CN107826270A - A kind of multipoint clamping formula locks relieving mechanism - Google Patents
A kind of multipoint clamping formula locks relieving mechanism Download PDFInfo
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- CN107826270A CN107826270A CN201711221342.6A CN201711221342A CN107826270A CN 107826270 A CN107826270 A CN 107826270A CN 201711221342 A CN201711221342 A CN 201711221342A CN 107826270 A CN107826270 A CN 107826270A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 28
- 230000005540 biological transmission Effects 0.000 claims description 6
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 3
- 230000009471 action Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
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- 239000002360 explosive Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000008045 co-localization Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 230000000505 pernicious effect Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
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- 239000007787 solid Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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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
Abstract
The present invention relates to a kind of multipoint clamping formula to lock relieving mechanism, and the both sides of aircraft are equipped with aircraft release platform, and locking releasing device is mounted on per side aircraft release platform；Drive device, gear drive and trapezoidal thread device are separately mounted on bottom plate, and drive device is connected by gear drive with multiple output gears, and each output gear is separately mounted on a trapezoidal thread device；Aircraft is towards being equipped with identical with trapezoidal thread device quantity and one-to-one passive locking end on each side surface of locking releasing device；Each output gear is driven by gear drive by drive device to be rotated, and then corresponding passive locking end is locked or unlocked by each trapezoidal thread device.The present invention has the advantages of structure is novel, compact, control is flexible, the small and reliability of impact is high, the locking and release of the higher clamped body of positioning requirements suitable for clamping process, especially suitable for the fixation of aircraft in space environment, locking, release and capture.
Description
Technical field
The present invention relates to locking relieving mechanism, specifically a kind of multipoint clamping formula locking relieving mechanism.
Background technology
In recent years, with space resources deep development and survey of deep space mission requirements it is growing, often face
Rail discharges or clamping captures the task of the aircraft devices such as moonlet, detector.
In emission process, aircraft device needs to bear severe mechanical load spacecraft, it is necessary to which firmly locking prevents
Come off；Also, it can smoothly discharge aircraft in the position of mission requirements.Although China connects and divided in spacecraft in recent years
Research from field of mechanisms has been achieved for many achievements, but locks relieving mechanism for the low impact that carries greatly of in-orbit application
Progress is slow, and existing locking relieving mechanism impacts the problem of excessive during having release.
For in Traditional Space locking separation device pass through frequently with Fire load for, Fire load separation caused by
The posture and precision controlling of enormous impact aircraft release platform and aircraft generate adverse effect, and Fire load may be used also
Pernicious gas can be produced, the sensitive equipment of pollutant aircraft release platform and aircraft produces larger interference, and traditional
Fire load can only be disposable, it is impossible to repeats to test.
For new non-Fire load, such as hot knife, non-firer separate bolt, although solving traditional firer's dress
The problem of release impact is greatly with pollution is put, but the mission requirements of the clamping capture of aircraft device can not be met.
With the development of space technology, it is small, reliable that the locking relieving mechanism of in-orbit application is faced with quality small volume, impact
Property task object high and that clamping capture spacecraft can be realized, so being badly in need of a kind of multipoint clamping formula locking relieving mechanism.
The content of the invention
For above mentioned problem existing for existing locking relieving mechanism, it is an object of the invention to provide a kind of multipoint clamping formula
Lock relieving mechanism.The locking relieving mechanism that multipoint clamping formula locking relieving mechanism is cut based on hot knife, structure is novel, control
Simply, it is reliable and stable, suitable for being locked the adverse circumstances of space and discharging small aircraft.
