A deployable flexible shield space debris protection device

Abstract

The present application provides a kind of flexible protection layer space debris protection device of foldable, the device includes: motor (4) of installation in the body to be protected, shaft coupling (5) and reducer (6), a plurality of cam linkages (1) connected with the motor, buffer folding mechanism (2) is driven to unfold by synchronous belt (17), and flexible composite protective layer (3) for protecting space debris impact;Each cam linkages (1) includes cam disk (9), pressing device (7), connecting rod (8) and cam roller (10), the cam roller (10) is installed with the cam disk (9), and the cam roller (10) slides in cam disk channel (12);The buffer folding mechanism (2) is connected with the cam roller (10) at one end, and the other end is connected with the flexible composite protective layer (3), when the cam roller (10) slides in the cam disk channel (12), the buffer folding mechanism (2) drives the flexible composite protective layer (3) to unfold or shrink.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of impact protection, in particular to a foldable flexible protective layer space debris protection device. BACKGROUND

[0002] With the rapid development of space technology in various countries, the number of space debris has increased dramatically. According to statistics, there are hundreds of millions of space debris above millimeter level with a mass of several thousand tons in orbit. Due to the extremely high speed of space debris, millimeter-level debris can cause the function of a spacecraft to fail, which poses a great threat to the safe operation of the spacecraft in orbit. The existing space debris protection technology mostly adopts Whipple protection structure, and is basically used for large spacecraft such as space stations. The protection effect is poor and the defense capability for centimeter-level debris is limited.

[0003] It is necessary to design a deployable space debris protection load for a satellite instead of the traditional fixed external protection structure, so as to improve the impact resistance of the satellite as much as possible without affecting the use of the effective load of the satellite, and prolong the on-orbit service life. SUMMARY

[0004] In view of the defects in the prior art, the present application provides a foldable flexible protective layer space debris protection device, which comprises a motor (4), a coupling (5) and a speed reducer (6) mounted on a body to be protected, a plurality of cam link mechanisms (1) connected with the motor, a buffer folding mechanism (2) driven to unfold through a synchronous belt (17), and a flexible composite protective layer (3) for protecting against space debris impact.

[0005] Each of the cam link mechanisms (1) comprises a cam disc (9), a pressing device (7), a connecting rod (8) and a cam roller (10), the cam roller (10) is mounted with the cam disc (9), and the cam roller (10) slides in a cam disc groove (12).

[0006] One end of the buffer folding mechanism (2) is connected with the cam roller (10), and the other end is connected with the flexible composite protective layer (3). When the cam roller (10) slides in the cam disc groove (12), the buffer folding mechanism (2) drives the flexible composite protective layer (3) to unfold or contract.

[0007] In a possible implementation, the buffer folding and unfolding mechanism (2) comprises a first main buffer device (14), a second main buffer device (15), an auxiliary buffer (16), a linear guide rail (30), a first driving gear (19), a first driven gear (25), and a synchronous belt (17), the first main buffer device (14) is arranged on the satellite body and connected with the cam linkage mechanism (1), the synchronous belt (17) is used to drive the rotation of the driving gear (19), the driving gear (19) is in meshing transmission with the driven gear (25) to drive the unfolding of the second main buffer device (15), one end of the auxiliary buffer (16) is connected with the linear guide rail (30) through a sliding block (31), and the other end is connected with the flexible protective layer (3), and the flexible protective layer (3) is connected with the second main buffer device (15) and the auxiliary buffer (16).

[0008] In a possible implementation, the first main buffer device (14) comprises a first piston rod (22), a first cylinder body (23), a synchronous belt (17), a first pin shaft (18), a first driving gear (19), and a first driven gear (25), an end of the first cylinder body (23) is provided with a first end cover (24), a gap is arranged between the first cylinder body (23) and the first piston rod (22), the first piston rod (22) is provided with a driving gear shaft and a driven gear shaft, the gear shaft is provided with a gear bearing, and the first piston rod (22) is provided with a spring limiting pin hole (20).

[0009] In a possible implementation, the first cylinder body (23) is internally provided with aluminum honeycomb buffer material (21).

[0010] In a possible implementation, the second main buffer device (15) comprises a second piston rod (26), a second cylinder body (28), a linear guide rail (30), a sliding block (31), and steel ball locks (32 and 33), an end of the second cylinder body (28) is provided with a second end cover (27), a gap is arranged between the second cylinder body (28) and the second piston rod (26), and the second cylinder body linear guide rail boss mounting place is provided with a spring steel ball lock.

