CN105000199A - Small butt locking device for space - Google Patents
Small butt locking device for space Download PDFInfo
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- CN105000199A CN105000199A CN201510424610.9A CN201510424610A CN105000199A CN 105000199 A CN105000199 A CN 105000199A CN 201510424610 A CN201510424610 A CN 201510424610A CN 105000199 A CN105000199 A CN 105000199A
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Abstract
The invention provides a small butt locking device for a space. The small butt locking device comprises a diving mechanism installed on a space station and a shell installed on a space test load. The diving mechanism comprises a fame, a positioning pin installation plate A, a coarse positioning pin A, a fine positioning pin A, a face detection switch A, a heating device, a motor, a temperature sensor, a speed reducer, a positioning pin installation plate B, a speed reducer support, a coarse positioning pin B, a face detection switch B, a fine positioning pin B, a potentiometer, a coupling, a potentiometer support, a pinion, a sliding guide bush, an optical axis, a bull gear, a screw, a fine positioning pin C, a face detection switch C, a positioning pin installation plate C, a locking detection switch, a drive rack, an unlocking detection switch, a switch installation plate, a face detection switch D, a locking pin A, a locking pin B, a floating connector socket and a nut. The small butt locking mechanism for the space is miniature and lightweight, and an astronaut does not need to participate in operation.
Description
Technical field
The invention belongs to docking technique field, space, particularly relate to the small-sized butt-joint locking device in a kind of space.
Background technology
The large-scale docking structure of Space Docking Mechanism mainly between two spacecrafts or between large-scale loading device and space station applied in-orbit at present, machine can be realized, electricity, heat, the resource transmission such as fluid, in Chinese Space station is tested out of my cabin, carry out the middle-size and small-size test load tested out of my cabin and account for the over half of test load total amount out of my cabin, it is large that existing docking mechanism has volume, the feature that quality is heavy, especially large-scale loading device docks with space station, the astronaut's deliver from vault that needs participates in more, cannot be applied directly to China out of my cabin load to dock with space station and in resource transmission.
The small-sized butt joint locking mechanism in space is used for docking of space station and middle-size and small-size load out of my cabin, space station and test load " bridge ", station, implementation space resource is to the transmission of test load, the miniaturization of Space Docking Mechanism, lightweight are carried out, docking operation participates in docking by mechanical arm, and mechanism's displacement realizes locking, operates without the need to astronaut's deliver from vault, save deliver from vault resource, reduce application cost.Also there is no the small-sized butt joint locking mechanism in the space of middle-size and small-size test load at present.
Summary of the invention
For solving the problem, the invention provides the small-sized butt-joint locking device in a kind of space, devise miniaturization, lightweight, without the need to the small-sized butt joint locking mechanism in the space of astronaut's Attended Operation.
The small-sized butt-joint locking device in space of the present invention, it comprises: be arranged on driving mechanism and the housing be arranged in space test load on space station;
Driving mechanism comprises: framework, locating dowel pin adapter plate A, coarse positioning pin A, fine positioning pin A, face detector switch A, heating arrangement, motor, temperature sensor, reductor, locating dowel pin adapter plate B, reductor support, coarse positioning pin B, face detector switch B, fine positioning pin B, potentiometer, coupler, potentiometer support, miniature gears, sliding guide sleeve, optical axis, big gear wheel, leading screw, fine positioning pin C, face detector switch C, locating dowel pin adapter plate C, locking detector switch, drive chassis, separate lock detection switch, switch installation board, face detector switch D, locking pin A, locking pin B, float connector socket, nut,
Annexation is:
Locating dowel pin adapter plate A, locating dowel pin adapter plate B, locating dowel pin adapter plate C, switch installation board are all installed in framework; Wherein, coarse positioning pin A, fine positioning pin A, face detector switch A are installed on locating dowel pin adapter plate A; Coarse positioning pin B, face detector switch B, fine positioning pin B are installed on locating dowel pin adapter plate B; Fine positioning pin C, face detector switch C are installed on locating dowel pin adapter plate C; Face detector switch D is installed on switch installation board;
The output shaft of motor is connected with the input shaft of reductor, and the output shaft of reductor is connected with coupler, and coupler is connected with leading screw, leading screw and nut screw connection form sliding spiral pair, miniature gears is installed on leading screw end, and miniature gears engages with big gear wheel, and big gear wheel is installed on potentiometer output shaft; Reductor is installed on reductor support, and potentiometer is installed on potentiometer support, and reductor support and potentiometer support are installed in framework; Temperature sensor, heating arrangement are installed on motor; Drive chassis and framework bearing fit, float connector socket, locking pin A, locking pin B, nut, sliding guide sleeve are arranged in drive chassis, and optical axis is fixed on framework, and sliding guide sleeve coordinates with optical axis and forms sliding pair;
Housing is provided with the locking hole coordinated with locking pin A, locking pin B, the taper hole coordinated with coarse positioning pin, the cylindrical hole coordinated with fine positioning pin and float connector plug;
Float connector socket and float connector plug engagement fit.