The purpose of the present invention is achieved through the following technical solutions：
The present invention includes aircraft release platform, locking releasing device and passive locking end, wherein clamped locking flies
The both sides of row device are equipped with aircraft release platform, and the one side of aircraft release platform towards aircraft is mounted on described in per side
Structure identical locking releasing device；The locking releasing device includes bottom plate, drive device, gear drive, trapezoidal spiral shell
Line device and output gear, the drive device, gear drive and trapezoidal thread device are separately mounted on the bottom plate, institute
State drive device by gear drive with multiple output gears to be connected, each output gear is separately mounted to a ladder
On shape screw device；The aircraft, should towards multiple passive locking ends are equipped with each side surface of locking releasing device
Passive locking end is identical with the trapezoidal thread device quantity and corresponds；Each output gear passes through gear drive
Device is driven by drive device to be rotated, and then corresponding passive locking end is locked or solved by each trapezoidal thread device
Lock；
Wherein：The adjusting pad for being used for adjusting trapezoidal thread device height is provided between the trapezoidal thread device and bottom plate
Piece；
The trapezoidal thread device include locking end trapezoidal screw, trapezoidal thread device mounting seat, bearing, trapezoidal nut,
Bearing (ball) cover, axle sleeve and fixed flat key, the trapezoidal thread device mounting seat are arranged on the bottom plate, and the trapezoidal screw passes through
Bearing is rotatably installed in trapezoidal thread device mounting seat, and is provided with the trapezoidal thread device mounting seat to bearing axial direction
Fixed bearing (ball) cover；The axle sleeve is arranged on trapezoidal screw, and the output gear passes through fixed flat key and trapezoidal screw
One end key connection is simultaneously connected with the axle sleeve, and the inner of the locking end trapezoidal screw is formed with external screw thread, another with trapezoidal screw
Threaded one end connects, and the outer end of the locking end trapezoidal screw is the frustum in the passive locking end of insertion；The passive locking end
It is identical with the taper of the frustum for taper hole structure corresponding with frustum, the taper hole；The locking end trapezoidal screw and trapezoidal silk
The lead angle of box thread transmission is less than equivalent friction angle, realizes self-locking；
Each trapezoidal thread device corresponds to a guide rod, and one end of the guide rod covers on the output gear
Go up and be installed on bottom plate, the other end is passed through by output gear, trapezoidal screw；The locking end trapezoidal screw center side of being provided with
Shape hole, the other end of the guide rod is hollow square cavernous structure, is inserted by the square opening, the trapezoidal silk of locking end
Thick stick is moved along a straight line along the other end of guide rod；
The gear drive includes driving spur gear, bevel gear end bearing, bevel gear end bearing block, driving cone tooth
Wheel, drive gear mounting seat, driven wheel of differential and central drive gear, the central drive gear are rotatably installed on bottom plate, and
It is meshed with each output gear；The drive gear mounting seat is arranged on the bottom plate, the drive gear mounting seat
Two bevel gear end bearing blocks are provided with, driving bevel gear is rotatably installed in bevel gear end bearing block respectively with driven wheel of differential
Upper and intermeshing transmission, the driving bevel gear are connected with the output end of drive device, are connected with the driven wheel of differential
The driving spur gear being meshed with central drive gear；
The driving bevel gear is rotatablely connected by bevel gear end bearing and one of bevel gear end bearing block, in the drive
The locking nut and bevel gear end bearing back-up ring that axial restraint is carried out to the bevel gear end bearing are respectively equipped with dynamic bevel gear；
The driven wheel of differential is rotatablely connected by bevel gear end bearing and another bevel gear end bearing block, on the driven wheel of differential
It is respectively equipped with the locking nut and bevel gear end bearing back-up ring that axial restraint is carried out to the bevel gear end bearing；The driving is straight
Gear is fixedly mounted on driven wheel of differential；
The center of the driving bevel gear and driven wheel of differential is equipped with the interior hexagonal hole for manual actuation；
The bottom plate is provided with counting device, and the counting device includes encoder, encoder mounting seat and counting gear, institute
State encoder mounting seat to be fixed on bottom plate, encoder is connected with the encoder mounting seat, the counting gear, which is arranged on, to be compiled
On code device, and it is connected with the gear drive, drives counting gear to rotate by the gear drive, and then realize institute
State encoder to count.
Advantages of the present invention is with good effect：
1. the crucial drive mechanism of the present invention all collects aircraft release platform with being arranged on the bottom of aircraft release platform
It is compact-sized in space between plate, small volume, it is not easy to damage.
2. the present invention using multipoint clamping formula locking relieving mechanism, have it is safe and reliable, it is low impact, it is pollution-free, repeatable
The advantages of locking release.
3. the present invention, can using the trapezoidal thread transmission (lead angle is less than equivalent friction angle) that auto-lock function can be achieved
Realize that aircraft device is firmly locked in adverse circumstances.
