CN116119042B - Flying net type space debris capturing device - Google Patents
Flying net type space debris capturing device Download PDFInfo
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- CN116119042B CN116119042B CN202310416295.XA CN202310416295A CN116119042B CN 116119042 B CN116119042 B CN 116119042B CN 202310416295 A CN202310416295 A CN 202310416295A CN 116119042 B CN116119042 B CN 116119042B
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Abstract
The invention belongs to the field of space debris removal, and particularly relates to a flying net type space debris capturing device which comprises a net cage, a net cage cover, a flying net, a control tether, a traction tether, a hot knife assembly for cutting off the control tether and the traction tether respectively, and a plurality of groups of emission assemblies for emitting the flying net, wherein each group of emission assemblies comprises an emission cylinder, a traction block and a spring, the hot knife assembly is arranged on the outer side of the net cage, the control tether bypasses the net cage cover, the net cage and the hot knife assembly respectively, the net cage is fixed with the net cage cover, one end of the traction tether is connected with the flying net, and the other end of the traction tether is connected with a spacecraft for capturing space debris after bypassing the hot knife assembly. According to the invention, the thermal knife assembly is adopted to control the emission of the traction blocks, so that the device is different from the traditional initiating explosive device and pneumatic emission method, is more suitable for space environment, can more effectively ensure synchronous emission of a plurality of traction blocks, simplifies the overall complexity of the device, and achieves light weight.
Description
Technical Field
The invention belongs to the field of space debris removal, and particularly relates to a flying net type space debris capturing device.
Background
An increasing number of space debris is a serious problem, such as catastrophic damage to a failed satellite upon collision with a spacecraft. At present, rockets are launched to space for more than 6000 times in various countries, and the number of satellites sent into space is more than 10000, wherein about 6000 satellites are still in orbit, and about 3000 satellites are still working. International regulatory regulations regarding when satellites end up operating have been promulgated, but many retired legacy satellites remain in orbit to date because of lack of legal restrictions. Most of these satellites are distributed in the near-earth orbit, and the operating speed of the satellites is above 7 km/s. This high velocity impact can result in a large amount of small debris being generated by the impacting object, further exacerbating the space debris problem.
The flying net type space debris capturing device is a device for capturing large space debris, and compared with other space debris capturing modes, the flying net has the following advantages: long capture distance, low precision requirement on navigation, low cost and wide application range.
The existing flying net type space debris capturing device has the following problems: the design structure of the traditional flying net device is too complex, so that on one hand, the design cost of the flying net is increased, and on the other hand, the stability of engineering application is reduced; the traditional flying net launching device has most of pneumatic and gunpowder power and poor stability in space; the problem of satellite separation from space debris after off-orbit capture is not considered, and the problem of space debris removal must be considered for the separation capture target; the traction block transmitting parts of the traditional flying net device are of relatively independent structures or are controlled by explosion bolts, and the structure cannot ensure synchronous transmission of a plurality of traction blocks.
Disclosure of Invention
In view of the foregoing, an object of the present invention is to provide a flying net type space debris capturing device.
The aim of the invention is realized by the following technical scheme:
a flying net type space debris capturing device comprises a net cage, a net cage cover, a flying net, a control tether, a traction tether, a hot knife assembly for cutting off the control tether and the traction tether respectively, and a plurality of groups of emission assemblies for emitting the flying net;
each group of emission components comprises an emission cylinder, a traction block and springs, the emission cylinders of each group of emission components are arranged on the outer side of the net cage, the tops of the emission cylinders of each group of emission components are all open, the traction block of each group of emission components is positioned in the emission cylinder of the same group of emission components, one end of each group of springs of each emission component is connected with the bottom of the emission cylinder of the same group of emission components, and the other end of each spring of each group of emission components is abutted to the bottom of the traction block of the same group of emission components;
the net cage is arranged on a spacecraft for capturing space debris, the main body of the flying net is contained in the net cage with an opening at the top, a plurality of connecting ropes for connecting the launching assembly are arranged on the periphery of the flying net, each connecting rope is connected with a traction block in the corresponding launching assembly, and the net cage cover simultaneously covers the opening at the top of the net cage and the opening at the top of each launching cylinder;
the hot knife assembly is arranged on the outer side of the net cage, the control tether bypasses the net cage cover, the net cage and the hot knife assembly respectively and fixes the net cage and the net cage cover, one end of the traction tether is connected with the flying net, and the other end of the traction tether bypasses the hot knife assembly and then is connected with a spacecraft for capturing space debris.