Further, coarse positioning pin A, fine positioning pin A are located along the same line; The central axis coaxial of coarse positioning pin B, fine positioning pin B; Fine positioning pin B, fine positioning pin C are located along the same line.
Further, coarse positioning pin A, coarse positioning pin B, fine positioning pin A, fine positioning pin B, fine positioning pin C are located along the same line.
Further, locking pin A, locking pin B are coaxial.
Beneficial effect:
(1) the large-scale docking mechanism size of current large-scale load is at 1.2m × more than 1.2m, quality is substantially at more than 100kg, transporting something containerized of the present invention is moved and control is integrated, integrated design has been carried out to crucial parts, external envelope size 0.4m × 0.4m, A end and passive part quality 10kg altogether, solve the lightweight of docking mechanism, miniaturization issues;
(2) heat when motor, reductor being carried out to temperature monitoring and select, can work in space wide temperature range-100 DEG C ~+100 DEG C, space environment comformability is good; The cylindrical hole that passive part coordinates with A end fine positioning pin is " a word hole ", during active and passive part operation on orbit, can adapt to the thermal deformation that space high/low temperature alternation causes;
(3) utilize the self-locking of leading screw to realize locking, without the need to special catch gear, simplify mechanism's composition, improve mechanism reliability; Each step of docking, locking process has method of inspection, with the midway location of potentiometer testing agency motion in locking process; Such docking operation participates in docking by mechanical arm, and mechanism's displacement realizes locking, without the need to the operation of astronaut's deliver from vault, has saved deliver from vault resource, has reduced application cost, and had repeatedly used advantage.
Accompanying drawing explanation
Fig. 1 is the composition birds-eye view of A end of the present invention;
Fig. 2 is the component part front view of A end of the present invention;
Fig. 3 is the composition birds-eye view of passive part of the present invention;
Fig. 4 is the A-A figure of passive part of the present invention.
Detailed description of the invention
The small-sized butt-joint locking device in space of the present invention, is applicable to the resource between space test load and space station, it is characterized in that, comprising: be arranged on driving mechanism and the driven member be arranged in space test load on space station; Passive part is housing 36;
As depicted in figs. 1 and 2, driving mechanism comprises: framework 1, locating dowel pin adapter plate A2, coarse positioning pin A3, fine positioning pin A4, face detector switch A5, heating arrangement 6, motor 7, temperature sensor 8, reductor 9, locating dowel pin adapter plate B10, reductor support 11, coarse positioning pin B12, face detector switch B13, fine positioning pin B14, potentiometer 15, coupler 16, potentiometer support 17, miniature gears 18, sliding guide sleeve 19, optical axis 20, big gear wheel 21, leading screw 22, fine positioning pin C23, face detector switch C24, locating dowel pin adapter plate C25, locking detector switch 26, drive chassis 27, separate lock detection switch 28, switch installation board 29, face detector switch D30, locking pin A31, locking pin B32, float connector socket 33, nut 34,
Wherein, locating dowel pin adapter plate A2, locating dowel pin adapter plate B10, locating dowel pin adapter plate C25, switch installation board 29, reductor support 11, potentiometer support 17 and optical axis 20 are installed in framework 1;
Coarse positioning pin A3, fine positioning pin A4, face detector switch A5 are installed on locating dowel pin adapter plate A2;
Coarse positioning pin B12, face detector switch B13, fine positioning pin B14 are installed on locating dowel pin adapter plate B10;
Fine positioning pin C23, face detector switch C24 are installed on locating dowel pin adapter plate C25;
Face detector switch D30 is installed on switch installation board 29;
Temperature sensor 8, heating arrangement 6 are installed on motor 7, and motor 7 is installed on reductor 9, and reductor 9 is installed on reductor support 11;
