CN111071494A - Space capturing butt joint mechanism - Google Patents
Space capturing butt joint mechanism Download PDFInfo
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- CN111071494A CN111071494A CN201911374214.4A CN201911374214A CN111071494A CN 111071494 A CN111071494 A CN 111071494A CN 201911374214 A CN201911374214 A CN 201911374214A CN 111071494 A CN111071494 A CN 111071494A
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- bevel gear
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- 230000007246 mechanism Effects 0.000 title claims abstract description 54
- 210000001503 joint Anatomy 0.000 title claims description 23
- 210000000078 claw Anatomy 0.000 claims abstract description 62
- 238000003032 molecular docking Methods 0.000 claims abstract description 38
- 230000005540 biological transmission Effects 0.000 claims abstract description 28
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 26
- 239000007788 liquid Substances 0.000 claims abstract description 26
- 238000009434 installation Methods 0.000 claims abstract description 4
- 230000002093 peripheral effect Effects 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 14
- 230000008569 process Effects 0.000 claims description 14
- 239000012530 fluid Substances 0.000 claims 3
- 238000002474 experimental method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000003472 neutralizing effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
Abstract
The invention discloses a space capturing docking mechanism, which comprises a docking mechanism a and a docking mechanism B, wherein peripheral equipment comprises a spacecraft A and a spacecraft B, and the docking mechanism a comprises: the device comprises an electric connector a, a cylinder body, a fixed frame, a liquid circuit disconnector a, a positioning pin, a holding claw, a driving end guide flap, a holding claw rotating shaft a, a holding claw rotating shaft b, a ball screw nut, a ball screw, a bearing end cover, a bearing a, a bevel gear b, a transmission shaft, a bevel gear, a key, a motor reducer, a bevel gear ring, a motor, a bearing b and a bevel gear ring supporting rod; the docking mechanism b includes: the passive end installation base plate is arranged on the passive end base plate; the invention can realize guiding, positioning and butting, active capturing, active tightening, blind plugging and unplugging of the electric connector, plugging and unplugging of the liquid circuit disconnector and rigid locking of the aircraft interface and the spacecraft berthing platform by a simple structure.
Description
Technical Field
The invention belongs to the field of space application equipment, and particularly relates to a space capturing and butting mechanism.
Background
High-orbit aircraft platforms are evolving towards service stations, with a large number of aircraft parking interfaces deployed on the parking platform to enable on-orbit service capabilities. A large number of exposure load experiment platforms are arranged on the outer wall of a cabin body of a space vehicle such as a space station, a manned spacecraft and the like so as to expand the exposure experiment capability of the space vehicle. At present, international space stations use various types of load butt joint locking interface devices and capture butt joint devices to support exposure experiment tasks; the on-orbit verification project implemented in the united states and the like supports aircraft docking experimental tasks using various forms of capture docking devices.
However, the capture docking device in the prior art is complex and high in cost.
Disclosure of Invention
In view of the above, the present invention provides a space capture docking mechanism, which can achieve guiding, positioning, docking, active capture, active tightening, blind plugging of an electrical connector, plugging of a liquid circuit breaker, and rigid locking of an aircraft interface and a spacecraft parking platform with a relatively simple structure, thereby providing technical support for docking various aircrafts and serving aircraft extravehicular set positions.