And the transmitting cylinders of each group of transmitting assemblies are respectively connected with the net cage through corner plates.
The axial center lines of the transmitting cylinders of the transmitting assemblies form included angles with the axial center lines of the net cages.
The net box cover and the net box are respectively provided with a rope penetrating through hole, and the number of the rope penetrating through holes in the net box cover and the number of the rope penetrating through holes in the net box are at least three.
The number of the rope penetrating holes in the net cage cover is equal to the number of the rope penetrating holes in the net cage.
The net body of the flying net is folded in a Z shape and is contained in the net box.
The thermal knife assembly comprises an insulating gasket, a control tether cutting resistance wire and a traction tether cutting resistance wire, wherein the insulating gasket is arranged on the outer side of the net cage, the control tether cutting resistance wire and the traction tether cutting resistance wire are respectively fixed on the insulating gasket through ceramic posts, and the control tether cutting resistance wire and the traction tether cutting resistance wire are respectively connected with a thermal knife assembly control circuit in a spacecraft for capturing space debris;
the control tether bypasses the net cover, the net box and the control tether cutting resistance wire, and presses the control tether cutting resistance wire against the insulating spacer, and a part of the traction tether is wound around the traction tether cutting resistance wire.
A group of closing-in assemblies are arranged in each traction block, and each group of closing-in assemblies comprises a closing-in assembly power supply, a closing-in assembly control circuit, a closing-in driving motor, a reduction gearbox and a coil;
the power supply, the control circuit, the driving motor and the reduction gearbox of the closing assembly of the same group are respectively and fixedly arranged in the corresponding traction blocks, the driving end of the driving motor of each group of closing assembly is connected with the input end of the reduction gearbox of the closing assembly of the same group, the coil of each group of closing assembly is connected with the output end of the reduction gearbox of the closing assembly of the same group, each group of coil of closing assembly is provided with a closing wire, one end of the closing wire is fixed on the corresponding coil, and the other end of the closing wire extends out of the corresponding traction block and is connected with the flying net;
each group of the closing-in assembly control circuits of the closing-in assemblies are respectively connected with a closing-in assembly power supply and a closing-in driving motor of the same group of closing-in assemblies, and each group of the closing-in assembly control circuits of the closing-in assemblies comprises a communication module which can receive signals sent by spacecrafts for capturing space fragments.
Each group of closing-in assembly further comprises a ratchet wheel and a pawl which are matched, the pawl of each group of closing-in assembly is fixedly arranged in the corresponding traction block, and the ratchet wheel of each group of closing-in assembly is connected with the output end of the reduction gearbox of the same group of closing-in assembly.
The other end of the closing-in line on the coil of each closing-in assembly extends out of the corresponding traction block and is connected with the other traction block close to the nearby position on the fly net.
The invention has the advantages and positive effects that:
1. according to the invention, the thermal knife assembly is adopted to control the emission of the traction blocks, so that the device is different from the traditional initiating explosive device and pneumatic emission method, is more suitable for space environment, can more effectively ensure synchronous emission of a plurality of traction blocks, simplifies the overall complexity of the device, and achieves light weight.
2. The net body of the flying net is folded and stored in a Z shape, so that the limited space can be more reasonably utilized, and the risk of winding and dragging the net body of the flying net is effectively reduced.
3. According to the invention, the closing-in assembly is arranged in the traction block, so that after the net body of the flying net wraps the target fragments, the closing-in assembly can automatically complete the capturing, and the flying net is ensured to stably capture the fragments.
Drawings
FIG. 1 is a schematic view of the overall external structure of the present invention;
FIG. 2 is a second overall external schematic view of the present invention;
FIG. 3 is a schematic view of the overall internal structure of the present invention;
FIG. 4 is a schematic view of the structure of the flying net of the present invention;
FIG. 5 is a schematic view of a folding and storing structure of a net body of the flying net according to the present invention;
FIG. 6 is a schematic view of the thermal knife assembly of the present invention;
fig. 7 is a schematic view of the internal structure of the traction block of the present invention.
