A spear attachment device with a spring honeycomb combined shock-absorbing structure

Abstract

The present invention is a spear attachment device with a spring honeycomb combined shock-absorbing structure. It comprises a cylindrical shell with a flange, a honeycomb panel arranged at the bottom of the shell, and a disk arranged inside the shell and on the honeycomb panel. The disk is fixed by a baffle connected to the flange of the shell. A groove is provided on the disk at a position corresponding to the baffle. A spring is provided in the groove. One end of the spring is connected to the lower surface of the baffle, and the other end of the spring is connected to the bottom of the groove of the disk. A plurality of flying spears are evenly provided on the outer surface of the disk. In the present invention, when the flying spear in the spear attachment device collides with the penetrating space debris, the reaction force generated is transmitted along the flying spear to the spring honeycomb combined shock-absorbing structure. The huge reaction force causes the spring in the spring honeycomb combined shock-absorbing structure to undergo elastic deformation, and the honeycomb panel is squeezed and deformed as a whole by the reaction force, thereby achieving the purpose of overall buffering and shock absorption of the spear attachment device.

Description

Technical Field

[0001] The present invention belongs to the technical field of active space debris removal, and in particular relates to a spear attachment device with a spring honeycomb combined shock-absorbing structure. Background Art

[0002] With the continuous advancement of science and technology, human exploration of space has become increasingly frequent. As a result, more and more spacecraft and space payloads are being launched into outer space. Each launch generates a large amount of rocket debris and abandoned satellites, which have become a significant source of space debris. Due to the secondary debris effect of space debris, collisions between debris in space can generate more space debris, leading to a growing amount of space debris. Furthermore, many abandoned satellites and defunct spacecraft are not promptly decommissioned or dismantled, but remain in orbit. This debris poses a high collision risk, further exacerbating the space debris problem. Proper satellite decommissioning and dismantling methods can effectively reduce the generation of debris. To address the rapid increase in space debris, the development of active space debris removal technologies is a top priority. This can reduce the amount of space debris, minimize the probability of collisions, improve the safety of space activities, and ensure the sustainable use of space resources.

[0003] The existing space debris cleaning technologies mainly include rope net capture, spear capture, drag-enhanced deorbit, and robotic arm capture. Among them, spear capture is a more common way to actively remove space debris. At the moment when the spear captures the space debris, the huge reaction force generated by the strong collision between the spear and the space debris will be transmitted along the spear to the rear of the spear device, which may cause damage or destruction to some components in the device at the rear of the spear. In order to solve the problem of large reaction force of the spear collision, some spring shock-absorbing mechanisms have been proposed at this stage. Since the current spear attachment device is generally a single spear device, the number of springs used in the shock-absorbing mechanism of this single spear device is limited and the stiffness is often large. Therefore, during the collision of the spear, the shock-absorbing mechanism does not play a good shock-absorbing and buffering role. In summary, although the spear devices in the existing spear space debris capture technology are of various types and have some technical basis, they all have two common problems:

[0004] 1. Most of the existing spear attachment devices are single-spear mechanisms. After penetrating the space debris, the spear has a small contact area and does not have a good adhesion ability. The flying spear is easily affected by external vibrations and detached.

[0005] 2. A small number of flying spear devices are equipped with a buffering and shock-absorbing device. The buffering and shock-absorbing structure simply uses a single large spring to absorb shock. At the moment when the flying spear captures space debris, it cannot play a good role in buffering and shock-absorbing. Summary of the Invention

[0006] The purpose of the present invention is to provide a spear attachment device with a spring honeycomb combined shock-absorbing structure. The device has multiple spears and a strong penetration attachment structure, and uses a spring honeycomb combined shock-absorbing structure to achieve the purpose of buffering and shock-absorbing during the impact and penetration process of the flying spears.

[0007] The technical solution for achieving the purpose of the present invention is: a spear attachment device with a spring honeycomb combined shock-absorbing structure, comprising a cylindrical shell with a flange flange, a honeycomb panel arranged at the bottom of the shell, and a disc arranged inside the shell and on the honeycomb panel. The disc is fixed by a baffle connected to the flange flange of the shell. A groove is provided on the disc at a position corresponding to the baffle. A spring is provided in the groove. One end of the spring is connected to the lower surface of the baffle, and the other end of the spring is connected to the bottom of the disc groove. A plurality of flying spears are evenly arranged on the outer surface of the disc.