The technical scheme for realizing the invention is as follows:
a space capturing docking mechanism comprises a docking mechanism a and a docking mechanism B, wherein peripheral equipment comprises a spacecraft A and a spacecraft B, the spacecraft A is a space service platform, and the spacecraft B is a spacecraft;
docking mechanism a includes: the device comprises an electric connector a, a cylinder body, a fixed frame, a liquid circuit disconnector a, a positioning pin, a holding claw, a driving end guide flap, a holding claw rotating shaft a, a holding claw rotating shaft b, a ball screw nut, a ball screw, a bearing end cover, a bearing a, a bevel gear b, a transmission shaft, a bevel gear, a key, a motor reducer, a bevel gear ring, a motor, a bearing b and a bevel gear ring supporting rod;
the docking mechanism b includes: the passive end installation base plate is arranged on the passive end base plate;
the butting mechanism a is provided with 4 fixed frames which are uniformly distributed around the barrel body at 90 degrees, the 4 fixed frames are provided with an electric connector a and a liquid circuit breaker a in a staggered manner, and one side of each fixed frame, which is close to the barrel body, is provided with an installation interface for fixedly connecting the fixed frame to the barrel body;
the electric connector a and the liquid circuit breaker a are provided with mounting interfaces and are fixedly connected on the fixed frame through screws; each fixed frame is provided with a pair of active end guide flaps, the butt joint mechanism a is provided with 8 active end guide flaps in total, and each pair of active end guide flaps are symmetrical in structure and are symmetrically arranged on two sides of the holding claw; the positioning pin is used for performing fine positioning in the process of capturing and butting the active end and the passive end, and a threaded hole is formed in the bottom of the positioning pin and is installed on the fixed frame through a screw;
the transmission shaft is fixed on the fixed frame through a pair of bearings a, a key groove is formed in the transmission shaft, and the bevel gear and the transmission shaft synchronously rotate through key matching; the ball screw is fixed on the fixed frame through bearings at two ends, wherein the bearing at the upper end of the ball screw is fixed on the fixed frame through a bearing end cover, and the bearing a at the lower end of the ball screw is clamped in the bearing groove by a structure at the lower end of the fixed frame, so that the ball screw rotates along the axial direction of the ball screw;
the bevel gear a is fixed on the transmission shaft through a key and a sleeve, so that the bevel gear a only synchronously rotates along the axial direction of the transmission shaft without relative slippage; the middle of the bevel gear b is provided with a through hole which is fixedly connected with a threaded hole at the bottom end of the ball screw through a screw, so that the bevel gear b and the ball screw rotate coaxially; the included angle between the central axes of the bevel gear a and the bevel gear b is 90 degrees, and the transmission steering function of the bevel gear a and the bevel gear b is realized through the matching angle;
the ball screw nut moves up and down along with the rotation of the ball screw, a hole groove is formed in the ball screw nut, a claw holding rotating shaft b is inserted into the hole groove, and the claw holding rotating shaft b is fixed on the ball screw nut through a pin; the claw-holding rotating shaft a is fixed in a corresponding hole of the fixed frame;
the upper end of the holding claw is a cuboid, the middle part of the holding claw is a cuboid structure vertical to the cuboid at the upper end, and the lower half part of the holding claw is a cuboid which forms a certain angle with the cuboid at the middle part; the middle positions of the middle part and the lower half part of the holding claw in the length direction are provided with long grooves parallel to the length direction and used for being matched with a holding claw rotating shaft a to restrain the motion trail of the holding claw; a round hole is formed in the middle of the lower half part of the holding claw in the length direction, is sleeved on the holding claw rotating shaft b and is used for being matched with the holding claw rotating shaft b to drive the holding claw to move up and down;
the cylinder body is cylindrical and is provided with 4 fixing frames, a bevel gear ring supporting rod and a mounting interface of a motor reducer, and meanwhile, the bottom of the cylinder body is provided with the mounting interface fixed on the aircraft A; the outer side of the lower half part of the cylinder body is provided with 4 symmetrically distributed holes for avoiding the transmission shaft and avoiding interference; 4 mounting surfaces are arranged in the lower half part of the cylinder body, one mounting surface is used for mounting a motor reducer, and the other three mounting surfaces are used for mounting and fixing a transmission shaft and a bevel gear;
the front end surface and the rear end surface of the motor reducer are respectively provided with a mounting hole, the rear end surface and a hole corresponding to the motor are fixed together by using screws to form an integral motor-reducer structure, and the mounting hole of the front end surface is connected with a corresponding mounting surface in the cylinder body so that the motor reducer structure is fixed in the cylinder body; the front end of the motor reducer is provided with an output shaft, the output shaft is connected with the bevel gear through key matching, and when the motor rotates, the motor reducer can drive the bevel gear to rotate;
the bevel gear ring support rod is provided with a mounting hole, the bevel gear ring support rod is fixed in the cylinder body through the mounting hole, a bearing b is sleeved on the bevel gear ring support rod, gaskets are arranged at two ends of the bearing b, the position of the bearing b is fixed, and the bearing b can only rotate along the axial direction of the bearing b; a groove is formed in the bevel gear ring, and the bearing b is embedded in the groove to support the bevel gear ring so that the bevel gear ring rotates along the central axis of the bevel gear ring;
the passive end mounting base plate is provided with a mounting hole which is fixedly connected with the aircraft B; the passive end base is provided with a mounting hole which is fixedly connected with the passive end mounting base plate, the electric connector b, the liquid circuit breaking connector b and the passive end guide flap, and the passive end base is provided with a positioning hole which is used for being matched with a positioning pin on the butt joint mechanism a to realize the precise positioning in the butt joint process.
