A cable net launching cabin with automatically closing hatch cover

Abstract

The present invention is a cable net launching cabin that can automatically close the hatch cover. It includes a rotatably connected hatch cover, a locking and separating device I, a launching device, a cabin body, a micro switch, a locking and separating device II, a net bag, a locking hinge, a rotating shaft mechanism on both sides, an intermediate rotating shaft mechanism and a flap; the two rotating shaft seats of the rotating shaft mechanisms on both sides are respectively connected to the hatch cover and the cabin body; the two rotating shaft seats of the intermediate rotating shaft mechanism are respectively connected to the cabin body and the flap, the two sides of the flap are respectively connected to the long plate I of the locking hinge, the long plate II of the locking hinge is arranged on the hatch cover, the intermediate rotating shaft mechanism provides the hatch cover with a torque when closing, and the torque provided for the hatch cover when closing is greater than the sum of the torques provided by the rotating shaft mechanisms on both sides; a locking and separating device II is arranged between the hatch cover and the cabin body away from the rotating end, and a launching device and a net bag are arranged in the cabin body. The present invention can realize the opening and closing of the hatch cover only when receiving an electrical signal for opening and closing the hatch door.

Description

Technical Field

[0001] The invention belongs to the field of spacecraft deorbiting, and in particular relates to a cable net launching cabin with a hatch cover capable of automatically closing. Background Art

[0002] As countries accelerate their exploration of space resources, the number of satellites in orbit increases year by year. However, due to satellite disintegration, collision, and operational debris, the number of debris in space has increased dramatically, seriously threatening the safety of spacecraft in orbit. Therefore, effective measures must be taken to clean up the problem of space debris deorbiting in order to curb the growing trend of debris and protect the safety of orbiting spacecraft.

[0003] At present, there are several ways to capture space debris, including mechanical arm capture, spear capture and cable net capture. Cable net capture has become a very popular way to capture space debris at this stage due to its strong adaptability and low cost. Summary of the invention

[0004] The purpose of the present invention is to provide a flying cable launch cabin device that can automatically close the hatch, so as to solve the problem that the current launch cabin in space uses motor operation to open and close the hatch door, thereby occupying too many satellite space resources. By using the elastic potential energy of the spring to open and close the hatch, the structure is simpler, the problem of low reliability of the motor drive is avoided, and the occupation of space resources of the spacecraft is greatly reduced.

[0005] The technical solution to achieve the purpose of the present invention is: a cable net launching cabin with a hatch cover that can be automatically closed, comprising a rotatably connected hatch cover, a locking and separating device I, a launching device, a cabin body, a micro switch, a locking and separating device II, a net bag, a locking hinge, two side rotating shaft mechanisms, a middle rotating shaft mechanism and a flap;

[0006] The two side rotating shaft mechanisms include two arranged on both sides of the middle rotating shaft mechanism, and the two rotating shaft seats of the two side rotating shaft mechanisms are respectively connected to the hatch cover and the cabin body, providing torque for the hatch cover when opening; the two rotating shaft seats of the middle rotating shaft mechanism are respectively connected to the cabin body and the flap, and the two sides of the flap are respectively connected to the long plate I of the locking hinge, and the long plate II of the locking hinge is arranged on the hatch cover, and the flap and the cabin body are locked and separated by the locking and separation device I, the middle rotating shaft mechanism provides the hatch cover with a torque when closing, and the torque provided for the hatch cover when closing is greater than the sum of the torques provided by the two side rotating shaft mechanisms; a locking and separation device II is arranged between the hatch cover and the cabin body away from the rotating end, and a signal micro switch for transmitting the hatch cover opening and closing signals by a satellite is arranged next to the locking and separation device II, and when the hatch cover is closed, it is locked and fixed by relying on the locking and separation device II; a launching device and a net bag are arranged in the cabin body.