4. locking end trapezoidal screw of the present invention uses taper fit with passive locking end, increase and coordinate redundancy range, avoid
Due to controlling error, cause to arrest unsuccessfully.
5. the present invention can motor operation control, manual mode of operation can also be switched to.
6. the present invention uses frustum cone structure using multipoint clamping formula locking pattern and locking end trapezoidal screw, can realize pair
Aircraft without passive locking end carries out arresting fixation, and the scope of application is wider.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of locking state of the present invention；
Fig. 2 is the dimensional structure diagram of present invention unblock release conditions completely；
Fig. 3 is the rear isometric view of first and second locking releasing device of the invention；
Fig. 4 is first and second locking releasing device main shaft side explosive view of the invention；
Fig. 5 is the explosive view of drive gear transmission device of the present invention；
Fig. 6 is the structural representation of trapezoidal thread device of the present invention；
Fig. 7 is the scheme of installation of guide rod of the present invention and trapezoidal screw；
Fig. 8 is drive gear actuator drives bevel gear of the present invention and driven wheel of differential manual actuation interface diagram；
Fig. 9 is locking end trapezoidal screw of the present invention and the matching relationship view of the passive locking end of aircraft；
Wherein：1 is aircraft release platform, and 2 be the first locking releasing device, and 3 be the second locking releasing device, and 4 be winged
Row device, 5 be passive locking end, and 6 be bottom plate, and 7 be drive device, and 8 be gear drive, and 9 be trapezoidal thread device, and 10 be to lead
To bar, 11 be output gear, and 12 be counting device, and 13 be adjust pad, and 14 be trapezoidal thread device fixing screws, and 15 be locking
Release device fixing screws, 16 be locking end trapezoidal screw, and 17 be trapezoidal thread device mounting seat, and 18 be bearing, and 19 be trapezoidal
Screw, 20 be bearing (ball) cover, and 21 be bearing (ball) cover fixing screws, and 22 be output gear fixing screws, and 23 be axle sleeve holding screw,
24 be axle sleeve, and 25 be fixed flat key, and 26 be driving spur gear, and 27 be locking nut, and 28 be bevel gear end bearing back-up ring, and 29 be cone
Gear end bearing, 30 be bevel gear end bearing block, and 31 be driven wheel of differential, and 32 be drive gear mounting seat, and 33 be driving cone tooth
Take turns, travelling gear centered on 34,35 be square opening, and 36 be interior hexagonal hole.
Embodiment
The invention will be further described below in conjunction with the accompanying drawings.
As shown in figures 1-4, the present invention includes aircraft release platform 1, locking releasing device and passive locking end, wherein
The both sides of the aircraft 4 of clamped locking are equipped with aircraft release platform 1, per side aircraft release platform 1 towards aircraft 4
One side be mounted on locking releasing device, i.e. the first locking releasing device 2 and the second locking releasing device 3.
First locking releasing device 2 is identical with the structure of the second locking releasing device 3, mirror image is set, and including bottom plate 6, drives
Dynamic device 7, gear drive 8, trapezoidal thread device 9, guide rod 10, output gear 11 and counting device 12, the bottom plate 6 are logical
Cross locking releasing device fixing screws 15 to be fixed on aircraft release platform 1, drive device 7, gear drive 8 and counting
Device 12 is separately mounted on bottom plate 6, and trapezoidal thread device 9 is fixed on bottom plate 6 by trapezoidal thread device fixing screws 14,
The adjust pad 13 for being used for adjusting the height of trapezoidal thread device 9 is provided between trapezoidal thread device 9 and bottom plate 6.Output gear
11 be multiple, and the corresponding trapezoidal thread device 9 of each output gear 11 is simultaneously arranged on corresponding trapezoidal thread device,
Drive device 7 is connected by gear drive 8 with each output gear 11.The trapezoidal thread device 9 of the present embodiment is four, is in
Central Symmetry is distributed, with the co-localization of counting device 12 around gear drive 8；Accordingly, output gear 11 is also
Four.Aircraft 4 is towards being equipped with multiple passive locking ends 5, the passive locking end 5 on each side surface of locking releasing device
And one-to-one corresponding identical with the quantity of trapezoidal thread device 9 in homonymy locking releasing device；Each output gear 11 passes through gear
Transmission device 8 drives rotation by drive device 7, and then corresponding passive locking end 5 is locked by each trapezoidal thread device 9
Or unblock.