Potentiometer 15 is installed on potentiometer support 17; Big gear wheel 21 is installed on potentiometer 15 output shaft, and miniature gears 18 is installed on leading screw 22 end, and big gear wheel 21 engages with miniature gears 18;
Drive chassis 27 and framework 1 bearing fit; Locking pin A31, locking pin B32, float connector socket 33, locking pin A31, locking pin B32, nut 34, sliding guide sleeve 19 are arranged in drive chassis 27, leading screw 22 is connected with reductor 9 by coupler 16, nut 34 coordinates with leading screw 22 and forms sliding spiral pair, and sliding guide sleeve 19 coordinates with optical axis 20 and forms sliding pair;
As shown in Figure 3 and Figure 4, housing 36 is provided with the locking hole coordinated with locking pin A31, locking pin B32, the taper hole coordinated with coarse positioning pin, the cylindrical hole coordinated with fine positioning pin, and float connector plug 37;
Float connector socket 33 and float connector plug 37 engagement fit.
Effect is good, and the upper surface of locating dowel pin adapter plate A2, locating dowel pin adapter plate B10, locating dowel pin adapter plate C25 and switch installation board 29 is at same plane.
Effect is good, the central axis coaxial of coarse positioning pin A3, fine positioning pin A4; The central axis coaxial of coarse positioning pin B12, fine positioning pin B13; The central axis coaxial of fine positioning pin B14, fine positioning pin C23.
Effect is good, and locking pin A31, locking pin B32 are coaxial.
The present invention is work like this: A end is arranged on space station, resource transmission one-way passage is formed with space station, and enter the orbit with space station transmitting, passive part is arranged on test load enters the orbit with freighter transmitting, be docked on A end by mechanical arm snatch test load and passive part in-orbit, then moved by A end internal mechanism, locking test load and passive part, float connector engagement simultaneously, completes the resource transmission of space station to test load.
In mechanical arm snatch test load and passive part docking operation, two taper holes of passive part housing 36 are introduced into the coarse positioning pin A3 of A end, in coarse positioning pin B12, by coarse positioning pin A3, coarse positioning pin B12 guide preliminary coarse positioning, again by the fine positioning pin A4 of drive end, fine positioning pin B14, three cylindrical holes of fine positioning pin C23 and passive part housing 36 guide fine positioning, until active end face detector switch A5, face detector switch B13, face detector switch C24, in the detector switch D30 of face, at least three are triggered, test load has docked, A end reports docking to complete instruction, mechanical arm stops action, rear A end motor 7 performs locking task, drive chassis 27 is moved, locking pin A31 in drive chassis 27, locking pin B32 enters the locking hole of passive part housing 36, float connector socket 33 enters float connector plug 37 simultaneously, until float connector socket 33 and float connector plug 37 measure loop are connected, the detector switch 26 of A end locking is simultaneously triggered, motor 7 stops action, station, implementation space is to the resource transmission path of test load, complete the locking to test load simultaneously.Now A end reports locking to complete instruction, and mechanical arm leaves.At the end of test load experimental duties, first by mechanical arm snatch test load, after snatch completes, A end motor 7 performs and unlocks load task, drive chassis 27 is moved, locking pin A31 in drive chassis 27, locking pin B32 exit the locking hole of passive part housing 36, float connector socket 33 is separated with float connector plug 37 simultaneously, be triggered until separate lock detection switch 28, motor 7 stops action, A end reports unblock to complete instruction, and mechanical arm snatch test load and passive part are left.
Certainly; the present invention also can have other various embodiments; when not deviating from the present invention's spirit and essence thereof; those of ordinary skill in the art are when making various corresponding change and distortion according to the present invention, but these change accordingly and are out of shape the protection domain that all should belong to the claim appended by the present invention.
