A foldable space debris reclaimer based on a launch vehicle

Abstract

This application relates to the field of aerospace technology, and in particular to a foldable space debris reclaimer for use in launch vehicles, comprising: a launch vehicle upper stage, a one-way rotating structure, a reclaimer fabric panel, a reclaimer frame, and a folding and unfolding mechanism; the upper part of the upper stage is cylindrical, and the lower part of the upper stage is conical, with the lower end of the upper stage connected to the upper end of the lower stage, and the conical surface facing the upper part of the upper stage; the one-way rotating structure is fixed at the junction of the upper and lower parts of the upper stage; the inner end of the reclaimer frame is hinged to the one-way rotating structure, and the left and right ends of the folding and unfolding mechanism are respectively connected to the outer ends of two adjacent reclaimer frames; the folding and unfolding mechanism, the two adjacent reclaimer frames, and the corresponding positions at the junction of the upper and lower parts of the upper stage form an arrangement frame; the edge of the reclaimer fabric panel is fixedly connected to the arrangement frame, and each piece of reclaimer fabric panel is stacked between the arrangement frames.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a foldable space debris reclaimer based on a launch vehicle. Background Technology

[0002] With the increasing number of launch vehicles each year, the amount of space debris generated is also increasing, and the density of space debris is becoming increasingly high, posing a significant safety hazard to space activities. Therefore, space debris disposal is necessary. Space debris disposal generally involves two methods: monitoring and destruction. By monitoring the trajectory of space debris, a spacecraft is launched to guide the space debris in a predetermined orbit, changing its trajectory so that it is destroyed through friction with the atmosphere.

[0003] Existing methods for disposing of space debris require the separate launch of spacecraft, which generates space debris in the process. Furthermore, these launched spacecraft have considerable weight and size, occupying space and carrying capacity of the launch vehicle, significantly increasing the cost of space debris disposal and reducing launch efficiency.

[0004] Therefore, how to reduce the space and carrying capacity occupied by spacecraft that destroy space debris, and how to reduce the generation of space debris and lower the cost of space debris disposal are technical problems that urgently need to be solved by those skilled in the art. Summary of the Invention

[0005] This application provides a foldable space debris reclaimer for use on launch vehicles to reduce their weight and space occupation. It can be applied to daily launch vehicle scenarios, increase the number of launches, reduce the generation of space debris, and lower the cost of space debris disposal.

[0006] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0007] A foldable space debris reclaimer based on a launch vehicle includes: a launch vehicle upper stage, multiple unidirectional rotating structures, multiple reclaimer fabric panels, multiple reclaimer frames, and multiple folding and unfolding mechanisms. The launch vehicle upper stage includes an upper stage and a lower stage. The upper stage is cylindrical, and the lower stage is conical. The lower end of the upper stage is connected to the upper end of the lower stage, with the conical surface facing the upper stage. All unidirectional rotating structures are fixed at the junction of the upper and lower stages, and adjacent unidirectional rotating structures are spaced apart. The inner end of a reclaimer frame is hinged to a unidirectional rotating structure. The left and right ends of a folding and unfolding mechanism are respectively connected to the outer ends of two adjacent reclaimer frames. A folding and unfolding mechanism, two adjacent reclaimer frames, and the corresponding positions at the junction of the upper and lower stages form an arrangement frame. The edge of a reclaimer fabric panel is fixedly connected to an arrangement frame, and each reclaimer fabric panel is stacked between the arrangement frames.

[0008] As described above, in the foldable space debris reclaimer based on a launch vehicle, preferably, each folding and unfolding mechanism is shortened, and the circle formed by all the folding and unfolding mechanisms is reduced; all reclaimer frames, folding and unfolding mechanisms, and reclaimer fabric surfaces are attached to the conical surface of the lower part of the upper stage.

[0009] As described above, in the foldable space debris reclaimer based on a launch vehicle, preferably, each folding and unfolding mechanism is elongated, and the circle formed by all the folding and unfolding mechanisms is expanded; all the folding and unfolding mechanisms are away from the conical surface of the lower part of the upper stage, all the reclaimer frames rotate around a one-way rotating structure so that they are perpendicular to the cylindrical surface of the upper part of the upper stage, and the stacked reclaimer fabric is away from the conical surface of the lower part of the upper stage, so that the arrangement frame and the reclaimer fabric form a circular net.

[0010] As described above, in the foldable space debris reclaimer based on a launch vehicle, preferably, four unidirectional rotating structures are uniformly fixed at the junction of the upper part and the lower part of the upper stage, and four reclaimer frames are hinged to the four unidirectional rotating structures.

[0011] In the aforementioned foldable space debris reclaimer based on a launch vehicle, preferably, the unidirectional rotating structure is provided with auxiliary rotational force by a spring, which drives the reclaimer frame to rotate.