Furthermore, the holding claw is connected with the driven end mounting base plate to realize clamping and locking of the mechanism.
Furthermore, the positioning pin is connected with the driven end mounting base plate, so that the accurate positioning in the butt joint process is realized.
Furthermore, the electric connector a and the liquid circuit disconnector a are respectively connected with the electric connector b and the liquid circuit disconnector b, so that the connection between a circuit and a liquid circuit in the butt joint process is realized.
Furthermore, the active end guide flap and the passive end guide flap are matched with each other, so that coarse positioning in the structure capturing and butting process is realized.
Has the advantages that:
the invention can realize continuous active capture butt joint, blind plugging of the electric connector, plugging and unplugging of the liquid circuit disconnection device and rigid locking of the spacecraft by the capture butt joint mechanism, thereby providing technical support for the spacecraft to be butted by the space service platform.
Drawings
FIG. 1 is a schematic view of the overall layout of the docking mechanism of the present invention;
FIG. 2 is a body structure of a space capture docking mechanism a;
fig. 3, 4 and 5 are detailed composition schematic diagrams of the space capture docking mechanism a;
fig. 6 is a schematic diagram of the composition of the space capture docking mechanism b.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a space capturing and docking mechanism which comprises a space capturing and docking mechanism a and a docking mechanism B as shown in fig. 1, wherein peripheral equipment comprises a spacecraft A and a spacecraft B, the spacecraft A is a space service platform, and the spacecraft B is a spacecraft.
The space capture docking mechanism a as shown in fig. 1 to 5 includes: the device comprises an electric connector a1, a cylinder body 2, a fixed frame 3, a liquid circuit breaker a4, a positioning pin 5, a holding claw 6, a driving end guide vane 7, a holding claw rotating shaft a8, a holding claw rotating shaft b9, a ball screw nut 10, a ball screw 11, a bearing end cover 12, a bearing a13, a bevel gear a14, a bevel gear b15, a transmission shaft 16, a bevel gear 17, a key 18, a motor reducer 19, a bevel gear ring 20, a motor 21, a bearing b22 and a bevel gear ring support rod 23.
The butt joint mechanism a is provided with 4 fixed frames 3 which are uniformly distributed around the barrel body 2 at 90 degrees, the 4 fixed frames 3 are alternately provided with an electric connector a1 and a liquid circuit breaker a4, and one side of the fixed frame 3 close to the barrel body 2 is provided with a mounting interface for fixedly connecting the fixed frame 3 with the barrel body 2.
The electric connector a1 (the liquid circuit breaker a4) is provided with a mounting interface, and the electric connector a1 (the liquid circuit breaker a4) is fixedly connected with the fixed frame 3 through screws; each fixed frame 3 is provided with a pair of active end guide flaps 7, the butt joint mechanism a is provided with 8 active end guide flaps 7 in total, and each pair of active end guide flaps 7 is symmetrical in structure and is symmetrically arranged on two sides of the holding claw 6; the positioning pin 5 is used for capturing and finely positioning the butt joint process of the active end and the passive end, and the bottom of the positioning pin is provided with a threaded hole and is installed on a specified position of the fixed frame 3 through a screw.
The transmission shaft 16 is fixed to the fixed frame 3 by a pair of bearings a13, and the transmission shaft 16 is provided with a key groove, and the bevel gear 17 and the transmission shaft 16 can rotate synchronously by the cooperation of the key 18. The ball screw 11 is fixed on the fixed frame 3 through the bearings a13 at both ends, wherein the bearing at the upper end of the ball screw 11 is fixed on the fixed frame 3 through the bearing end cover 12, the lower end bearing a13 is clamped in the bearing groove by the structure at the lower end of the fixed frame 3, and the ball screw 11 can rotate along the axial direction.