[0008] Furthermore, there are four flying spears in number, which are evenly distributed on the disc in a circular shape, and the flying spears are connected to the disc by threads.

[0009] Furthermore, the spear head is in the shape of a pointed cone, and the length-to-diameter ratio of the spear is not less than 10:1.

[0010] Furthermore, the outer surface of the bottom of the shell is connected to components by screws.

[0011] Furthermore, the number of the springs and the number of the blocking pieces are both 4, and they are evenly distributed along the circumference of the disc.

[0012] Furthermore, the baffle and the flange of the housing are connected by bolts.

[0013] A method for space debris cleaning using the spear attachment device is provided on a parent satellite platform. The method comprises the following steps:

[0014] Step (1): The mother satellite platform identifies the space debris and moves towards it;

[0015] Step (2): The mother star platform arrives at the designated capture position and launches a spear attachment device towards the space debris. The flying spear penetrates the space debris and attaches to it.

[0016] Step (3): The reaction force generated by the collision is transmitted to the disc along the flying spear, and the disc applies an extrusion force to the honeycomb panel, causing the honeycomb panel to be deformed by the extrusion, thereby achieving the initial absorption and unloading of the reaction force; the remaining reaction force is transmitted to the spring, causing the spring to undergo axial elastic deformation, thereby achieving the secondary absorption and unloading of the reaction force.

[0017] Compared with the prior art, the present invention has the following significant advantages:

[0018] (1) The present invention adopts a flying spear design with a pointed cone shape and a large aspect ratio, and there are four flying spears in total, which ensures the strong adhesion ability of the entire flying spear mechanism, so that the spear attachment device can attach to various types of space debris and has a wide range of applications.

[0019] (2) The present invention designs a spear attachment device with a spring honeycomb combined shock-absorbing structure. Relying on the extrusion deformation of the honeycomb plate, the reaction force generated when the spear attachment device collides with space debris can be initially absorbed and unloaded, and the elastic deformation of the spring device can secondarily absorb and unload the reaction force. The spring honeycomb combined shock-absorbing structure designed in this way can achieve the purpose of overall buffering and shock absorption of the spear attachment device to the greatest extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Schematic diagram of the spear attachment device with a spring honeycomb combined shock-absorbing structure of the present invention.

[0021] Figure 2 This is a cross-sectional view of the spear attachment device with a spring honeycomb combined shock-absorbing structure of the present invention.

[0022] Figure 3 Workflow diagram for clearing space debris for the spear attachment device.

[0023] Description of reference numerals:

[0024] 1-flying spear penetration part, 2-spring honeycomb combined shock-absorbing structure, 3-flying spear, 4-bolt, 5-blocking plate, 6-spring, 7-disc, 8-honeycomb plate, 9-screw, 10-housing. DETAILED DESCRIPTION

[0025] The present invention is further described in detail below with reference to the accompanying drawings.

[0026] The present invention aims to provide a multi-spear, high-penetration attachment structure that utilizes a spring-honeycomb composite shock-absorbing structure to achieve cushioning and shock reduction during the impact and penetration of the spears. When the spear penetrating portion 1 of the spear attachment device strikes and penetrates space debris, the resulting reaction force is transmitted along the spear to the spring-honeycomb composite shock-absorbing structure 2. This immense reaction force causes the springs 6 in the spring-honeycomb composite shock-absorbing structure 2 to elastically deform, and the honeycomb panel 8, under the reaction force, undergoes compression deformation as a whole, thereby achieving the overall cushioning and shock-absorbing purpose of the spear attachment device.

[0027] like Figure 1 、 Figure 2As shown, the present invention discloses a spear attachment device with a spring-honeycomb combined shock-absorbing structure, which mainly comprises a spear penetration portion 1 and a spring-honeycomb combined shock-absorbing structure 2. The spear penetration portion 1 is mainly implemented by a spear 3. The spring-honeycomb combined shock-absorbing structure 2 mainly comprises a spring 6, a disk 7, and a honeycomb panel. When the mother satellite platform identifies space debris, the spear attachment device is launched to capture it. The spear 3 penetrates the space debris and firmly adheres to it. The reaction force generated by the impact is transmitted along the spear 3 to the disk 7. The disk 7 applies a compressive force to the honeycomb panel 8, causing it to deform and initially absorb and unload the reaction force. The remaining reaction force is then transmitted to the spring 6, causing it to undergo axial elastic deformation, thereby achieving secondary absorption and unloading of the reaction force. This combined shock-absorbing structure maximizes the overall buffering and shock absorption of the spear attachment device, protecting the rear components of the spear attachment device from damage due to vibration.

