CN213057578U

CN213057578U - Hinge type satellite spray pipe capturing device

Info

Publication number: CN213057578U
Application number: CN202021611861.0U
Authority: CN
Inventors: 张瀚林
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-08-06
Filing date: 2020-08-06
Publication date: 2021-04-27
Anticipated expiration: 2030-08-06

Abstract

A hinge type satellite spray pipe capturing device belongs to the technical field of aerospace. The method is used for capturing the space non-cooperative target satellite so as to carry out operations such as repair, maintenance and refueling of parts. The invention includes a fast capture mechanism and a slow lock mechanism. The main action completing mode is as follows: 1) in the capturing process, the screw rod drives the sliding sleeve to move, the constraint of the pull rod bottom block is removed, the capturing spring pushes the pull rod to move, the opening action of the hinge capturing mechanism is completed, and the sliding sleeve restrains the pull rod bottom block again to keep capturing action; 2) in the locking process, the screw drives the sliding sleeve at a low speed to drive the sleeve to approach the target satellite and complete locking; 3) in the releasing process, the lead screw drives the sliding sleeve to push the capturing mechanism away from the target satellite and remove the restraint on the pull rod bottom block, and the push-pull electromagnet enables the pull rod bottom block to reset to complete releasing.

Description

Hinge type satellite spray pipe capturing device

Technical Field

The invention relates to a hinge type satellite nozzle capturing device, which is mainly used for capturing a space non-cooperative target and belongs to the technical field of aerospace.

Background

With the rapid development of space technology, more and more space vehicles are launched into space for activities in the fields of civilian use, scientific research, military use and the like. Due to the complex structure and system of the aerospace craft and the shortage of research and development technology, the parts of the aerospace craft are easy to be damaged in the complex space environment, so that the aerospace craft cannot normally operate, and a great deal of economic loss is caused. There are also many aerospace vehicles that cannot continue to operate because of fuel depletion. Therefore, space docking is needed to perform component replacement, maintenance, refueling and other operations on the failed aerospace vehicle so as to prolong the service life of the aerospace vehicle and reduce economic loss.

At present, the space docking technology researched at home and abroad mainly comprises a space cooperative target docking technology and a space non-cooperative target docking technology. The application conditions of the space cooperation target docking technology are very harsh, and the capture target is required to be provided with a docking ring, a variant isomorphic mechanism and other structures which can be used for docking. However, not all in-orbit aerial vehicles have passive capture mechanisms that match the serving satellite capture mechanisms. The space non-cooperative target docking technology is wide in application range and strong in adaptability, and can be used for targets such as satellites without passive capturing mechanisms and space garbage. At present, domestic researches on a space non-cooperative target docking technology are many, and mainly a docking technology based on the outer contour of a target satellite nozzle is reported in document 1 (dawn snow, research on a non-cooperative target docking and capturing mechanism [ D ]. hamabin industry university, 2009). The device has large volume and mass and high requirement on driving of the movable mechanical arm because the capture is carried out through the outline of the spray pipe.

In conclusion, the research on the space non-cooperative target docking technology has a very good research and development prospect. The invention is a space butt joint device based on the inner hole of the satellite spray pipe and has wide application range.

Disclosure of Invention

The invention aims to design a hinge type capturing device based on an inner hole of a satellite spray pipe, which has the characteristics of wide application range and strong adaptability and can be used for butt joint of a space non-cooperative target with a spray pipe structure.

The technical scheme of the invention is as follows: a hinge type satellite spray pipe capturing device is characterized in that three hinges are mounted on a sleeve and a pull rod through pin shafts, and the included angle between each group of hinges is 120 degrees; the pull rod is arranged in the sleeve; the lower end of the pull rod is connected with a pull rod bottom block, and a capture spring is arranged between the pull rod bottom block and the sleeve; the lower end of the sleeve is provided with a sleeve bottom block, and the pull rod bottom block is positioned in the sleeve bottom block; six conical holes in the upper part of the sleeve bottom block are provided with positioning and locking steel balls, and the conical holes can prevent the locking steel balls from entering the sliding area of the pull rod bottom block; the lower part of the sleeve bottom block is provided with a push-pull electromagnet for resetting the pull rod bottom block; six pulling and locking steel balls are arranged in six cylindrical holes in the lower part of the sleeve bottom block, and an end cover of the sleeve bottom block is matched with the sliding sleeve to prevent the pulling and locking steel balls from being separated from the cylindrical holes; a sliding sleeve is sleeved outside the sleeve bottom block, and a capturing guide flat key is arranged on the sliding sleeve and can slide in the front end shell along the axial direction; the sliding sleeve bottom block is connected to the lower end of the sliding sleeve, and a thrust spring is arranged between the sliding sleeve bottom block and the sleeve bottom block end cover; a lead screw nut sliding block is arranged in the sliding sleeve bottom block, and a lead screw nut is arranged on the lead screw nut sliding block; the screw nut sliding block is provided with a locking guide flat key which can slide in the bottom block of the sliding sleeve along the axial direction; the tail end of the bottom block of the sliding sleeve is provided with a sliding sleeve end cover, a disc spring is arranged between the sliding sleeve end cover and the screw nut, and the disc spring is sleeved outside the screw; the lead screw is arranged on the second shell, and the tail end of the lead screw is also provided with an angular contact bearing and a lead screw locking block; the second housing is mounted at the end of the front housing; the speed reducing motor is arranged on the motor mounting end cover; the motor mounting end cover is arranged on the bearing pressing block; the bearing pressing block is arranged on the second shell; a third housing is mounted at the second housing end.