[0007] Further, the locking hinge also includes a shaft, a swivel and a shaft sleeve;

[0008] One end of long board I and long board II are connected by shaft rotation. When the two long boards of the locking hinge are rotated to the same position, they are locked by turning the head and cannot be rotated, thereby achieving the locking of the flap and the hatch cover.

[0009] Furthermore, the bulkhead of the cabin is hollow, and the locking and separating device I comprises a separating mechanism arranged on the side wall of the cabin and a locking sleeve arranged on the flap, and the locking and separation of the flap and the cabin are achieved through the cooperation of the separating mechanism and the locking sleeve.

[0010] Furthermore, the launch device includes a cone-shaped launch chamber, four traction bodies, four pistons and a bottom igniter;

[0011] Four net bags are installed around the launch device. The net bags are connected to the traction body and are deployed under the drive of the traction body.

[0012] Furthermore, a clamping device is provided at a position of the hatch cover corresponding to the position of the net bag, and the net bag is clamped by the clamping device.

[0013] Furthermore, the locking and separating device I is arranged on an unlocking device bracket, and the unlocking device bracket is fixed to the cabin body by threads.

[0014] Furthermore, an electrical connector is installed on the floor of the cabin, and two electrical connectors are symmetrically distributed to provide power for the entire launch cabin device.

[0015] Furthermore, the launch cabin is rectangular as a whole, the cabin cover is a rectangular plate with a circular protrusion in the middle, the cabin body is connected to four sides by a bottom plate, the bottom plate and the four sides are connected by threaded holes, and each side frame is provided with a weight-reducing hole.

[0016] Furthermore, the locking and separating device II includes a separating mechanism connected to the cabin body and a locking sleeve connected to the cabin cover.

[0017] A method for launching a cable net using the cable net launching cabin comprises the following steps:

[0018] Before the launch cabin is opened, the compression device compresses the net bag to prevent it from collapsing;

[0019] When the launch cabin receives the hatch opening signal, the locking and separation device II receives the signal, the lock sleeve separates from the separation mechanism, and the hatch cover begins to flip under the torque provided by the shaft mechanisms on both sides, and the hatch cover will drive the two locking hinges to flip at the same time. Finally, the hatch cover and the locking hinge flip 270 degrees at the same time to be parallel to the flap, the locking hinge is locked by the rotating head, and the flap is bound to the hatch cover; at this time, the micro switch will transmit the hatch cover opening signal to the satellite;

[0020] The igniter of the launch device ignites the gunpowder to generate high-pressure gas, which pushes the piston and then pushes the traction body to launch, and the traction body drives the net bag to unfold the cable net;

[0021] After the cable net is deployed, the launch cabin needs to be closed again so that the clamping device continues to clamp the net bag to prevent the net bag from escaping from the launch cabin; the launch cabin receives the cabin closing signal, the lock sleeve of the locking and separating device I is disconnected from the separation mechanism, and the flap and the hatch cover are turned 270 degrees in the opposite direction under the action of the torque provided by the intermediate rotating shaft mechanism until the hatch cover and the cabin body are closed again, and the clamping device continues to clamp and fix the net bag; the micro switch (7) transmits the hatch cover closing signal to the satellite.

[0022] Compared with the prior art, the present invention has the following significant advantages:

[0023] Compared with the traditional method of opening and closing the hatch cover by motor drive, the present invention is a launch cabin device that can automatically close the hatch cover. Based on the elastic potential energy provided by the spring, the hatch cover can be opened and closed by separating the lock sleeve of the locking separation device from the locking separation mechanism only when the electrical signal of the hatch opening and closing is received, thereby greatly saving the resources and space of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the initial state of the cable net launching cabin.

[0025] Figure 2 This is a schematic diagram of the cable net launch cabin in the open state.

[0026] Figure 3 It is a schematic diagram of the locking and separation device.

[0027] Figure 4 Schematic diagram of the launch device.

[0028] Figure 5 This is a schematic diagram of a micro switch.

[0029] Figure 6 This is a schematic diagram of the network packet.