[0028] The spear attachment device, featuring a spring honeycomb composite shock-absorbing structure, consists of four flying spears 3, evenly distributed in a circular pattern on the front disc 7. These spears are threadedly connected to the disc 7, ensuring a secure connection. The spears 3 feature a pointed, conical tip with a large aspect ratio, ensuring excellent penetration of the target plate. The four spears 3 provide robust attachment capabilities, making the spear attachment device suitable for penetrating a wide range of targets and providing a wider range of applications.

[0029] The spring-honeycomb composite shock-absorbing structure 2 comprises one honeycomb panel 8, mounted within a housing 10. When the lance attachment device collides with space debris, the resulting reaction force is transmitted along the lance 3 to the disc 7. The disc 7 applies an axial compressive force to the honeycomb panel 8, causing it to deform. This initially absorbs and unloads the reaction force generated by the lance attachment device's collision, ultimately achieving a primary cushioning and shock-absorbing effect, protecting components connected to the rear of the screw 9 from damage due to vibration.

[0030] The spring honeycomb composite shock-absorbing structure 2 comprises four springs 6, evenly distributed in a circular pattern on the front disc 7 of the spear attachment device. One end of the spring 6 is connected to the baffle 5, and the other end is connected to the disc 7. When the spear 3 collides with the target, the reaction force generated is first buffered and damped by the honeycomb panel 8. The remaining reaction force is then transferred to the spring 6, causing it to undergo axial elastic deformation, thereby achieving a secondary buffering and shock absorption effect for the entire spear attachment device. The baffle 5 not only ensures the stable axial elastic deformation of the spring 6, but also prevents the disc 7 from detaching during axial displacement, thus acting as a limiter.

[0031] As above Figure 3This is a workflow diagram for clearing space debris using a spear attachment device with a spring-honeycomb combined shock-absorbing structure. The specific workflow is as follows: Phase 1: The mothership platform identifies space debris and approaches it. Phase 2: The mothership platform reaches the designated capture position and launches the spear attachment device toward the space debris, capturing it. Phase 3: The spring-honeycomb combined shock-absorbing structure absorbs and unloads the reaction force generated by the collision, thereby achieving cushioning and shock reduction.

Claims

1. A method for space debris cleaning using a spear attachment device with a spring honeycomb combined shock-absorbing structure, characterized in that: The spear attachment device with a spring honeycomb combined shock-absorbing structure comprises a cylindrical shell (10) with a flange flange, a honeycomb plate (8) arranged at the bottom of the shell, and a disc (7) arranged in the shell and on the honeycomb plate, wherein the disc (7) is fixed by a baffle (5) connected to the flange flange of the shell, a groove is provided at a position corresponding to the baffle (5) on the disc (7), a spring (6) is arranged in the groove, one end of the spring (6) is connected to the lower surface of the baffle (5), and the other end of the spring (6) is connected to the bottom of the disc groove, and the outer surface of the disc (7) is A plurality of flying spears (3) are evenly arranged; the flying spears (3) are four in number and are evenly distributed on the disc (7) in a circular shape, and the flying spears (3) and the disc (7) are connected by threads; the spearheads of the flying spears (3) are in the shape of a pointed cone, and the length-to-diameter ratio of the flying spears (3) is not less than 10:1; the outer surface of the bottom of the shell (10) is connected to the components by screws (9); the number of springs and baffles is four and evenly distributed along the circumference of the disc; the baffles and the flange of the shell are connected by bolts; the spear attachment device is arranged on the mother satellite platform, and the method comprises the following steps: Step (1): The mother satellite platform identifies the space debris and moves towards it; Step (2): The mother star platform arrives at the designated capture position and launches the spear attachment device towards the space debris. The flying spear (3) penetrates the space debris and attaches to it. Step (3): The reaction force generated by the collision is transmitted to the disc (7) along the flying spear (3), and the disc (7) applies an extrusion force to the honeycomb plate (8), so that the honeycomb plate (8) is deformed by the extrusion, thereby achieving preliminary absorption and unloading of the reaction force; the remaining reaction force is transmitted to the spring (6), so that the spring (6) undergoes axial elastic deformation, thereby achieving secondary absorption and unloading of the reaction force.

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