The rapid capturing mechanism consisting of the capturing spring, the pull rod bottom block, the positioning locking steel ball, the sleeve bottom block and the sliding sleeve in the device can drive the sliding sleeve at a low speed and simultaneously realize rapid unfolding of the capturing structure, so that the target satellite is prevented from escaping.

The device can pull the sleeve bottom block to move at a low speed through the sliding sleeve, realize low-speed tensioning on the target satellite, and prevent the occurrence of large load caused by severe conflict in the process of capturing the target satellite.

The locking force required by the device for locking the target satellite is provided by the disc spring.

The device can realize the reset of the pull rod bottom block by utilizing the action control of the control circuit board on the push-pull type electromagnet so as to reset the hinge capturing mechanism.

The invention has the beneficial effects that:

1. the application range is wide, and most spacecrafts are provided with the spray pipe structure, so that the application range of the invention is wide;

2. the adaptability is strong, the capture diameter is larger after the hinge is opened, and the hinge can adapt to different nozzle throat sizes;

3. the capturing spring can be used for rapidly opening the hinge in the capturing process, and the lead screw drives the sliding sleeve to slowly lock the target satellite, so that the severe conflict in the capturing process of the target satellite can be prevented, and the occurrence of large load can be avoided.

Drawings

FIG. 1 is a schematic structural diagram of a hinge-type satellite nozzle capture device according to the present invention;

FIG. 2 is a schematic structural diagram of a sliding sleeve in the articulated satellite nozzle capture device of the present invention;

FIG. 3 is a schematic view of a drawbar bottom block in the hinge-type satellite nozzle capture device of the present invention;

FIG. 4 is a schematic view of a bottom block of a sleeve in the articulated satellite nozzle capture device of the present invention;

FIG. 5 is an external view of the articulated satellite nozzle capture device of the present invention;

FIG. 6 is a schematic view of the hinge opening of the hinged satellite nozzle capture device of the present invention;

FIG. 7 is a schematic diagram of the hinge-type satellite nozzle capturing device for capturing a satellite nozzle according to the present invention.

In fig. 1:

1. the hinge comprises a hinge, 2, a pull rod, 3, a sleeve, 4, a front end shell, 5, a capture spring, 6, a pull rod bottom block, 7, a positioning locking steel ball, 8, a sleeve bottom block, 9, a capture guide flat key, 10, a push-pull type electromagnet, 11, a pulling locking steel ball, 12, a sleeve bottom block end cover, 13, a sliding sleeve, 14, a thrust spring, 15, a sliding sleeve bottom block, 16, a second shell, 17, a lock guide flat key, 18, a lead screw nut sliding block, 19, a lead screw nut, 20, a lead screw, 21, a disc spring, 22, a sliding sleeve end cover, 23, an angular contact ball bearing, 24, a lead screw locking block, 25, a bearing pressing block, 26, a coupler, 27, a motor mounting end cover, 28, a speed reducing motor and 29, and a third shell.

In fig. 2:

13. sliding sleeve, 131, sliding sleeve upper end groove, 132, sliding sleeve lower end bevel edge.

In fig. 3:

6. a pull rod bottom block 61, a groove at the upper end of the pull rod bottom block, and 62, the bevel edge at the lower end of the pull rod bottom block.

In fig. 4:

8. the sleeve comprises a sleeve bottom block 81, a conical hole at the upper end of the sleeve bottom block, and a cylindrical hole at the lower end of the sleeve bottom block 82.

In fig. 5:

30. satellite spray pipes.