Bevel gear a14 is fixed to drive shaft 16 by a key and a socket so that bevel gear a14 can only rotate synchronously along the drive shaft axis without relative slippage. The middle of the bevel gear b15 is a through hole which is fixedly connected with the threaded hole at the bottom end of the ball screw 11 through a screw, so that the bevel gear b15 and the ball screw 11 rotate coaxially. The included angle between the central axes of the bevel gear a14 and the bevel gear b15 is 90 degrees, and the transmission steering function of the bevel gear a14 and the bevel gear b15 is realized through the matching angle.
The ball screw nut 10 moves up and down with the rotation of the ball screw 11, and a hole groove is formed in the ball screw nut 10, and the pawl rotation shaft b9 is inserted into the hole groove, and the pawl rotation shaft b9 is fixed to the ball screw nut 10 by a pin. The claw rotating shaft a8 is fixed in a corresponding hole of the fixed frame 3.
Embrace 6 upper ends of claws and be a cuboid, the middle part is the longer cuboid of perpendicular to upper end cuboid, and the lower half is the cuboid that is certain angle with the middle part cuboid. The middle positions of the middle part and the lower half part of the holding claw 6 in the length direction are provided with long grooves parallel to the length direction, and the long grooves are used for being matched with the holding claw rotating shaft a8 to restrict the motion trail of the holding claw 6. A round hole is formed in the middle of the lowest half part of the holding claw 6 in the length direction, and the round hole is sleeved on the holding claw rotating shaft b9 and used for being matched with the holding claw rotating shaft b9 to drive the holding claw to move up and down through the ball screw nut 10.
The cylinder 2 is cylindrical and is provided with 4 mounting interfaces of a fixed frame 3, a bevel gear ring support rod 23 and a motor reducer 19, and meanwhile, the bottom of the cylinder 2 is provided with a mounting interface fixed on an aircraft A. The outer side of the lower half part of the cylinder body 2 is provided with 4 symmetrically distributed holes for avoiding the transmission shaft 16 and avoiding interference. The inside of the lower half part of the cylinder body 2 is provided with 4 mounting surfaces, one of which is used for mounting a motor reducer 19, and the other three mounting surfaces are used for mounting and fixing a transmission shaft 16 and a bevel gear 17
The front end face and the rear end face of the motor reducer 19 are respectively provided with a mounting hole, the rear end face and a corresponding hole of the motor 21 are fixed together by screws to form an integral motor-reducer structure, and the mounting holes on the front end face are connected with a corresponding mounting surface in the barrel 2, so that the motor-reducer structure is fixed in the barrel 2. The front end of the motor reducer 19 is provided with an output shaft, the output shaft is connected with the bevel gear 17 through key matching, and when the motor 21 rotates, the motor reducer 19 can drive the bevel gear 17 to rotate.
The bevel gear ring support rod 23 is provided with a mounting hole, the mounting hole is fixed in the cylinder body 2, a bearing b22 is sleeved on the mounting hole, gaskets are arranged at two ends of the bearing b22 to fix the position of the bearing b 3526, and the bearing b22 can only rotate along the axial direction of the bearing b. The bevel ring gear 20 has a groove formed therein, and a bearing b22 is inserted into the groove to support the bevel ring gear so that the bevel ring gear can rotate along its central axis.
The space capture docking mechanism b shown in fig. 6 includes: an electric connector b24, a passive end mounting base plate 25, a passive end base 26, a liquid circuit breaker b27 and a passive end guide vane 28.
The passive end mounting base plate 25 is provided with a mounting hole which is fixedly connected with the aircraft B. The passive end base 26 is provided with a mounting hole which is fixedly connected with a passive end mounting bottom plate, an electric connector b24, a liquid circuit breaker b27 and a passive end guide flap 28, and meanwhile, the passive end base 26 is provided with a positioning hole which is used for being matched with a positioning pin 5 on the butt joint mechanism a to realize the fine positioning in the butt joint process.