[0012] As described above, in the foldable space debris reclaimer based on a launch vehicle, preferably, a fixing groove is provided in the unidirectional rotating structure, and a limiting protrusion is provided at the inner end of the reclaimer frame. When the reclaimer frame rotates around the unidirectional rotating structure until it is perpendicular to the cylindrical surface of the upper stage, the limiting protrusion is engaged in the fixing groove.

[0013] As described above, the foldable space debris reclaimer based on a launch vehicle preferably includes a main frame and a secondary frame; the inner end of the main frame is hinged to a one-way rotating structure, the outer end of the main frame is vertically fixed to the middle position of the secondary frame, the left end of the secondary frame is connected to the right end of the folding and unfolding mechanism located on its left, and the right end of the secondary frame is connected to the left end of the folding and unfolding mechanism located on its right.

[0014] As described above, the foldable space debris reclaimer based on a launch vehicle preferably includes a folding and unfolding mechanism comprising: a spring, an unfolding rope, a rotary guide hinge, and a locking rope; wherein both ends of the sub-frame have inwardly recessed spring cylinders; one end of a spring is fixedly installed inside the spring cylinder at the left end of a sub-frame, and the other end of the spring extends to the left and connects to the right end of the unfolding rope; one end of another spring is fixedly installed inside the spring cylinder at the right end of the opposite sub-frame, and the other end of the spring extends to the right and connects to the left end of the unfolding rope; both ends of the rotary guide hinge are respectively connected to the spring cylinders on both sides, and the unfolding rope passes through the middle of the rotary guide hinge; both ends of the locking rope are respectively connected to the springs on both sides, and the middle portion of the locking rope is connected to the shearing device of the upper stage of the launch vehicle.

[0015] As described above, in the foldable space debris reclaimer based on a launch vehicle, preferably, the locking rope is tightened, the spring is extended, and the rotary guide hinge is in a stable folded state, so that all reclaimer frames, folding and unfolding mechanisms, and reclaimer fabric surfaces are attached to the conical surface of the lower part of the upper stage.

[0016] In the aforementioned foldable space debris reclaimer based on a launch vehicle, preferably, a shearing device cuts the locking rope, a spring shortens and pulls the unfolding rope to tighten, and a rotary guide hinge moves along the guide direction to unfold, forming a circle with the sub-frame of the reclaimer skeleton.

[0017] Compared to the aforementioned background technologies, the foldable space debris reclaimer based on launch vehicles proposed in this application can reduce the space and carrying capacity occupied by spacecraft used to dispose of space debris, and can also reduce the generation of space debris and lower the cost of space debris disposal. Attached Figure Description

[0018] 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.

[0019] Figure 1This is a schematic diagram based on the foldable space debris reclaimer used in the launch vehicle being in a folded state;

[0020] Figure 2 This is a schematic diagram based on the unfolded state of the foldable space debris reclaimer used in the launch vehicle;

[0021] Figure 3 This is a schematic diagram of the folding and unfolding mechanism based on the foldable space debris reclaimer used in launch vehicles. Detailed Implementation

[0022] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0023] like Figure 1 and Figure 2 As shown, this application provides a foldable space debris reclaimer based on a launch vehicle, including: a launch vehicle upper stage 110, multiple unidirectional rotating structures 120, multiple reclaimer fabric panels 130, multiple reclaimer frames 140, and multiple folding and unfolding mechanisms 150.

[0024] The upper stage 110 of the launch vehicle includes an upper stage 111 and a lower stage 112. The upper stage 111 is cylindrical in shape, and the lower stage 112 is conical in shape. The lower end of the upper stage 111 is connected to the upper end of the lower stage 112, and the conical surface faces the upper stage 111.

[0025] All unidirectional rotating structures 120 are fixed at the junction of the upper part 111 and the lower part 112 of the upper stage, and are spaced apart from each other. The inner end of a recycler frame 140 is hinged to a unidirectional rotating structure 120, and the left and right ends of a folding and unfolding mechanism 150 are respectively connected to the outer ends of two adjacent recycler frames 140. Thus, the corresponding positions of a folding and unfolding mechanism 150, two adjacent recycler frames 140 and the junction of the upper part 111 and the lower part 112 of the upper stage form an arrangement frame. The edge of a recycler fabric 130 is fixedly connected to an arrangement frame, and each recycler fabric 130 is stacked between the arrangement frames.

[0026] like Figure 1As shown, each folding and unfolding mechanism 150 is shortened, reducing the circle formed by all the folding and unfolding mechanisms 150. This causes all the recoverer frames 140 and folding and unfolding mechanisms 150 to fit onto the conical surface of the lower part 112 of the upper stage, and consequently, the recoverer fabric 130 also fits onto the conical surface of the lower part 112 of the upper stage. This reduces the space occupied by the launch vehicle during launch.