Claims (4)
1. the small-sized butt-joint locking device in space, is characterized in that, comprising: be arranged on driving mechanism and the housing (36) be arranged in space test load on space station;
Driving mechanism comprises: framework (1), locating dowel pin adapter plate A (2), coarse positioning pin A (3), fine positioning pin A (4), face detector switch A (5), heating arrangement (6), motor (7), temperature sensor (8), reductor (9), locating dowel pin adapter plate B (10), reductor support (11), coarse positioning pin B (12), face detector switch B (13), fine positioning pin B (14), potentiometer (15), coupler (16), potentiometer support (17), miniature gears (18), sliding guide sleeve (19), optical axis (20), big gear wheel (21), leading screw (22), fine positioning pin C (23), face detector switch C (24), locating dowel pin adapter plate C (25), locking detector switch (26), drive chassis (27), separate lock detection switch (28), switch installation board (29), face detector switch D (30), locking pin A (31), locking pin B (32), float connector socket (33), nut (34),
Annexation is:
Locating dowel pin adapter plate A (2), locating dowel pin adapter plate B (10), locating dowel pin adapter plate C (25), switch installation board (29) are all installed in framework (1); Wherein, coarse positioning pin A (3), fine positioning pin A (4), face detector switch A (5) are installed on locating dowel pin adapter plate A (2); Coarse positioning pin B (12), face detector switch B (13), fine positioning pin B (14) are installed on locating dowel pin adapter plate B (10); Fine positioning pin C (23), face detector switch C (24) are installed on locating dowel pin adapter plate C (25); Face detector switch D (30) is installed on switch installation board (29);
The output shaft of motor (7) is connected with the input shaft of reductor (9), the output shaft of reductor (9) is connected with coupler (16), coupler (16) is connected with leading screw (22), leading screw (22) coordinates with nut (34) and forms sliding spiral pair, miniature gears (18) is installed on leading screw (22) end, miniature gears (18) engages with big gear wheel (21), and big gear wheel (21) is installed on potentiometer (15) output shaft; Reductor (9) is installed on reductor support (11), potentiometer (15) is installed on potentiometer support (17), and reductor support (11) and potentiometer support (17) are installed in framework (1); Temperature sensor (8), heating arrangement (6) are installed on motor (7); Drive chassis (27) and framework (1) bearing fit, float connector socket (33), locking pin A (31), locking pin B (32), nut (34), sliding guide sleeve (19) are arranged in drive chassis (27), optical axis (20) is fixed on framework (1), and sliding guide sleeve (19) coordinates with optical axis (20) and forms sliding pair;
Housing (36) is provided with the locking hole coordinated with locking pin A (31), locking pin B (32), the taper hole coordinated with coarse positioning pin, the cylindrical hole coordinated with fine positioning pin and float connector plug (37);
Float connector socket (33) and float connector plug (37) engagement fit.
2. the small-sized butt joint locking mechanism in space according to claim 1, is characterized in that,
Coarse positioning pin A (3), fine positioning pin A (4) are located along the same line; The central axis coaxial of coarse positioning pin B (12), fine positioning pin B (13); Fine positioning pin B (14), fine positioning pin C (23) are located along the same line.
3. the small-sized butt joint locking mechanism in space according to claim 1, it is characterized in that, coarse positioning pin A (3), coarse positioning pin B (12), fine positioning pin A (4), fine positioning pin B (14), fine positioning pin C (23) are located along the same line.