[0011] In a possible implementation, the second cylinder body (28) is internally provided with aluminum honeycomb buffer material (29).

[0012] In a possible implementation, the auxiliary buffer (16) comprises an auxiliary buffer piston rod (34), an auxiliary buffer cylinder body (36), a body (39), and a body shaft sleeve (38), a gap is arranged between the body (39) and the piston rod (34), the auxiliary buffer piston rod (34) and the cylinder body (36) are provided with a reset spring (37) and an auxiliary buffer end cover (35).

[0013] In a possible implementation, the body (39) and the body sleeve (38) are provided with an O-shaped sealing ring.

[0014] In a possible implementation, the pressing device (7) comprises a pressing base (11) and a pressing block (13).

[0015] In a possible implementation, the cam link mechanism (1) is provided with four groups which are arranged at an angle of 90° with respect to each other.

[0016] Compared with the prior art, the present application has at least the following beneficial effects:

[0017] Compared with the traditional Whipple protective structure, the present application has the advantages of light weight, excellent protection performance, small volume, high deployment reliability, etc.

[0018] The foldable flexible protective layer of the present application is more flexible and reliable than general passive protective structures, and still has certain defense capability in the non-deployed and semi-deployed states. Due to the large deployment spacing, the kinetic energy damage caused by space debris to the satellite can be greatly reduced.

[0019] The present application uses a flexible protective layer in cooperation with a multi-stage buffer, which has the advantages of compact structure, energy absorption, excellent protection performance, and different buffer adjustment according to the impact degree, and better energy absorption coordination.

[0020] The present application has a wide range of applications, and can be applied not only to satellite impact kinetic energy defense, but also to important space devices such as space stations and space telescopes, and can also be applied to ground important facilities and devices. BRIEF DESCRIPTION OF DRAWINGS

[0021] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0022] Figure 1 is a structural schematic view of a foldable flexible protective layer space debris protective device of the present application,

[0023] Figure 2 is a structural schematic view of a foldable flexible protective layer space debris protective device in a folded state of the present application,

[0024] Figure 3 is a schematic view of a cam link mechanism in the present application,

[0025] Figure 4 is a schematic view of a cam disc structure in the present application,

[0026] Figure 5 is a series-parallel foldable buffer mechanism of the present application,

[0027] Figure 6 is a first buffer structure schematic diagram in the application,

[0028] Figure 7 is a second main buffer structure schematic diagram in the application

[0029] Figure 8 is a steel ball lock structure partial enlarged view in the application,

[0030] Figure 9 is an auxiliary buffer structure schematic diagram in the application,

[0031] Figure 10 is a flexible protective layer structure schematic diagram in the application. DETAILED DESCRIPTION

[0032] The application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the application. These are within the scope of the application.

[0033] As shown in the accompanying drawings Figure 1 and Figure 2 : a deployable flexible protective layer protection device against space debris impact, comprising a motor 4, a shaft coupling 5 and a speed reducer 6 installed on a body to be protected (in this embodiment, a satellite), a cam link mechanism 1 connected with the motor, a buffer deployment mechanism 2 deployed by a synchronous belt 17, and a flexible composite protective layer 3 for protecting against space debris impact. The cam link mechanism 1 comprises a cam disc 9, a pressing device 7, a connecting rod 8 and a cam roller 10, the cam roller 10 is installed with the cam disc 9, the cam roller 10 slides in the cam disc groove 12, the pressing device 7 comprises a pressing base 11 and a pressing block 13, and there are four groups of cam link mechanisms.

[0034] Through the above arrangement, the motor 4 can drive the cam disc 9 to rotate, the rotation of the cam disc 9 drives the cam roller 10 to slide in the cam disc groove 12, and drives the cam link mechanism 1 to gradually deploy.

[0035] The buffer folding and unfolding mechanism comprises a first main buffer device 14, a second main buffer device 15, an auxiliary buffer 16, a linear guide rail 30, a first driving gear 19, a first driven gear 25, and a synchronous belt 17. The first main buffer device 14 is arranged on the satellite body and connected with the cam linkage mechanism 1. The synchronous belt 17 is used to drive the rotation of the driving gear 19. The meshing transmission of the driving gear 19 and the driven gear 25 drives the unfolding of the second main buffer device 15. One end of the auxiliary buffer 16 is connected with the linear guide rail 30 through a sliding block 31, and the other end is connected with the flexible protective layer 3. The flexible protective layer 3 is connected with the second main buffer device 15 and the auxiliary buffer 16.