In the figure: the device comprises a net cage 1, a net box cover 2, a flying net 3, a control tether 4, a traction tether 5, a transmitting cylinder 6, a traction block 7, a spring 8, a connecting rope 9, a corner plate 10, a rope through hole 11, an insulating gasket 12, a resistance wire 13 for cutting the control tether, a resistance wire 14 for cutting the traction tether, a ceramic column 15, a closing component power supply 16, a closing component control circuit 17, a closing driving motor 18, a reduction gearbox 19, a coil 20, a ratchet 21 and a pawl 22;
001 is the folded front net body and 002 is the folded back net body.
Detailed Description
The invention is further described in detail below with reference to fig. 1-7.
As shown in fig. 1-7, the flying net type space debris capturing device comprises a net cage 1, a net cage cover 2, a flying net 3, a control tether 4, a traction tether 5, a hot knife assembly for cutting off the control tether 4 and the traction tether 5 respectively, and four groups of launching assemblies for launching the flying net 3. In the embodiment, the flying net 3 is a quadrilateral net body, the mesh shape adopts quadrilateral meshes, the side size of each mesh is 10cm, and the net body material is aramid fiber.
Each group of emission components comprises an emission cylinder 6, a traction block 7 and a spring 8, and the emission cylinders 6 of each group of emission components are arranged on the outer side of the net cage 1. In this embodiment, four groups of emission components are uniformly arranged outside the net cage 1 and respectively correspond to each angular position of the flying net 3. The top of the transmitting cylinders 6 of each group of transmitting assemblies are all open, the traction block 7 of each group of transmitting assemblies is positioned in the transmitting cylinders 6 of the same group of transmitting assemblies, one end of the spring 8 of each group of transmitting assemblies is connected with the bottom of the transmitting cylinders 6 of the same group of transmitting assemblies, and the other end of the spring is abutted to the bottom of the traction block 7 of the same group of transmitting assemblies.
The net cage 1 is mounted on a spacecraft for capturing space debris, and a main body of the flying net 3 is accommodated inside the net cage 1 with an opening at the top. The installation mode between the net cage 1 and the spacecraft in the embodiment is the prior art, for example, the net cage is fixedly connected through bolts and screws. Each corner of the periphery of the flying net 3 is provided with one connecting rope 9, namely four connecting ropes 9 in four corners, and each connecting rope 9 is connected with the bottom surface of the traction block 7 in the corresponding group of emission components. The net cover 2 simultaneously covers the top opening of the net cover 1 and the top opening of each of the transmitting drums 6, and simultaneously presses the traction block 7 inside the transmitting drum 6. In this embodiment, the elastic force of the fully compressed spring 8 should meet the requirement of emission, and the speed of the net cover 2 in vitro is greater than or equal to the speed of the traction block 7 in vitro. In this embodiment, the top opening of the launch canister 6 is not completely covered by the net cover 2, and the net cover 2 includes a plurality of weight-reducing grooves to achieve the weight-reducing effect.
The hot knife assembly is arranged on the outer side of the net cage 1, the control tether 4 bypasses the net cage cover 2, the net cage 1 and the hot knife assembly respectively and fixes the net cage 1 and the net cage cover 2, one end of the traction tether 5 is connected with the flying net 3, and the other end of the traction tether is connected with a spacecraft for capturing space debris after bypassing the hot knife assembly.
Specifically, as shown in fig. 2 and 3, the transmitting cylinders 6 of each group of transmitting assemblies in the embodiment are respectively connected with the net cage 1 through corner plates 10, the axial center lines of the transmitting cylinders 6 of each group of transmitting assemblies respectively form included angles with the axial center line of the net cage 1, and the magnitude of the included angles, namely the magnitude of the outward transmitting angles of the traction blocks 7. In the embodiment, the transmitting cylinder 6 is connected with the corner plate 10 through bolts, and the corner plate 10 is connected with the net cage 1 through bolts.