4. the small-sized butt joint locking mechanism in space according to claim 1, is characterized in that, locking pin A (31), locking pin B (32) are coaxial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510424610.9A CN105000199B (en) | 2015-07-17 | 2015-07-17 | A kind of space is with small-sized butt-joint locking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510424610.9A CN105000199B (en) | 2015-07-17 | 2015-07-17 | A kind of space is with small-sized butt-joint locking device |
Publications (2)
| Publication Number | Publication Date |
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| CN105000199A true CN105000199A (en) | 2015-10-28 |
| CN105000199B CN105000199B (en) | 2016-11-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510424610.9A Active CN105000199B (en) | 2015-07-17 | 2015-07-17 | A kind of space is with small-sized butt-joint locking device |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106945852A (en) * | 2017-03-09 | 2017-07-14 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking and emergent unblock interface arrangement |
| CN107054699A (en) * | 2017-03-09 | 2017-08-18 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking interface arrangement |
| CN107416234A (en) * | 2017-03-09 | 2017-12-01 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking and locking instruction interface arrangement |
| CN107492749A (en) * | 2017-03-09 | 2017-12-19 | 兰州空间技术物理研究所 | Realize the space load butt-joint locking interface arrangement of emergent unblock and locking instruction |
| CN108216692A (en) * | 2018-01-16 | 2018-06-29 | 哈尔滨工业大学 | A kind of steel wire rope type noncooperative target retaining mechanism |
| CN110002009A (en) * | 2019-04-12 | 2019-07-12 | 北京控制工程研究所 | A kind of passive compliance component and in-orbit add interface arrangement |
| CN110884697A (en) * | 2019-12-12 | 2020-03-17 | 北京空间技术研制试验中心 | Extravehicular load interface supporting device |
| CN111114853A (en) * | 2019-12-24 | 2020-05-08 | 兰州空间技术物理研究所 | Docking and locking interface device capable of conducting heat actively for space aircraft |
| CN111169660A (en) * | 2019-12-12 | 2020-05-19 | 北京空间技术研制试验中心 | Exposed load support system for spacecraft |
| CN112591141A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Compressing and releasing device suitable for flexible spacecraft |
| CN113879570A (en) * | 2021-11-18 | 2022-01-04 | 中国科学院空间应用工程与技术中心 | Spacecraft active capturing device and docking device and method |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416234B (en) * | 2017-03-09 | 2019-12-13 | 兰州空间技术物理研究所 | load butt joint locking and locking indication interface device for space |
| CN107054699A (en) * | 2017-03-09 | 2017-08-18 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking interface arrangement |
| CN107416234A (en) * | 2017-03-09 | 2017-12-01 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking and locking instruction interface arrangement |
| CN107492749A (en) * | 2017-03-09 | 2017-12-19 | 兰州空间技术物理研究所 | Realize the space load butt-joint locking interface arrangement of emergent unblock and locking instruction |
| CN106945852A (en) * | 2017-03-09 | 2017-07-14 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking and emergent unblock interface arrangement |
| CN106945852B (en) * | 2017-03-09 | 2019-04-05 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking and unlock interface arrangement of meeting an urgent need |
| CN107054699B (en) * | 2017-03-09 | 2019-06-18 | 兰州空间技术物理研究所 | A kind of space load butt-joint locking interface arrangement |
| CN108216692A (en) * | 2018-01-16 | 2018-06-29 | 哈尔滨工业大学 | A kind of steel wire rope type noncooperative target retaining mechanism |
| CN110002009A (en) * | 2019-04-12 | 2019-07-12 | 北京控制工程研究所 | A kind of passive compliance component and in-orbit add interface arrangement |
| CN110884697A (en) * | 2019-12-12 | 2020-03-17 | 北京空间技术研制试验中心 | Extravehicular load interface supporting device |
| CN111169660A (en) * | 2019-12-12 | 2020-05-19 | 北京空间技术研制试验中心 | Exposed load support system for spacecraft |
| CN111114853A (en) * | 2019-12-24 | 2020-05-08 | 兰州空间技术物理研究所 | Docking and locking interface device capable of conducting heat actively for space aircraft |
| CN111114853B (en) * | 2019-12-24 | 2021-04-20 | 兰州空间技术物理研究所 | Docking and locking interface device capable of conducting heat actively for space aircraft |
| CN112591141A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Compressing and releasing device suitable for flexible spacecraft |
| CN113879570A (en) * | 2021-11-18 | 2022-01-04 | 中国科学院空间应用工程与技术中心 | Spacecraft active capturing device and docking device and method |
| CN113879570B (en) * | 2021-11-18 | 2022-04-19 | 中国科学院空间应用工程与技术中心 | Spacecraft active capturing device and docking device and method |
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| CN105000199B (en) | 2016-11-30 |
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