 5 corresponds to four M5 screws 7. The four M5 screws 7 are arranged at the four corners of the limiting cover plate 5, and a total of 16 M5 screws 7 are provided.

[0042] To address the issues of insecure and inconvenient installation between the piston push rod 3 and the push frame 6, the second fixing component is an M3 screw 8. Each piston push rod 3 corresponds to two M3 screws 8, and a total of eight M3 screws 8 are provided.

[0043] Reference Figure 1 and Figure 3 To ensure that the guide frame 2 has better structural strength and lighter weight, four weight-reducing holes 22 are provided on the four side plates of the guide frame 2 and X-shaped support ribs 23 are formed.

[0044] Reference Figure 1 and Figure 4 To ensure that the pusher frame 6 has better structural strength and lighter weight, a ring 61 is provided in the middle of the pusher frame 6 to avoid contact with the satellite protrusion. Reinforcing ribs 62 are provided between the ring 61 and the four corners of the pusher frame 6, and the four reinforcing ribs 62 are arranged in an X shape.

[0045] Each of the four corners of the push frame 6 is provided with a rectangular protrusion 63 for pushing the satellite to separate along the pushing direction. The center of the upper surface of the rectangular protrusion 63 is provided with a circular boss 64 for limiting the push point. The rectangular protrusion 63 is also provided with two countersunk holes 65 for the nuts of two M3 screws 8 to be accommodated respectively.

[0046] Reference Figure 1 and Figure 5 To address the issue of stable sliding of the piston rod 3 during pushing, the piston part 32 is cylindrical and forms a guide section. The piston part 32 and the inner wall of the guide sleeve 21 are slidably assembled. The top surface of the piston rod 3 is provided with a threaded hole 34 that matches the M3 screw 8. The central axes of the piston rod 3 and the guide sleeve 21 coincide and have high relative positional accuracy. The axial spacing tolerance is required to be less than 0.03 mm, and the hole roughness is small with high smoothness. Protrusions and excess particles are not allowed.

[0047] Reference Figure 1 and Figure 5 To reduce the weight of the piston rod 3 so that the compression spring 1 can drive its movement, the outer peripheral wall of the piston rod 3 is provided with a plurality of first weight reduction grooves 35 and a plurality of second weight reduction grooves 36. The first weight reduction grooves 35 are located between the top surface of the piston rod 3 and the piston part 32, and the second weight reduction grooves 36 are located between the piston part 32 and the limiting hole 31. The plurality of first weight reduction grooves 35 and the plurality of second weight reduction grooves 36 are all evenly and symmetrically arranged along the central axis of the piston rod 3. The limiting hole 31, the first weight reduction grooves 35 and the second weight reduction grooves 36 are all oval in shape and are all arranged along the central axis of the piston rod 3.

[0048] The implementation principle of a spacecraft four-spring parallel guide satellite-rocket separation device according to an embodiment of this application is as follows: After the locking pin 4 is removed, the compression spring 1 extends and outputs energy. The piston push rod 3 moves forward a certain distance with the push frame 6 until the piston part 32 moves to the limit cover plate 5 and is restricted from continuing to move, thereby stopping the piston push rod 3. The four compression springs 1 form a separation energy source in parallel, the four guide sleeves 21 are connected in parallel to form a guide frame 2, and the four piston push rods 3 are connected in parallel to the push frame 6 to ensure that the piston push rod 3 drives the push frame 6 to push the satellite to achieve separation.

[0049] The four-spring parallel guiding separation method increases the satellite pushing area and effectively improves the satellite's centroid deviation adaptability; the push frame 6 design avoids the risk of push tilting caused by the elastic force deviation between different springs, effectively reduces the satellite separation attitude angular velocity, and improves the safety of satellite-rocket separation; it has a certain degree of versatility and good adaptability, which greatly shortens the design cycle of the launch vehicle adapter and significantly reduces the design cost.

[0050] The separation device adapts to changes in the satellite's center of mass deviation by increasing the satellite's pushing area. Through configuration design and separation simulation verification, the simulation results show that the separation mechanism has good adaptability to satellite center of mass deviation, which is conducive to reducing the satellite's separation attitude angular velocity and meets the design requirements for satellite-rocket separation.