Specifically, as shown in fig. 1, in this embodiment, the net cover 2 and the net cover 1 are respectively provided with a rope penetrating hole 11, and the number of the rope penetrating holes 11 on the net cover 2 and the number of the rope penetrating holes 11 on the net cover 1 are three, so that the tether 4 can be controlled to effectively wind and keep the net cover 1 and the net cover 2 fixed and stable.
Specifically, as shown in fig. 5, in the present embodiment, the net body of the flying net 3 is folded in a zigzag shape and stored in the net box 1, wherein 001 is a net body before folding, and 002 is a net body after folding. The adoption of Z-shaped folding storage can more reasonably utilize limited space, and reduce the risk of winding and dragging of the net body of the flying net 3.
Specifically, as shown in fig. 3 and 6, the thermal knife assembly in this embodiment includes an insulating spacer 12, a control tether cutting resistance wire 13, and a traction tether cutting resistance wire 14, the insulating spacer 12 is mounted on the outside of the net cage 1, the control tether cutting resistance wire 13 and the traction tether cutting resistance wire 14 are fixed to the insulating spacer 12 by ceramic posts 15, and the control tether cutting resistance wire 13 and the traction tether cutting resistance wire 14 are connected to a thermal knife assembly control circuit located in a spacecraft for space debris capturing. In this embodiment, the installation and connection method of the insulating spacer 12 and the cage 1, the connection method of the ceramic posts 15 and the insulating spacer 12, and the installation method of the control tether cutting resistance wire 13 and the traction tether cutting resistance wire 14 are all conventional. The arrangement mode of the hot knife assembly control circuit in the spacecraft is achieved by adopting the prior art, the hot knife assembly control circuit in the embodiment comprises a PCB provided with STM32F103RCT6, a relay and a power supply, and the hot knife assembly control circuit is controlled by an upper controller in the spacecraft to act. In this embodiment, the control tether cutting resistance wire 13 and the traction tether cutting resistance wire 14 are nichrome wires.
The control tether 4 is wound around the net cover 2, the net case 1, and the control tether cutting resistance wire 13 is pressed against the insulating spacer 12, and a part of the traction tether 5 is wound around the traction tether cutting resistance wire 14. The adoption of the hot knife assembly to control the emission of the traction blocks 7 is different from the traditional initiating explosive device and pneumatic emission method, is more suitable for space environment, and can more effectively ensure the synchronous emission of a plurality of traction blocks 7.
Specifically, as shown in fig. 7, in this embodiment, a group of necking assemblies is disposed in each traction block 7, and each group of necking assemblies includes a necking assembly power source 16, a necking assembly control circuit 17, a necking driving motor 18, a reduction gearbox 19 and a coil 20.
The closing-in assembly power supply 16, the closing-in assembly control circuit 17, the closing-in driving motor 18 and the reduction gearbox 19 of the same group of closing-in assemblies are respectively and fixedly arranged in the corresponding traction block 7, and the installation modes are all in the prior art, for example, the closing-in assembly power supply, the closing-in assembly control circuit, the closing-in driving motor and the reduction gearbox are installed through bolts, partition plates and the like. The driving end of the closing-in driving motor 18 of each closing-in assembly is connected with the input end of the reduction gearbox 19 of the same closing-in assembly, the coil 20 of each closing-in assembly is connected with the output end of the reduction gearbox 19 of the same closing-in assembly, closing-in wires are arranged on the coils 20 of each closing-in assembly, one end of each closing-in wire is fixed on the corresponding coil 20, and the other end of each closing-in wire extends out of the corresponding traction block 7 and is connected with the flying net 3. In this embodiment, the other end of the closing-in wire on the coil 20 of each closing-in assembly extends out of the corresponding traction block 7 and is connected to another traction block 7 on the flying net 3 close to the adjacent one. The closing-in driving motor 18 acts, the coil 20 is driven to rotate through the reduction gearbox 19, the closing-in wire on the coil 20 is wound, the other end of the closing-in wire pulls the flying mesh 3, and the flying mesh 3 is closed in order to ensure that the flying mesh 3 stably captures fragments.