[0027] like Figure 2 As shown, the upper stage 110 of the launch vehicle is equipped with remote sensing equipment, attitude and orbit control equipment, and state change equipment. After the upper stage 110 completes its mission, the remote sensing equipment receives ground commands, and the state change equipment extends each folding and unfolding mechanism 150, thereby expanding the circle formed by all the folding and unfolding mechanisms 150. This causes all the folding and unfolding mechanisms 150 to move away from the conical surface of the lower part 112 of the upper stage. All the recoverer frames 140 rotate around the one-way rotating structure 120, making it perpendicular to the cylindrical surface of the upper part 111 of the upper stage. The stacked recoverer fabric 130 moves away from the conical surface of the lower part 112 of the upper stage, so that the arrangement frame and the recoverer fabric 130 form a circular net. The attitude and orbit control equipment adjusts its trajectory to approach the location of the space debris to capture it. After capturing a predetermined amount of space debris, the attitude and orbit control equipment adjusts its trajectory, causing the upper stage 110 of the launch vehicle to carry the space debris and undergo atmospheric friction to complete its destruction.

[0028] Optionally, four unidirectional rotating structures 120 are evenly fixed at the junction of the upper part 111 and the lower part 112 of the upper stage, thus the foldable space debris reclaimer has four reclaimer frames 140 and four reclaimer fabric panels 130. Furthermore, the number of unidirectional rotating structures 120 and reclaimer frames 140 can be configured according to the shape and size of the conical surface to maintain stability after unfolding. Alternatively, the unidirectional rotating structure 120 has an auxiliary rotational force function, which can be provided by a spring to drive the reclaimer frames 140 to rotate. Still alternatively, the unidirectional rotating structure 120 has a fixing groove, and the inner end of the reclaimer frame 140 has a limiting protrusion. When the reclaimer frame 140 rotates around the unidirectional rotating structure 120 until it is perpendicular to the cylindrical surface of the upper part 111 of the upper stage, the limiting protrusion engages in the fixing groove to fix the movement height of the reclaimer frame 140, keeping the foldable space debris reclaimer in the unfolded state.

[0029] Optionally, each reclaimer frame 140 includes a main frame 141 and a secondary frame 142; the inner end of the main frame 141 is hinged to the one-way rotating structure 120, the outer end of the main frame 141 is vertically fixed to the middle position of the secondary frame 142, the left end of the secondary frame 142 is connected to the right end of the folding and unfolding mechanism 150 located to its left, and the right end of the secondary frame 142 is connected to the left end of the folding and unfolding mechanism 150 located to its right. Alternatively, the reclaimer frame 140 uses carbon fiber composite material, which reduces weight while increasing strength. Still optional, the reclaimer fabric 130 is made of Kevlar fiber cloth, whose strength and tear resistance ensure the reliability of the space debris capture net, and the reclaimer fabric 130 is a non-metallic material, featuring light weight, small footprint, and low processing cost.

[0030] Based on the above, such as Figure 3 As shown, the folding and unfolding mechanism 150 includes: a spring 151, an unfolding rope 152, a rotary guide hinge 153, and a locking rope 154; wherein, both the left and right ends of the sub-frame 142 have inwardly recessed spring cylinders 1421; one end of a spring 151 is fixedly installed inside the spring cylinder 154 at the left end of a sub-frame 142, and the other end of the spring 151 extends to the left and connects to the right end of the unfolding rope 152; one end of another spring 151 is fixedly installed inside the spring cylinder 154 at the right end of the opposite sub-frame 142, and the other end of the spring 151 extends to the right and connects to the right end of the unfolding rope 152. The left end of the deployment rope 152 is connected to the spring cylinders 1421 on both sides of the rotary guide hinge 153, and the deployment rope 152 passes through the middle of the rotary guide hinge 153; the two ends of the locking rope 154 are connected to the springs 151 on both sides, and the springs 151 are tightened to be in an extended state. The state-changing device of the upper stage 110 of the launch vehicle is a shearing device. The middle part of the locking rope 154 is connected to the shearing device of the upper stage 110 of the launch vehicle. The locking rope 154 is cut by the shearing device, thereby shortening the spring 151 and tightening the deployment rope 152.

[0031] In the folded state, the locking cord 154 tightens the spring 151, causing the spring 151 to extend and its elastic force to reach a predetermined value. The locking cord 154 also keeps the rotary guide hinge 153 in a stable folded state, so that all the reclaimer frames 140, the folding and unfolding mechanism 150 and the reclaimer fabric 130 are attached to the conical surface of the lower part 112 of the upper stage.