The working principle of the invention is as follows:
step 1, synchronously expanding 4 holding claws of a space capture butt joint mechanism a to the maximum position, and outwards expanding the holding claws to the maximum angle;
and 4, controlling a motor 21 of the space capturing and butting mechanism a to drive an internal mechanism to enable 4 holding claws 6 to pull the space capturing and butting mechanism b to be attached to the upper surface of the fixed frame 3, and synchronously completing the plugging of the blind-plugging electric connector and the liquid circuit breaker.
The unlocking process is the reverse of the locking process.
In the pulling and neutralizing process, the motor 21 drives the bevel gear 17 connected with the motor reducer 19 to rotate, the bevel gear 17 drives the bevel gear ring 20 to rotate, and the bevel gear ring 20 drives the other 3 bevel gears 17 to rotate, so that the synchronous rotation of the 4 bevel gears 17 is realized. Meanwhile, the bevel gear 17 drives the transmission shaft 16 to rotate, the bevel gear a14 is fixedly connected with the transmission shaft 16, the bevel gear b15 is fixedly connected with the ball screw 11, the ball screw 11 is driven to rotate through the angle meshing relationship between the bevel gear a14 and the bevel gear b15, and the ball screw 11 drives the ball screw nut 10 to move up and down.
The hole in the lower half part of the holding claw 6 is connected with the ball screw nut 10 through the holding claw rotating shaft b9, so that the holding claw 6 can move up and down while rotating along the central axis of the holding claw rotating shaft b9, the holding claw rotating shaft a8 is fixed on the fixed frame 3 and is matched with a groove in the middle length direction of the holding claw 6, the motion track of the holding claw 6 is further restrained, and the holding claw 6 can contract, expand, pull, close and push away.
When the space capturing and butting mechanism b is pulled to a certain distance by the holding claw 6 of the space capturing and butting mechanism a, the electric connector a1 is inserted into the electric connector b24, the liquid circuit breaker a4 is inserted into the liquid circuit breaker b27, and the positioning pin 5 is inserted into the positioning hole on the passive end base 26. Finally, the space capturing butt-joint mechanism b is pulled to be attached to the upper surface of the fixed frame 3 by the holding claw 6, and butt-joint mechanical locking is achieved.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A space capturing docking mechanism is characterized by comprising a docking mechanism a and a docking mechanism B, wherein peripheral equipment comprises a spacecraft A and a spacecraft B, the spacecraft A is a space service platform, and the spacecraft B is a spacecraft;
docking mechanism a includes: the device comprises an electric connector a (1), a cylinder body (2), a fixed frame (3), a liquid circuit breaker a (4), a positioning pin (5), a holding claw (6), a driving end guide vane (7), a holding claw rotating shaft a (8), a holding claw rotating shaft b (9), a ball screw nut (10), a ball screw (11), a bearing end cover (12), a bearing a (13), a bevel gear a (14), a bevel gear b (15), a transmission shaft (16), a bevel gear (17), a key (18), a motor reducer (19), a bevel gear ring (20), a motor (21), a bearing b (22) and a bevel gear ring support rod (23);
the docking mechanism b includes: comprises an electric connector b (24), a passive end mounting base plate (25), a passive end base (26), a liquid circuit breaker b (27) and a passive end guide flap (28);
the butt joint mechanism a is provided with 4 fixed frames (3) which are uniformly distributed around the cylinder body (2) at 90 degrees, the 4 fixed frames (3) are provided with an electric connector a (1) and a liquid circuit breaker a (4) in a staggered manner, one side of each fixed frame (3) close to the cylinder body (2) is provided with an installation interface, and the fixed frames (3) are fixedly connected on the cylinder body (2);
the electric connector a (1) and the liquid circuit breaker a (4) are provided with mounting interfaces, and the electric connector a (1) and the liquid circuit breaker a (4) are fixedly connected to the fixed frame (3) through screws; each fixed frame (3) is provided with a pair of active end guide flaps (7), the butt joint mechanism a is provided with 8 active end guide flaps (7) in total, and each pair of active end guide flaps (7) are symmetrical in structure and are symmetrically arranged on two sides of the holding claw (6) at the same time; the positioning pin (5) is used for carrying out precise positioning in the process of capturing and butting the active end and the passive end, and the bottom of the positioning pin is provided with a threaded hole and is arranged on the fixed frame (3) through a screw;