[0036] The first main buffer device 14 comprises a first piston rod 22, a first cylinder body 23, the synchronous belt 17, a first pin shaft 18, the first driving gear 19, and the first driven gear 25. The end of the first cylinder body 23 is provided with a first end cover 24. A gap is arranged between the first cylinder body 23 and the first piston rod 22. The inside of the first cylinder body 23 is filled with aluminum honeycomb buffer material 21. The first piston rod 22 is provided with a driving gear shaft and a driven gear shaft. The gear shaft is provided with a gear bearing. The first piston rod 22 is provided with a spring limiting pin hole 20. The second main buffer device 15 comprises a second piston rod 26, a second cylinder body 28, the linear guide rail 30, the sliding block 31, steel ball locks 32 and 33. The end of the second cylinder body 28 is provided with a second end cover 27. A gap is arranged between the second cylinder body 28 and the second piston rod 26. The inside of the second cylinder body 28 is filled with aluminum honeycomb buffer material 29. The second cylinder body linear guide rail boss installation is provided with spring steel ball locks 32 and 33. The auxiliary buffer 16 comprises an auxiliary buffer piston rod 34, an auxiliary buffer cylinder body 36, a body 39, and a body shaft sleeve 38. A gap is arranged between the body 39 and the piston rod 34. The body 39 and the body shaft sleeve 38 are provided with O-shaped sealing rings. The auxiliary buffer piston rod 34 and the cylinder body 36 are provided with a return spring 37 and an auxiliary buffer end cover 35.

[0037] Through the above arrangement, when the space debris hits the foldable and unfoldable flexible protective layer, most of the kinetic energy of the space debris is first offset by the plastic destruction of the flexible protective layer, thereby causing the vibration of the protective layer to be offset by the auxiliary buffer, reducing the influence of the vibration of the protective layer on the satellite body. The first and second main buffers further buffer the impact kinetic energy through aluminum honeycomb.

[0038] Exemplarily, the flexible protective layer 3 in the application has 9 layers, including the first, fifth and ninth layers from inside to outside as Kevlar cloth protective layer 40, the second, fourth, sixth and eighth layers as polyurethane foam 41, and the third and seventh layers as aramid fiber cloth buffer layer 42. The aramid protective layer 42 has good energy absorption effect on space debris, the Kevlar protective layer 40 has good crushing effect on space debris, and the polyurethane foam 41 is used to fill the fiber protective layer due to its good compressibility and also has a certain buffering effect.

[0039] The structure of the application will be further described in detail below by taking a rocket launching satellite as an example in combination with the working process of the present application:

[0040] In the launching state, the repeatable folding and unfolding mechanism is in the contracted state. After the satellite enters the predetermined orbit, the driving device is started, the motor can drive the cam disc to rotate, the rotation of the cam disc drives the cam roller to slide in the cam disc groove, and the cam link is gradually unfolded. Specifically, the cam roller 10 is connected with the cam disc 9 and moves in the cam disc sliding groove 12. The pressing device 7 is installed on the cam disc 9 and is used to constrain the sliding of the cam roller 10 in the cam disc groove 12. Under the action of the cam roller 10, the cam link 8 pushes the first main buffer 14 to rotate. The first buffer 14 is provided with a synchronous belt 17 on both sides, which can transmit power more stably to the first driving gear 19. The unfolding angles of the first buffer 14 and the second main buffer 15 are 135° and 225° respectively, and the gear ratio of the driving gear and the driven gear is 3:5. The power is transmitted to the synchronous belt 17 through the first buffer pin shaft 18, the synchronous belt 17 drives the first driving gear 19 to rotate, the second main buffer 15 is connected with the first driven gear 25, and the first main buffer piston rod 22 is provided with a spring limiting pin hole 20. When the second main buffer 15 rotates to a certain angle, the positions of the two main buffers are locked. The second cylinder body 28 is provided with a linear guide rail 30, and the auxiliary buffer 16 is connected with the linear guide rail 30 through a sliding block 31. In the unfolding process of the flexible protective layer 3, the auxiliary buffer piston rod 34 slides along the linear guide rail 30. The second cylinder body 28 is provided with steel ball locks 32 and 33, and the steel ball locks lock the sliding block 31 after the flexible protective layer 3 is completely unfolded. The flexible protective layer 3 is used to directly crush space debris and protect the satellite body and its load, and the first main buffer 14, the second main buffer 15 and the auxiliary buffer 16 absorb the energy generated by the impact.