Detailed Description

Referring to fig. 1, the invention relates to a hinge type satellite nozzle capturing device, which comprises a hinge 1, a pull rod 2, a sleeve 3, a front end shell 4, a capturing spring 5, a pull rod bottom block 6, a positioning locking steel ball 7, a sleeve bottom block 8, a capturing guide flat key 9, a push-pull type electromagnet 10, a pulling locking steel ball 11, a sleeve bottom block end cover 12, a sliding sleeve 13, a thrust spring 14, a sliding sleeve bottom block 15, a second shell 16, a locking guide flat key 17, a lead screw nut slider 18, a lead screw nut 19, a lead screw 20, a disc spring 21, a sliding sleeve end cover 22, an angular contact ball bearing 23, a lead screw locking block 24, a bearing pressing block 25, a coupler 26, a motor mounting end cover 27, a speed reducing motor 28 and a third shell 29.

The hinge 1 is installed on a pull rod 2 and a sleeve 3 through a pin shaft, a pull rod bottom block 6 is connected with the pull rod 2 through threads, a capture spring 5 is installed between the pull rod bottom block 6 and the sleeve 3, a sleeve bottom block 8 is connected with the sleeve 3 through a bolt, a positioning and locking steel ball 7 is installed in a conical hole in the upper portion of the sleeve bottom block 8, a push-pull electromagnet 10 is installed in the sleeve bottom block 8, a sliding sleeve 13 is sleeved outside the sleeve bottom block 8, and the above components form a quick capture mechanism;

a sliding sleeve bottom block 15 is connected with a sliding sleeve 13 through a bolt, a capturing guide flat key 9 is installed on the sliding sleeve 13, a lead screw nut slider 18 is installed in the sliding sleeve bottom block 15, a locking guide flat key 17 is installed on the lead screw nut slider 18, a lead screw nut 19 is installed on the lead screw nut slider 18, a lead screw 20 is matched with the lead screw nut 19, a sliding sleeve end cover 22 is connected with the sliding sleeve bottom block 15 through a bolt, a disc spring 21 is installed between the sliding sleeve end cover 22 and the lead screw nut 19, and the slow locking mechanism is formed by the above parts;

the screw 20 is installed on the second shell 16, the second shell 16 is connected with the front end shell 4 through a bolt, the angular contact ball bearing 23 is arranged between the screw 20 and the second shell 16, the screw locking block 24 is installed on the screw 20, the bearing pressing block 25 is connected with the second shell 16 through a bolt, the motor installation end cover 27 is connected with the bearing pressing block 25 through a bolt, the motor 28 is installed on the motor installation end cover 27, the motor 28 is connected with the screw 20 through the coupler 26, the third shell 29 is connected with the second shell 16 through a bolt, and the driving part is formed by the above components.

The working principle of the invention is as follows:

1. and (3) a capturing process: the sliding sleeve 13 is driven to move downwards by the threaded spindle 20. The sliding sleeve recess 131 will align with the sleeve bottom block upper end conical bore 81 during downward movement of the sliding sleeve 13. The positioning locking steel ball 7 is not restrained by the sliding sleeve 13. The pull rod bottom block 6 moves downwards under the thrust of the capture spring 5, and the positioning locking steel ball 7 is extruded into the groove 131 of the sliding sleeve by the inclined edge 62 at the lower end of the pull rod bottom block. The pull rod bottom block 6 continues to move downwards until the lower end limit position is contacted with the sleeve bottom block 8. At this time, the upper hinge 1 is unfolded to capture the target satellite. In the process, the sliding sleeve 13 is moved slowly downwards. When the inclined edge of the groove 131 of the sliding sleeve is in contact with the positioning locking steel ball 7, the positioning locking steel ball 7 is extruded into the groove 61 at the upper end of the bottom block of the pull rod, the unfolding state of the hinge is kept, and the target satellite is captured.

2. And (3) tensioning: the sliding sleeve 13 continues to move downwards after the hinge 1 is unfolded. When the bevel edge 132 at the lower end of the sliding sleeve is clamped and pulled, the locking steel ball 11 is pulled, and then the quick capturing mechanism is driven to move downwards integrally. After the front-end shell 4 is contacted with the target satellite spray pipe, the screw nut 19 continues to move downwards again to compress the disc spring 21, and the disc spring 21 provides locking force required by locking.