[0051] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A spacecraft four-spring parallel guide star-rocket separation device, characterized in that: Includes a compression spring (1), a guide frame (2), a piston push rod (3), a locking pin (4), a limit cover plate (5), a push frame (6), a first fixing member, and a second fixing member. The guide frame (2) is a square frame structure. The four corners of the guide frame (2) are provided with guide sleeves (21) arranged along its height direction. The piston push rod (3) is provided in four parts and is installed in the four guide sleeves (21) respectively. The piston push rod (3) is slidably fitted inside the guide sleeve (21) and the sliding direction is the height direction of the guide frame (2). The bottom of the piston push rod (3) is provided with a limiting hole (31). The locking pin (4) passes through the bottom of the guide sleeve (21) and the limiting hole (31) to prevent the piston push rod (3) from sliding. The piston push rod (3) is provided with a piston part (32) in the middle. The bottom of the piston push rod (3) passes through the compression spring (1). The compression spring (1) is located inside the guide sleeve (21). The bottom of the compression spring (1) abuts against the inner bottom wall of the guide sleeve (21), and the top of the compression spring (1) abuts against the piston part (32). The limiting cover plate (5) is provided in four pieces. The top of the four limiting cover plates (5) and the guide sleeve (21) are connected and fixed by a number of first fixing members. The limiting cover plate (5) has a hole in the middle. The top of the piston push rod (3) can pass through the hole and the piston part (32) cannot pass through the hole. The push frame (6) is rectangular, and the four corners of the push frame (6) are connected and fixed to the tops of the four piston push rods (3) by a number of second fasteners.

2. The spacecraft four-spring parallel guide star-rocket separation device according to claim 1, characterized in that: The first fixing component is an M5 screw (7), and the limiting cover plate (5) is rectangular. Each limiting cover plate (5) corresponds to four M5 screws (7), and the four M5 screws (7) are respectively located at the four corners of the limiting cover plate (5).

3. The spacecraft four-spring parallel guide star-rocket separation device according to claim 1, characterized in that: The second fastener is an M3 screw (8), and each piston push rod (3) corresponds to two M3 screws (8).

4. The spacecraft four-spring parallel guide star-rocket separation device according to claim 3, characterized in that: The piston part (32) is a cylindrical structure and forms a guide section. The piston part (32) and the inner wall of the guide sleeve (21) are slidably assembled. The top surface of the piston push rod (3) is provided with a threaded hole (34) that is compatible with the M3 screw (8).

5. The spacecraft four-spring parallel guide star-rocket separation device according to claim 4, characterized in that: The outer peripheral wall of the piston push rod (3) is provided with a plurality of first weight reduction grooves (35) and a plurality of second weight reduction grooves (36). The first weight reduction grooves (35) are located between the top surface of the piston push rod (3) and the piston part (32), and the second weight reduction grooves (36) are located between the piston part (32) and the limiting hole (31). The plurality of first weight reduction grooves (35) and the plurality of second weight reduction grooves (36) are all uniformly and symmetrically arranged along the central axis of the piston push rod (3).

6. The spacecraft four-spring parallel guide star-rocket separation device according to claim 5, characterized in that: The limiting hole (31), the first weight reduction groove (35) and the second weight reduction groove (36) are all oval in shape and are arranged along the central axis of the piston push rod (3).

7. The spacecraft four-spring parallel guide star-rocket separation device according to claim 1, characterized in that: The push frame (6) has a ring (61) in the middle to avoid contact with the satellite protrusion. There are reinforcing ribs (62) between the ring (61) and the four corners of the push frame (6), and the four reinforcing ribs (62) are arranged in an X shape.

8. The spacecraft four-spring parallel guide star-rocket separation device according to claim 3, characterized in that: The four corners of the push frame (6) are each provided with a rectangular protrusion (63) for pushing the satellite to make the satellite separate along the pushing direction.

9. The spacecraft four-spring parallel guide star-rocket separation device according to claim 8, characterized in that: The rectangular protrusion (63) has a circular boss (64) at the center of its upper surface for limiting the push point. The rectangular protrusion (63) also has two countersunk holes (65) for the nuts of the two M3 screws (8) to be received.

10. The spacecraft four-spring parallel guide star-rocket separation device according to claim 1, characterized in that: The guide frame (2) has four weight-reducing holes (22) on its four side plates and X-shaped support ribs (23).

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