[0041] The specific embodiments of the application are described above. It should be understood that the application is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the application. The embodiments of the application and the features in the embodiments can be combined with each other arbitrarily without conflict.

Claims

1. A space debris protection device with a foldable flexible protective layer, characterized in that, The device includes: a motor (4), a coupling (5) and a reducer (6) installed on the body to be protected, multiple cam linkage mechanisms (1) connected to the motor, a buffer folding mechanism (2) that is driven by a synchronous belt (17) and a flexible protective layer (3) for protecting against impacts from space debris. Each of the cam linkage mechanisms (1) includes a cam disk (9), a clamping device (7), a connecting rod (8), and a cam roller (10), the cam roller (10) being mounted to the cam disk (9) and sliding within a cam disk groove (12); One end of the buffer folding mechanism (2) is connected to the cam roller (10), and the other end is connected to the flexible protective layer (3). When the cam roller (10) slides in the cam disk groove (12), the buffer folding mechanism (2) drives the flexible protective layer (3) to unfold or retract. The buffer unfolding mechanism (2) includes a first main buffer device (14), a second main buffer device (15), an auxiliary buffer (16), a linear guide rail (30), a first driving gear (19), a first driven gear (25), and a synchronous belt (17). The first main buffer device (14) is mounted on the satellite body and connected to the cam linkage mechanism (1). The synchronous belt (17) is used to drive the first driving gear (19) to rotate. The meshing transmission between the first driving gear (19) and the first driven gear (25) drives the second main buffer device (15) to unfold. One end of the auxiliary buffer (16) is connected to the linear guide rail (30) through a slider (31), and the other end is connected to the flexible protective layer (3). The flexible protective layer (3) is connected to the second main buffer device (15) and the auxiliary buffer (16).

2. The space debris protection device with a foldable flexible protective layer according to claim 1, characterized in that, The first main buffer device (14) includes a first piston rod (22), a first cylinder (23), a synchronous belt (17), a first pin (18), a first driving gear (19), and a first driven gear (25). The end of the first cylinder (23) is provided with a first end cap (24). There is a gap between the first cylinder (23) and the first piston rod (22). The first piston rod (22) is provided with a driving gear shaft and a driven gear shaft. The gear shaft is provided with a gear bearing. The first piston rod (22) is provided with a spring limiting pin hole (20).

3. The space debris protection device with a foldable flexible protective layer according to claim 2, characterized in that, The first cylinder (23) is filled with a first aluminum honeycomb buffer material (21).

4. The space debris protection device with a foldable flexible protective layer according to claim 1, characterized in that, The second main buffer device (15) includes a second piston rod (26), a second cylinder (28), a linear guide rail (30), a slider (31), and a steel ball lock. The end of the second cylinder (28) is provided with a second end cap (27). There is a gap between the second cylinder (28) and the second piston rod (26). A spring steel ball lock is provided at the mounting position of the linear guide rail boss of the second cylinder.

5. A space debris protection device with a deployable flexible protective layer according to claim 4, characterized in that, The interior of the second cylinder (28) is filled with a second aluminum honeycomb buffer material (29).

6. A space debris protection device with a deployable flexible protective layer according to claim 1, characterized in that, The auxiliary buffer (16) includes an auxiliary buffer piston rod (34), an auxiliary buffer cylinder (36), a body (39), and a body bushing (38). A gap is provided between the body (39) and the auxiliary buffer piston rod (34). The auxiliary buffer piston rod (34) and the auxiliary buffer cylinder (36) are provided with a return spring (37) and an auxiliary buffer end cap (35).

7. A space debris protection device with a deployable flexible protective layer according to claim 6, characterized in that, The body (39) and the body bushing (38) are provided with O-ring seals.

8. A space debris protection device with a deployable flexible protective layer according to claim 1, characterized in that, The pressing device (7) includes a pressing base (11) and a pressing block (13); the pressing block (13) is installed at the starting end of the cam disk channel (12) and is used to press the cam roller into the cam disk channel (12).

9. A space debris protection device with a deployable flexible protective layer according to claim 1, characterized in that, The cam linkage mechanism (1) is provided in four sets, which are distributed at 90° to each other.

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