3. And (3) a release process: when release is required, the sliding sleeve 13 is driven upward by the lead screw 20. In the process of upward movement of the sliding sleeve 13, the push-pull electromagnet 10 is always in an electrified state and is propped against the bottom of the pull rod bottom block 6. During the upward movement of the sliding sleeve 13, the sliding sleeve upper groove 131 is aligned with the sleeve bottom block upper end conical bore 81. The positioning locking steel ball 7 is not restrained by the sliding sleeve 13. The pull rod bottom block 6 moves upwards under the thrust action of the push-pull electromagnet 10, and the positioning locking steel ball 7 is extruded into the groove 131 on the sliding sleeve. The push-pull electromagnet 10 pushes the pull rod bottom block 6 which is not restrained by the positioning locking steel ball 7 back to the initial position. When the sliding sleeve 13 moves upwards, the inclined edge of the groove 131 at the upper end of the sliding sleeve extrudes the positioning locking steel ball 7 back to the sleeve bottom block 8 to clamp the inclined edge 62 at the lower end of the pull rod bottom block, so that the pull rod bottom block 6 is in a pre-capture state. At this time, the target satellite is not restrained by the hinge type capturing device any more, and the release is completed. When the sliding sleeve 13 pushes the sleeve 3 back to the front end shell 4 to contact, the push-pull electromagnet 10 is powered off, and the whole device returns to the initial state before capture.

Claims

1. A hinge type satellite spray pipe capturing device is characterized in that three hinges (1) are mounted on a sleeve (3) and a pull rod (2) through pin shafts, and the included angle between each group of hinges (1) is 120 degrees; the pull rod (2) is arranged in the sleeve (3); the lower end of the pull rod (2) is connected with a pull rod bottom block (6), and a capture spring (5) is arranged between the pull rod bottom block (6) and the sleeve (3); the lower end of the sleeve (3) is provided with a sleeve bottom block (8), and the pull rod bottom block (6) is positioned in the sleeve bottom block (8); six conical holes in the upper part of the sleeve bottom block (8) are provided with positioning and locking steel balls (7), and the conical holes can prevent the locking steel balls from entering the sliding area of the pull rod bottom block; the lower part of the sleeve bottom block (8) is provided with a push-pull electromagnet which is used for resetting the pull rod bottom block (6); six pulling locking steel balls (11) are arranged in six cylindrical holes in the lower part of the sleeve bottom block (8), and the sleeve bottom block end cover (12) is matched with the sliding sleeve (13) to prevent the pulling locking steel balls (11) from being separated from the cylindrical holes; a sliding sleeve (13) is sleeved outside the sleeve bottom block (8), and a capturing guide flat key (9) is arranged on the sliding sleeve (13) and can slide in the front end shell (4) along the axial direction; a sliding sleeve bottom block (15) is connected to the lower end of the sliding sleeve (13), and a thrust spring (14) is arranged between the sliding sleeve bottom block (15) and the sleeve bottom block end cover (12); a screw nut sliding block (18) is arranged in the sliding sleeve bottom block (15), and a screw nut (19) is arranged on the screw nut sliding block (18); a locking guide flat key (17) is arranged on the screw nut sliding block (18) and can slide in the sliding sleeve bottom block (15) along the axial direction; a sliding sleeve end cover (22) is arranged at the tail end of the sliding sleeve bottom block (15), a disc spring (21) is arranged between the sliding sleeve end cover (22) and the screw rod nut (19), and the disc spring (21) is sleeved outside the screw rod (20); the screw rod (20) is installed on the second shell (16), and an angular contact bearing (23) and a screw rod locking block (24) are further installed at the tail end of the screw rod (20); the second housing (16) is mounted at the end of the front housing (4); the speed reducing motor (28) is arranged on the motor mounting end cover (27); the motor mounting end cover (27) is mounted on the bearing pressing block (25); the bearing press block (25) is mounted on the second housing (16); a third housing (29) is mounted on the end of the second housing (16).

2. The device according to claim 1, characterized in that a rapid capturing mechanism consisting of the capturing spring (5), the pull rod bottom block (6), the positioning locking steel ball (7), the sleeve bottom block (8) and the sliding sleeve (13) can realize rapid unfolding of the capturing structure while driving the sliding sleeve (13) at a slow speed, so as to avoid the target satellite from escaping.

3. The device according to claim 1, further characterized in that the sliding sleeve (13) pulls the sleeve bottom block (8) to move slowly, so that the target satellite is tensioned slowly, and the process of capturing the target satellite can be prevented from violent collision, thereby causing large load.

4. The device of claim 1, further characterized in that the locking force for locking the target satellite is provided by a disc spring (21).

5. A device according to claim 1, further characterized in that the return of the pull rod bottom block (6) to return the hinge catch mechanism is achieved by the control of the push-pull electromagnet by the control circuit board.