As shown in Fig. 3, Fig. 5, gear drive 8 includes driving spur gear 26, locking nut 27, bevel gear end bearing gear
Circle 28, bevel gear end bearing 29, bevel gear end bearing block 30, driving bevel gear 33, drive gear mounting seat 32, driven wheel of differential
31 and central drive gear 34, central drive gear 34 be rotatably installed on bottom plate 6, and be meshed with each output gear 11；Drive
Moving gear mounting seat 32 is by the way that on bottom plate 6, drive gear mounting seat 32 is provided with two bevel gear end bearing blocks 30, often
Bevel gear end bearing 29 is equipped with individual bevel gear end bearing block 30.Driven wheel of differential 31 and one of bevel gear end bearing block
Bevel gear end bearing 29 in 30 is rotatablely connected, and driving spur gear 26 is fixedly mounted on driven wheel of differential 31, and and center
Travelling gear 4 is meshed；The locking that axial restraint is carried out to bevel gear end bearing 29 is respectively and fixedly connected with driven wheel of differential 31
Nut 27 and bevel gear end bearing back-up ring 28.Driving bevel gear 33 and the bevel gear end axle in another bevel gear end bearing block 30
Hold 29 rotation connections and be meshed with driven wheel of differential 31, has been respectively and fixedly connected with driving bevel gear 33 to bevel gear end bearing
29 carry out the locking nut 27 and bevel gear end bearing back-up ring 28 of axial restraint.The output of driving bevel gear 33 and drive device 7
End is connected.As shown in figure 8, the center of driving bevel gear 33 and driven wheel of differential 31 is equipped with the interior hexagonal hole for manual actuation
36。
As shown in Fig. 6, Fig. 7 and Fig. 9, trapezoidal thread device 6 includes locking end trapezoidal screw 16, trapezoidal thread device is installed
Seat 17, bearing 18, trapezoidal screw 19, bearing (ball) cover 20, axle sleeve 24 and fixed flat key 25, trapezoidal thread device mounting seat 17 are fixed
On bottom plate 6, adjust pad 13 is located between the trapezoidal thread device mounting seat 17 and bottom plate 6；Trapezoidal screw 19 passes through
Bearing 18 is rotatablely connected with trapezoidal thread device mounting seat 17, and bearing (ball) cover 20 is fixedly mounted by bearing (ball) cover fixing screws 21
In trapezoidal thread device mounting seat 17, and realize the axial restraint to bearing 18.Axle sleeve 24 is solid by axle sleeve holding screw 23
On trapezoidal screw 19, output gear 11 is circumferentially fixed in one end of trapezoidal screw 19 and position by fixed flat key 25 for Dingan County
It is fixedly mounted in the side of bottom plate 6, and by output gear fixing screws 22 on axle sleeve 24；Fixed flat key 25 is located at axle sleeve 24
The outside of outer face, locking end trapezoidal screw 16 are arranged in the trapezoidal other end of screw 19, positioned at bottom plate 3 by worm drive
Opposite side.The inner of locking end trapezoidal screw 16 is formed with external screw thread, is threadedly coupled with trapezoidal screw 19, the locking end trapezoidal screw
16 outer end is the frustum 23 in the passive locking end 5 of insertion.Passive locking end 5 is taper hole structure corresponding with frustum 23, should
Taper hole is identical with the taper of frustum 23, the good fit when frustum 23 inserts taper hole.Locking end trapezoidal screw 16 and trapezoidal screw
19 screw-driven meets condition of self-locking, i.e. lead angle is less than equivalent friction angle.
Each trapezoidal thread device 9 corresponds to a guide rod 10, as shown in fig. 7, one end of the guide rod 10 covers on pair
On the output gear 11 answered and it is installed on bottom plate 6, the other end is hollow square cavernous structure.Locking end trapezoidal screw 16
Center be provided with square opening 35, the other end of guide rod 10 is passed through by output gear 11, trapezoidal screw 19 and inserts locking end ladder
In square opening 35 on shape leading screw 16, the other end of the locking end trapezoidal screw 16 along guide rod 10 is moved along a straight line.