[0030] Figure 7 Schematic diagram of the clamping device.

[0031] Figure 8 Schematic diagram of locking hinge.

[0032] Fig. 9 It is a schematic diagram of the left and right rotating shaft mechanism.

[0033] Fig.10 It is a schematic diagram of the intermediate shaft mechanism.

[0034] Description of reference numerals:

[0035] 1-hatch cover, 2-unlocking device bracket, 3-locking and separating device I, 4-electric connector, 5-launching device, 6-cabin, 7-micro switch, 8-locking and separating device II, 9-net bag, 10-pressing device, 11-locking hinge, 12-side rotating shaft mechanism, 13-middle rotating shaft mechanism, 14-flip plate, 301-locking sleeve, 302-separation mechanism, 501-launching chamber, 502-traction body, 503-piston, 504-igniter, 1101 long board I, 1102-shaft, 1103-long board II, 1104-rotating head, 1105-shaft sleeve, 1201-side rotating shaft torsion springs, 1202-side rotating shaft seats, 1203-side rotating shafts, 1301-middle rotating shaft, 1302-middle rotating shaft seat, 1303-middle rotating shaft torsion spring. DETAILED DESCRIPTION

[0036] The present invention is further described in detail below in conjunction with the accompanying drawings.

[0037] like Figure 1-10 As shown, a cable net launch cabin device capable of automatically closing a hatch cover comprises a hatch cover 1, an unlocking device bracket 2, a locking and separating device I3, an electrical connector 4, a launching device 5, a cabin body 6, a micro switch 7, a locking and separating device II8, a net bag 9, a pressing device 10, a locking hinge 11, a left and right rotating shaft mechanism 12, an intermediate rotating shaft mechanism 13, and a flap 14. The entire launch cabin is a rectangular parallelepiped. The hatch cover 1 is connected to the cabin body 6 through the two-side rotating shaft mechanism 12 and the intermediate rotating shaft mechanism 13. The two-side rotating shaft mechanism 12 is composed of two-side rotating shaft torsion springs 1201, two-side rotating shaft seats 1202 and two-side rotating shafts. The two rotating shaft seats 1202 of the two-side rotating shaft mechanism 12 are respectively fixedly connected to the hatch cover 1 and the cabin body 6. The two rotating shaft seats 1202 tend to close under the action of the two-side rotating shaft torsion springs 1201, so the two-side rotating shaft mechanism 12 can provide the hatch cover 1 with torque when opening. The intermediate rotating shaft mechanism 13 is composed of an intermediate rotating shaft 1301, an intermediate rotating shaft seat 1302 and an intermediate rotating shaft torsion spring 1303. The two rotating shaft seats 1302 of the intermediate rotating shaft mechanism 13 are respectively fixedly connected to the cabin body 6 and the flap 14. The two rotating shaft seats 1302 of the intermediate rotating shaft mechanism 13 are in a closed state, and tend to open under the action of the intermediate rotating shaft torsion spring 1303. Therefore, the intermediate rotating shaft 13 can provide the cabin cover 1 with a torque when closing, and the torque provided by the intermediate rotating shaft 13 is greater than the sum of the torques provided by the rotating shaft mechanisms 12 on both sides.

[0038] The unlocking device bracket 2 is fixed to the cabin 6 through the threaded hole, and provides fixed support for the locking and separating device 3. The locking and separating device 3 is composed of a locking sleeve 301 and a separating mechanism 302. The locking and separating device 3 can fix the flap 14. The flap 14 is also installed on the intermediate rotating shaft mechanism 13 and can rotate under the drive of the intermediate rotating shaft mechanism 13.

[0039] A locking hinge 11 is installed on both sides of the flap 14. The locking hinge 11 consists of a long plate I 1101, a long plate II 1103, an axis 1102, a swivel 1104 and a sleeve 1105. When the two long plates of the locking hinge are rotated to the same position, they can be locked by the swivel 1104 and cannot rotate, thereby achieving the locking of the flap 14 and the hatch 1.