the transmission shaft (16) is fixed on the fixed frame (3) through a pair of bearings a (13), a key groove is formed in the transmission shaft (16), and the bevel gear (17) and the transmission shaft (16) synchronously rotate through key matching; the ball screw (11) is fixed on the fixed frame (3) through bearings at two ends, wherein the bearing at the upper end of the ball screw (11) is fixed on the fixed frame (3) through a bearing end cover (12), and a bearing a (13) at the lower end is clamped in a bearing groove by a structure at the lower end of the fixed frame (3), so that the ball screw (11) rotates along the axial direction of the ball screw;
the bevel gear a (14) is fixed on the transmission shaft (16) through a key (18) and a sleeve, so that the bevel gear a (14) only rotates synchronously along the axial direction of the transmission shaft (16) without relative slippage; the middle of the bevel gear b (15) is provided with a through hole which is fixedly connected with a threaded hole at the bottom end of the ball screw (11) through a screw, so that the bevel gear b (15) and the ball screw (11) rotate coaxially; the included angle between the central axes of the bevel gear a (14) and the bevel gear b (15) is 90 degrees, and the transmission steering function of the bevel gear a (14) and the bevel gear b (15) is realized through the matching angle;
the ball screw nut (10) moves up and down along with the rotation of the ball screw (11), a hole groove is formed in the ball screw nut (10), the claw holding rotating shaft b (9) is inserted into the hole groove, and the claw holding rotating shaft b (9) is fixed on the ball screw nut (10) through a pin; the claw-holding rotating shaft a (8) is fixed in a corresponding hole of the fixed frame (3);
the upper end of the holding claw (6) is a cuboid, the middle part of the holding claw is of a cuboid structure vertical to the cuboid at the upper end, and the lower half part of the holding claw is a cuboid which forms a certain angle with the cuboid at the middle part; the middle positions of the middle part and the lower half part of the holding claw (6) in the length direction are provided with long grooves parallel to the length direction and used for being matched with a holding claw rotating shaft a (8) to restrain the motion track of the holding claw (6); a round hole is formed in the middle of the lower half part of the holding claw (6) in the length direction, is sleeved on the holding claw rotating shaft b (9) and is used for being matched with the holding claw rotating shaft b (9) to drive the holding claw (6) to move up and down through a ball screw nut (10);
the cylinder body (2) is cylindrical and is provided with 4 mounting interfaces of a fixed frame (3), a bevel gear ring support rod (23) and a motor reducer (19), and meanwhile, the bottom of the cylinder body (2) is provided with a mounting interface fixed on an aircraft A; the outer side of the lower half part of the cylinder body (2) is provided with 4 symmetrically distributed holes for avoiding the transmission shaft (16) and avoiding interference; 4 mounting surfaces are arranged in the lower half part of the cylinder body (2), wherein one mounting surface is used for mounting a motor reducer (19), and the other three mounting surfaces are used for mounting and fixing a transmission shaft (16) and a bevel gear (17);
the front end face and the rear end face of the motor reducer (19) are respectively provided with a mounting hole, the rear end face and a hole corresponding to the motor (21) are fixed together by using screws to form an integral motor (21) -reducer structure, and the mounting hole of the front end face is connected with a corresponding mounting surface in the barrel body (2) so that the motor reducer (19) structure is fixed in the barrel body (2); an output shaft is arranged at the front end of the motor reducer (19), the output shaft is connected with the bevel gear (17) through key matching, and when the motor (21) rotates, the motor reducer (19) can drive the bevel gear (17) to rotate;
the bevel gear ring support rod (23) is provided with a mounting hole, the bevel gear ring support rod is fixed in the cylinder body (2) through the mounting hole, a bearing b (22) is sleeved on the bevel gear ring support rod, gaskets are arranged at two ends of the bearing b (22), so that the position of the bearing b (22) is fixed, and the bearing b (22) can only rotate along the axial direction of the bearing b; a groove is formed in the bevel gear ring (20), and a bearing b (22) is embedded in the groove to support the bevel gear ring (20) so that the bevel gear ring (20) rotates along the central axis of the bevel gear ring;
the passive end mounting base plate (25) is provided with a mounting hole and fixedly connected with the aircraft B; the passive end base (26) is provided with mounting holes which are fixedly connected with a passive end mounting base plate (25), an electric connector b (24), a liquid circuit breaker b (27) and a passive end guide flap (28) respectively, and the passive end base (26) is provided with positioning holes which are used for being matched with positioning pins (5) on the butt joint mechanism a to realize the precise positioning of the butt joint process.