Bottom plate 6 is provided with counting device 12, and the counting device 12 includes encoder, encoder mounting seat and counting gear,
Encoder mounting seat is fixed on bottom plate 6 by encoder mounting seat fixing screws, and encoder is pacified by encoder fixing screws
In encoder mounting seat, counting gear is installed on the encoder, and is meshed with central drive gear 34, is passed by center
Moving gear 34 drives counting gear rotation, and then realizes encoder to count.
The present invention operation principle be：
Motor running mode：Drive device 7 in first locking releasing device 2 drives driving bevel gear 33 to turn round, so as to
Driven wheel of differential 31 and driving spur gear 26 is driven to turn round, driving spur gear 26 drives central drive gear 34 to turn round, due to defeated
Go out gear 11 and counting gear 5 is installed in around central drive gear 34 and is meshed with central drive gear 34, therefore in
Output gear 11 and counting gear revolution around the revolution meeting synchronous drive of heart travelling gear 34；Due to output gear 11 and ladder
Trapezoidal screw 19 in shape screw device 9 is fixed, therefore trapezoidal screw 19 can be driven to turn round, so as to the meeting of locking end trapezoidal screw 16
Inwardly or outwardly slided along guide rod 10, insert in the taper hole of passive locking end 5 or removed from taper hole, realize locking or
The action of unblock；Because output gear 11 and counting gear are synchronous revolvings, counting gear is connected with encoder, therefore can control
The sliding distance of locking end trapezoidal screw 16 processed.Passive locking is inserted by adjust pad 13 or adjustment locking end trapezoidal screw 16
Distance in the taper hole at end 5.Similarly, the locking in the second locking releasing device 3 set with the mirror image of the first locking releasing device 2
End trapezoidal screw 16 equally outwardly or inwardly slides along guide rod 10, is unlocked or locking action.When the first locking release
The locking end trapezoidal screw 16 of the locking releasing device 3 of device 2 and second is bonded with being arranged on passive locking end 5 on aircraft 4
And after being loaded into expected coupling mechanism force, locking function is completed, otherwise complete unlocking function.
Manual mode of operation：By spanner insert driving bevel gear 33 or the gear centre of driven wheel of differential 31 it is reserved in six
In square hole 36, mechanism operation is switched into manual mode.
The present invention is to copy action and the function of human body carry an object, and the object clamped to needs is clamped according to instruction
With the automatic pilot of release, clamping capture operation can be carried out to aircraft under space environment.Structure of the present invention is novel,
Control is flexible, and the higher clamped body of positioning requirements clamps and releases suitable for clamping process, especially suitable for spatial loop
The capture clamping of aircraft under border.
Claims (10)
1. a kind of multipoint clamping formula locks relieving mechanism, it is characterised in that：Including aircraft release platform (1), locking release dress
Put and passive locking end, wherein the both sides of the aircraft (4) of clamped locking are equipped with aircraft release platform (1), per side institute
The one side for stating aircraft release platform (1) towards aircraft (4) is mounted on structure identical locking releasing device；The locking
Release device includes bottom plate (6), drive device (7), gear drive (8), trapezoidal thread device (9) and output gear
(11), the drive device (7), gear drive (8) and trapezoidal thread device (9) are separately mounted on the bottom plate (6), institute
State drive device (7) by gear drive (8) with multiple output gears (11) to be connected, each output gear (11) point
An Zhuan not be on a trapezoidal thread device (9)；The aircraft (4) is towards being all provided with each side surface of locking releasing device
There are multiple passive locking ends (5), the passive locking end (5) is identical with trapezoidal thread device (9) quantity and corresponds；
Each output gear (11) is driven by gear drive (8) by drive device (7) to rotate, and then passes through each ladder
Shape screw device (9) is locked by corresponding passive locking end (5) or unblock.
2. multipoint clamping formula according to claim 1 locks relieving mechanism, it is characterised in that：The trapezoidal thread device
(9) adjust pad (13) for being used for adjusting trapezoidal thread device (9) height is provided between bottom plate (6).