[0032] When in the unfolded state, the shearing device receives a command to cut the locking rope 154, the spring 151 shortens, and at the same time pulls the unfolding rope 152 to tighten, causing the rotary guide hinge 153 to move along the guide direction. Under the force of the spring 151, the rotary guide hinge 153 is pulled and unfolded into an arc state, forming a ring with the sub-frame 142 of the reclaimer frame 140, thus completing the unfolding action. Through the elastic force of the spring 151, the unfolding time can be reduced and the self-adaptive capability can be improved.

[0033] 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.

[0034] 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 foldable space debris reclaimer based on a launch vehicle, characterized in that, include: The launch vehicle upper stage, multiple unidirectional rotating structures, multiple recoverer fabric panels, multiple recoverer frames, and multiple folding and unfolding mechanisms; The upper stage of the launch vehicle includes an upper stage and a lower stage. The upper stage is cylindrical in shape, and the lower stage is conical in shape. The lower end of the upper stage is connected to the upper end of the lower stage, and the conical surface faces the upper stage. All unidirectional rotary structures are fixed at the junction of the upper part of the upper stage and the lower part of the upper stage, and are spaced apart from each other. The inner end of a reclaimer frame is hinged to a one-way rotating structure, and the left and right ends of a folding and unfolding mechanism are respectively connected to the outer ends of two adjacent reclaimer frames. The folding and unfolding mechanism, the two adjacent reclaimer frames, and the corresponding positions at the junction of the upper part and the lower part of the upper stage form an arrangement frame. An edge of a recycler fabric sheet is fixedly attached to a layout frame, and each recycler fabric sheet is stacked between the layout frames.

2. The foldable space debris reclaimer based on a launch vehicle according to claim 1, characterized in that, Each folding and unfolding mechanism shortens, and the circle formed by all the folding and unfolding mechanisms shrinks; All reclaimer frames, folding and unfolding mechanisms, and reclaimer fabric surfaces are attached to the conical surface of the lower part of the upper stage.

3. The foldable space debris reclaimer based on a launch vehicle according to claim 1 or 2, characterized in that, Each folding and unfolding mechanism elongates, and the circle formed by all the folding and unfolding mechanisms expands. All folding and unfolding mechanisms are away from the conical surface at the bottom of the upper stage, and all recycler frames rotate around the one-way rotating structure so that they are perpendicular to the cylindrical surface at the top of the upper stage. The stacked recycler fabric is away from the conical surface at the bottom of the upper stage, so that the arrangement frame and the recycler fabric form a circular net.

4. The foldable space debris reclaimer based on a launch vehicle according to claim 1 or 2, characterized in that, Four unidirectional rotating structures are evenly fixed at the junction of the upper part and the lower part of the upper stage, and four reclaimer frames are hinged to the four unidirectional rotating structures.

5. The foldable space debris reclaimer based on a launch vehicle according to claim 3, characterized in that, The unidirectional rotary structure is assisted by a spring to rotate, which drives the reclaimer frame to rotate.

6. The foldable space debris reclaimer based on a launch vehicle according to claim 3, characterized in that, The unidirectional rotary structure has a fixing groove, and the inner end of the recycler frame has a limiting protrusion. When the recycler frame rotates around the unidirectional rotary structure until it is perpendicular to the cylindrical surface of the upper part of the upper stage, the limiting protrusion is engaged in the fixing groove.

7. The foldable space debris reclaimer based on a launch vehicle according to claim 1 or 2, characterized in that, Each recycler skeleton includes: a main skeleton and a secondary skeleton; The inner end of the main frame is hinged to the one-way rotating structure, the outer end of the main frame is vertically fixed to the middle position of the secondary frame, the left end of the secondary frame is connected to the right end of the folding and unfolding mechanism located to its left, and the right end of the secondary frame is connected to the left end of the folding and unfolding mechanism located to its right.

8. The foldable space debris reclaimer based on a launch vehicle according to claim 7, characterized in that, The folding and unfolding mechanism includes: a spring, an unfolding rope, a rotary guide hinge, and a locking rope; The sub-frame has inwardly concave spring cylinders at both ends. One end of a spring is fixedly installed inside a spring tube on the left side of a sub-frame, and the other end of the spring extends to the left and is connected to the right end of the deployment rope; one end of another spring is fixedly installed inside a spring tube on the right side of the opposite sub-frame, and the other end of the spring extends to the right and is connected to the left end of the deployment rope. The two ends of the rotary guide hinge are respectively connected to the spring cylinders on both sides, and the unfolding rope passes through the middle of the rotary guide hinge; The two ends of the locking rope are connected to the springs on both sides, and the middle part of the locking rope is connected to the shearing device of the upper stage of the launch vehicle.

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