2. A space capture docking mechanism as claimed in claim 1 wherein the connection between the clasps (6) and the passive end mounting plate (25) provides a clamp-lock of the mechanism.
3. A space capture docking mechanism as claimed in claim 1 wherein the alignment pins (5) are connected to the passive end mounting plate (25) to provide precise alignment of the docking process.
4. The space capture docking mechanism according to claim 1, wherein the electrical connector a (1) and the fluid circuit breaker a (4) are respectively connected with the electrical connector b (24) and the fluid circuit breaker b (27), so as to connect the electrical circuit with the fluid circuit during the docking process.
5. A space capturing docking mechanism according to claim 1, characterized by the active end guide flap (7) and the passive end guide flap (28) cooperating to achieve coarse positioning during the capturing docking of the structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911374214.4A CN111071494A (en) | 2019-12-27 | 2019-12-27 | Space capturing butt joint mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911374214.4A CN111071494A (en) | 2019-12-27 | 2019-12-27 | Space capturing butt joint mechanism |
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| CN111071494A true CN111071494A (en) | 2020-04-28 |
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| CN201911374214.4A Pending CN111071494A (en) | 2019-12-27 | 2019-12-27 | Space capturing butt joint mechanism |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112141368A (en) * | 2020-09-04 | 2020-12-29 | 中国空间技术研究院 | Electric screw locking mechanism |
| CN112389686A (en) * | 2020-11-24 | 2021-02-23 | 西北工业大学深圳研究院 | Passive target synchronous despun capture operation method based on space multi-arm contact |
| CN112429251A (en) * | 2020-12-11 | 2021-03-02 | 西安电子科技大学 | Small aerial array docking and separating mechanism and method meeting electrical connection |
| CN113401371A (en) * | 2021-06-11 | 2021-09-17 | 上海宇航系统工程研究所 | Ultra-light multifunctional space module connecting mechanism and application method |
| CN114104343A (en) * | 2021-12-28 | 2022-03-01 | 中国科学院长春光学精密机械与物理研究所 | Butt joint locking mechanism for space optical load |
| CN114379822A (en) * | 2022-03-22 | 2022-04-22 | 中国人民解放军战略支援部队航天工程大学 | Circumferential and axial double-locking mechanism for multi-body allosteric satellite |
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| CN112141368A (en) * | 2020-09-04 | 2020-12-29 | 中国空间技术研究院 | Electric screw locking mechanism |
| CN112389686A (en) * | 2020-11-24 | 2021-02-23 | 西北工业大学深圳研究院 | Passive target synchronous despun capture operation method based on space multi-arm contact |
| CN112389686B (en) * | 2020-11-24 | 2022-06-07 | 西北工业大学深圳研究院 | Passive target synchronous despun capture operation method based on space multi-arm contact |
| CN112429251A (en) * | 2020-12-11 | 2021-03-02 | 西安电子科技大学 | Small aerial array docking and separating mechanism and method meeting electrical connection |
| CN113401371A (en) * | 2021-06-11 | 2021-09-17 | 上海宇航系统工程研究所 | Ultra-light multifunctional space module connecting mechanism and application method |
| CN113401371B (en) * | 2021-06-11 | 2022-11-11 | 上海宇航系统工程研究所 | Ultra-light multifunctional space module connecting mechanism and application method |
| CN114104343A (en) * | 2021-12-28 | 2022-03-01 | 中国科学院长春光学精密机械与物理研究所 | Butt joint locking mechanism for space optical load |
| CN114104343B (en) * | 2021-12-28 | 2023-12-15 | 中国科学院长春光学精密机械与物理研究所 | Butt-joint locking mechanism for space optical load |
| CN114379822A (en) * | 2022-03-22 | 2022-04-22 | 中国人民解放军战略支援部队航天工程大学 | Circumferential and axial double-locking mechanism for multi-body allosteric satellite |
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Application publication date: 20200428 |