The closing-in assembly control circuit 17 of each closing-in assembly is respectively connected with the closing-in assembly power supply 16 and the closing-in driving motor 18 of the same closing-in assembly, and the closing-in assembly control circuit 17 of each closing-in assembly comprises a communication module which can receive signals sent by the spacecraft for capturing space debris. In this embodiment, the closing-in driving motor 18 and the reduction gearbox 19 are all commercial products, and the closing-in driving motor 18 is a commercial direct current motor. The connection mode of the closing-up assembly control circuit 17 and the closing-up assembly power supply 16 and the closing-up driving motor 18 is also the prior art. The setting mode of the closing-in assembly control circuit 17 is just to adopt prior art, and closing-in assembly control circuit 17 comprises PCB board, relay, infrared sensor module and power that are provided with STM32F103RCT6 in this embodiment. The infrared sensor module is used as a communication module for receiving signals sent by the spacecraft for capturing space fragments, after receiving the signals sent by the upper controller in the spacecraft, the closing-in assembly control circuit 17 starts timing when the traction block 7 emits according to a program, and after the timing reaches the expected unfolding time, the closing-in driving motor 18 is commanded to rotate for closing-in.
Each group of closing-in components further comprises a ratchet wheel 21 and a pawl 22 which are matched, the pawl 22 of each group of closing-in components is fixedly arranged in the corresponding traction block 7, and the ratchet wheel 21 of each group of closing-in components is connected with the output end of the reduction gearbox 19 of the same group of closing-in components. Through the setting of ratchet 21 and pawl 22 for the dead-lock reducing gear box 19's output after the binding off is finished, guarantee the binding off stability.
Working principle:
when space debris needs to be captured, the spacecraft for capturing the space debris reaches a preset position 100 meters away from the space debris and the flying net capturing device is aligned to the space debris; then an upper controller in the spacecraft controls a tether cutting resistance wire 13 to cut off a control tether 4 for fixing the net cage 1 and the net cage cover 2 so as to release the net cage cover 2, each traction block 7 loses resistance along with the release of the net cage cover 2 to start transmitting and drives the net body of the flying net 3 to be unfolded, and a closing-in assembly control circuit 17 starts timing when the traction block 7 transmits according to a program after receiving a signal sent by the upper controller in the spacecraft; after the net body of the flying net 3 wraps the target fragments, the closing-up driving motor 18 rotates to close up to finish capturing after the timing reaches the expected unfolding time; after the space debris is captured, the spacecraft drags the space debris to the tomb orbit, and after the space debris arrives, the drag tether 5 connected between the flying net 3 and the spacecraft is cut off by the drag tether cutting resistance wire 14, so that the space debris off-orbit processing is completed.
Claims (9)
1. The utility model provides a fly net formula space debris capturing device which characterized in that: the device comprises a net cage (1), a net cage cover (2), a flying net (3), a control tether (4), a traction tether (5) and a hot knife assembly for cutting off the control tether (4) and the traction tether (5) respectively, and further comprises a plurality of groups of emission assemblies for emitting the flying net (3);
each group of emission components comprises an emission cylinder (6), a traction block (7) and a spring (8), the emission cylinders (6) of each group of emission components are arranged on the outer side of the net cage (1), the tops of the emission cylinders (6) of each group of emission components are all open, the traction block (7) of each group of emission components is positioned in the emission cylinders (6) of the same group of emission components, one end of the spring (8) of each group of emission components is connected with the bottoms of the emission cylinders (6) of the same group of emission components, and the other end of the spring is abutted to the bottoms of the traction blocks (7) of the same group of emission components;
the net cage (1) is arranged on a spacecraft for capturing space debris, the main body of the flying net (3) is contained in the net cage (1) with an opening at the top, a plurality of connecting ropes (9) for connecting the launching components are arranged on the periphery of the flying net (3), each connecting rope (9) is connected with a traction block (7) in the corresponding launching component, and the net cage cover (2) simultaneously covers the opening at the top of the net cage (1) and the opening at the top of each launching cylinder (6);
the hot knife assembly is arranged on the outer side of the net cage (1), the control tether (4) bypasses the net cage cover (2), the net cage (1) and the hot knife assembly respectively, the net cage (1) and the net cage cover (2) are fixed, one end of the traction tether (5) is connected with the flying net (3), and the other end of the traction tether bypasses the hot knife assembly and is connected with a spacecraft for capturing space debris;
the thermal knife assembly comprises an insulating gasket (12), a control tether cutting resistance wire (13) and a traction tether cutting resistance wire (14), wherein the insulating gasket (12) is arranged outside the net cage (1), the control tether cutting resistance wire (13) and the traction tether cutting resistance wire (14) are respectively fixed on the insulating gasket (12) through ceramic posts (15), and the control tether cutting resistance wire (13) and the traction tether cutting resistance wire (14) are respectively connected with a thermal knife assembly control circuit positioned in a spacecraft for capturing space debris;
the control tether (4) bypasses the net box cover (2), the net box (1) and the control tether cutting resistance wire (13) respectively, the control tether cutting resistance wire (13) is pressed on the insulating gasket (12), and a part of the traction tether (5) is wound on the traction tether cutting resistance wire (14).