[0040] The launch device 5 is composed of a launch cavity 501, four traction bodies 502, four pistons 503 and an igniter 504. Four net bags 9 are installed around the launch device. The net bags 9 are connected to the traction bodies 502 and are deployed under the drive of the traction bodies 502. The net bags 9 are compressed by the compression device 10 connected to the hatch 1 to prevent the net bags 9 from collapsing before and after the cable net is deployed.

[0041] When the hatch cover 1 is closed, it is locked and fixed by means of a locking and separating device II 8. A micro switch 7 is installed next to the locking and separating device II 8 to transmit the signal of opening and closing the hatch cover 1 to the satellite.

[0042] Before the launch cabin is opened, the clamping device 10 will clamp the net bag 9 to prevent the net bag 9 from collapsing. When the launch cabin receives the cabin opening signal, the locking and separation device II8 receives the signal, the lock sleeve is separated from the separation mechanism, and the hatch cover 1 begins to flip under the torque provided by the left and right rotating shaft mechanisms 12, and the hatch cover 1 will drive the two locking hinges 11 to flip at the same time. Finally, the hatch cover 1 and the locking hinge 11 are simultaneously flipped 270° parallel to the flap 14. At this time, the locking hinge 11 is locked by the rotating head 1104, so as to realize the binding of the flap 14 and the hatch cover 1. At this time, the micro switch 7 will transmit the signal of the hatch cover 1 opening to the satellite. Then the igniter 504 of the launch device 5 ignites the gunpowder to generate high-pressure gas, which will push the piston 503 and then push the traction body 502 to launch. At the same time as the traction body 502 is launched, it will drive the net bag 9 to unfold the cable net. After the cable net is unfolded, the launch cabin needs to be closed again so that the clamping device 10 can continue to clamp the net bag 9 to prevent the net bag 9 from escaping from the launch cabin. The specific process is that the launch cabin receives the cabin closing signal, the lock sleeve 301 of the locking and separating device I is automatically disconnected from the separation mechanism 302, and the flap 14 will be turned 270 degrees in the opposite direction together with the hatch 1 under the torque provided by the intermediate shaft mechanism 13, until the hatch 1 and the cabin body 6 are closed again, at which time the pressing device 10 will continue to press and fix the net bag 9. Finally, the micro switch 7 transmits the signal that the hatch 1 is closed to the satellite.

Claims

1. A cable net launching cabin with a hatch that can automatically close, characterized in that: It comprises a rotatably connected hatch cover (1), a locking and separating device I (3), a launching device (5), a cabin body (6), a micro switch (7), a locking and separating device II (8), a net bag (9), a locking hinge (11), two side rotating shaft mechanisms (12), a middle rotating shaft mechanism (13) and a flap (14); The two side rotating shaft mechanisms (12) include two, which are arranged on the two sides of the middle rotating shaft mechanism (13); the two side rotating shaft seats (1202) of the two side rotating shaft mechanisms (12) are respectively connected to the hatch cover (1) and the cabin body (6), so as to provide torque for the hatch cover (1) when opening; the two middle rotating shaft seats (1302) of the middle rotating shaft mechanism (13) are respectively connected to the cabin body (6) and the flap (4); the two sides of the flap (4) are respectively connected to the long plates I of the two locking hinges (11); the long plates II of the locking hinges (11) are arranged on the hatch cover (1); the flap (4) and the cabin body (6) are connected by The locking and separating device I (3) is locked and separated, and the intermediate rotating shaft mechanism (13) provides the hatch cover with a torque when closing, and the torque provided for the hatch cover (1) when closing is greater than the sum of the torques provided by the two rotating shaft mechanisms (12) on both sides; a locking and separating device II (8) is provided between the hatch cover (1) and the cabin body (6) away from the rotating end, and a micro switch (7) for transmitting the opening and closing signal of the hatch cover (1) by a satellite is provided next to the locking and separating device II (8). When the hatch cover (1) is closed, it is locked and fixed by relying on the locking and separating device II (8); a launching device (5) and a net bag (9) are provided in the cabin body (6); The locking hinge (11) further comprises a shaft (1102), a rotating head (1104) and a shaft sleeve (1105); One end of the long board I (1101) and the long board II (1103) are rotatably connected via a shaft (1102). When the two long boards of the locking hinge are rotated to the same position, they are locked by a rotating head (1104) and cannot rotate, thereby achieving the locking of the flap (14) and the hatch cover (1); The cabin wall of the cabin body (6) is hollow, and the locking and separating device I (3) comprises a separating mechanism (302) arranged on the side wall of the cabin body (6) and a locking sleeve (301) arranged on the flap (14), and the locking and separation of the flap (14) and the cabin body are achieved through the cooperation of the separating mechanism (302) and the locking sleeve (301); The launching device (5) comprises a cone-shaped launching cavity (501), four traction bodies (502), four pistons (503) and an igniter (504); Four net bags (9) are installed around the launching device (5), and the net bags (9) are connected to the traction body (502) and are deployed under the drive of the traction body (502); A pressing device (10) is provided at a position of the hatch cover (1) corresponding to the position of the net bag (9), and the net bag (9) is pressed by the pressing device (10).