2. A flying mesh space debris trapping device according to claim 1, wherein: the transmitting cylinders (6) of each group of transmitting assemblies are respectively connected with the net cage (1) through corner plates (10).
3. A flying mesh space debris trapping device according to claim 2, wherein: the axial center lines of the transmitting cylinders (6) of the transmitting assemblies form included angles with the axial center lines of the net boxes (1) respectively.
4. A flying mesh space debris trapping device according to claim 1, wherein: the net box cover (2) and the net box (1) are respectively provided with a rope penetrating through hole (11), and the number of the rope penetrating through holes (11) in the net box cover (2) and the number of the rope penetrating through holes (11) in the net box (1) are at least three.
5. The flying net type space debris capturing device according to claim 4, wherein: the number of the rope through holes (11) on the net box cover (2) is equal to the number of the rope through holes (11) on the net box (1).
6. A flying mesh space debris trapping device according to claim 1, wherein: the net body of the flying net (3) is folded in a Z shape and is contained in the net box (1).
7. A flying mesh space debris trapping device according to claim 1, wherein: a group of closing-in assemblies are arranged in each traction block (7), and each group of closing-in assemblies comprises a closing-in assembly power supply (16), a closing-in assembly control circuit (17), a closing-in driving motor (18), a reduction gearbox (19) and a coil (20);
the power supply (16) of the closing assembly, the control circuit (17) of the closing assembly, the closing driving motor (18) and the reduction gearbox (19) of the closing assembly are respectively and fixedly arranged in the corresponding traction block (7), the driving end of the closing driving motor (18) of each closing assembly is connected with the input end of the reduction gearbox (19) of the closing assembly of the same group, the coil (20) of the closing assembly of each group is connected with the output end of the reduction gearbox (19) of the closing assembly of the same group, closing wires are arranged on the coils (20) of the closing assembly of each group, one end of each closing wire is fixed on the corresponding coil (20), and the other end of each closing wire extends out of the corresponding traction block (7) and is connected with the flying net (3);
each group of closing-in assembly control circuits (17) of the closing-in assemblies are respectively connected with a closing-in assembly power supply (16) and a closing-in driving motor (18) of the same group of closing-in assemblies, and each group of closing-in assembly control circuits (17) of the closing-in assemblies comprises a communication module capable of receiving signals sent by spacecrafts for capturing space debris.
8. The flying net type space debris capturing device of claim 7, wherein: each group of closing-in components further comprises a ratchet wheel (21) and a pawl (22) which are matched, the pawl (22) of each group of closing-in components is fixedly arranged in the corresponding traction block (7), and the ratchet wheel (21) of each group of closing-in components is connected with the output end of the reduction gearbox (19) of the same group of closing-in components.
9. The flying net type space debris capturing device of claim 7, wherein: the other end of the closing-in line on the coil (20) of each closing-in assembly extends out of the corresponding traction block (7) and is connected with the position, close to the adjacent traction block (7), of the flying mesh (3).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310416295.XA CN116119042B (en) | 2023-04-19 | 2023-04-19 | Flying net type space debris capturing device |
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| CN202310416295.XA CN116119042B (en) | 2023-04-19 | 2023-04-19 | Flying net type space debris capturing device |
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| CN112896562A (en) * | 2021-02-11 | 2021-06-04 | 西北工业大学 | Space debris tether trapper based on inertia |
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| CN116119042A (en) | 2023-05-16 |
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