2. The cable net launching cabin according to claim 1, characterized in that: The locking and separating device I (3) is arranged on the unlocking device bracket (2), and the unlocking device bracket (2) is fixed to the cabin body (6) by means of threads.

3. The cable net launching cabin according to claim 2, characterized in that: The electrical connector is installed on the floor of the cabin. The two electrical connectors are symmetrically distributed to provide power for the entire launch cabin device.

4. The cable net launching cabin according to claim 3, characterized in that: The launch cabin is rectangular in shape as a whole, the cabin cover (1) is a rectangular plate with a circular protrusion in the middle, the cabin body is connected by a bottom plate and four side frames, the bottom plate and the four side frames are connected by threaded holes, and each side frame is provided with a weight reduction hole.

5. The cable net launching cabin according to claim 4, characterized in that: The locking and separating device II (8) comprises a separating mechanism connected to the cabin body and a locking sleeve connected to the cabin cover.

6. A method for launching a cable net using the cable net launching cabin according to any one of claims 1 to 5, characterized in that: The steps include: Before the launch cabin is opened, the pressing device (10) presses the net bag (9) to prevent the net bag (9) from collapsing; When the launch module receives the signal to open the module, the locking and separation device II (8) receives the signal, the lock sleeve separates from the separation mechanism, the module cover (1) starts to flip under the torque provided by the rotating shaft mechanisms (12) on both sides, and the module cover (1) drives the two locking hinges (11) to flip at the same time, and finally the module cover (1) and the locking hinges (11) flip 270 degrees at the same time to be parallel to the flap (14), the locking hinges (11) are locked by the rotating head (1104), and the flap (14) is bound to the module cover (1); at this time, the micro switch (7) transmits the module cover (1) opening signal to the satellite; The igniter (504) of the launching device (5) ignites gunpowder to generate high-pressure gas, and the high-pressure gas pushes the piston (503) and then pushes the traction body (502) to launch, and the traction body (502) drives the net bag (9) to unfold the cable net; After the cable net is deployed, the launch cabin needs to be closed again so that the pressing device (10) continues to press the net bag (9) to prevent the net bag (9) from escaping from the launch cabin; The launch cabin receives the cabin closing signal, the lock sleeve of the locking and separating device I is disconnected from the separating mechanism, and the flap (14) and the cabin cover (1) are turned 270 degrees in the opposite direction under the action of the torque provided by the intermediate rotating shaft mechanism (13) until the cabin cover (1) and the cabin body (6) are closed again, and the clamping device (10) will continue to clamp and fix the net bag (9); the micro switch (7) transmits the cabin cover (1) closing signal to the satellite.

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