3. multipoint clamping formula according to claim 1 or 2 locks relieving mechanism, it is characterised in that：The trapezoidal thread dress
Putting (9) includes locking end trapezoidal screw (16), trapezoidal thread device mounting seat (17), bearing (18), trapezoidal nut (19), bearing
End cap (20), axle sleeve (24) and fixed flat key (25), the trapezoidal thread device mounting seat (17) are arranged on the bottom plate (6),
The trapezoidal screw (19) is rotatably installed in trapezoidal thread device mounting seat (17) by bearing (18), and in the trapezoidal spiral shell
Line device mounting seat (17) is provided with the bearing (ball) cover (20) to bearing (18) axial restraint；The axle sleeve (24) is arranged on trapezoidal
On screw (19), the output gear (5) by one end key connection of fixed flat key (25) and trapezoidal screw (19) and with it is described
Axle sleeve (24) is connected, and the inner of the locking end trapezoidal screw (16) is formed with external screw thread, the other end spiral shell with trapezoidal screw (19)
Line connects, and the outer end of the locking end trapezoidal screw (16) is the frustum (23) in the passive locking end (5) of insertion.
4. multipoint clamping formula according to claim 3 locks relieving mechanism, it is characterised in that：The passive locking end (5)
It is identical with the taper of the frustum (23) for taper hole structure corresponding with frustum (23), the taper hole.
5. multipoint clamping formula according to claim 3 locks relieving mechanism, it is characterised in that：The locking end trapezoidal screw
(16) lead angle with trapezoidal screw (19) screw-driven is less than equivalent friction angle, realizes self-locking.
6. multipoint clamping formula according to claim 3 locks relieving mechanism, it is characterised in that：Each trapezoidal thread dress
Put (9) and correspond to a guide rod (10), one end of the guide rod (10) covers on the output gear (11) and is installed on bottom
On plate (6), the other end is passed through by output gear (11), trapezoidal screw (19)；Locking end trapezoidal screw (16) center is provided with
Square opening (35), the other end of the guide rod (10) is hollow square cavernous structure, is inserted by the square opening (35), institute
The other end of the locking end trapezoidal screw (16) along guide rod (10) is stated to be moved along a straight line.
7. multipoint clamping formula according to claim 1 locks relieving mechanism, it is characterised in that：The gear drive
(8) driving spur gear (26), bevel gear end bearing (29), bevel gear end bearing block (30), driving bevel gear (33), driving are included
Gear installation base (32), driven wheel of differential (31) and central drive gear (34), the central drive gear (34) are rotatably installed in
On bottom plate (6), and it is meshed with each output gear (11)；The drive gear mounting seat (32) is arranged on the bottom plate
(6) on, the drive gear mounting seat (32) is provided with two bevel gear end bearing blocks (30), driving bevel gear (33) with it is driven
Bevel gear (31) is rotatably installed on bevel gear end bearing block (30) and is intermeshed transmission, the driving bevel gear respectively
(33) output end with drive device (7) is connected, and is connected with the driven wheel of differential (31) and central drive gear (34) phase
The driving spur gear (26) of engagement.
8. multipoint clamping formula according to claim 7 locks relieving mechanism, it is characterised in that：The driving bevel gear (33)
It is rotatablely connected by bevel gear end bearing (29) and one of bevel gear end bearing block (30), in the driving bevel gear (33)
It is respectively equipped with the locking nut (27) and bevel gear end bearing back-up ring that axial restraint is carried out to the bevel gear end bearing (29)
(28)；The driven wheel of differential (31) is rotated by bevel gear end bearing (29) and another bevel gear end bearing block (30) to be connected
Connect, the locking nut that axial restraint is carried out to the bevel gear end bearing (29) is respectively equipped with the driven wheel of differential (31)
And bevel gear end bearing back-up ring (28) (27)；The driving spur gear (26) is fixedly mounted on driven wheel of differential (31).
9. multipoint clamping formula according to claim 1 locks relieving mechanism, it is characterised in that：The driving bevel gear (33)
And the center of driven wheel of differential (31) is equipped with the interior hexagonal hole (36) for manual actuation.
10. multipoint clamping formula according to claim 1 locks relieving mechanism, it is characterised in that：The bottom plate (6) is provided with
Counting device (12), the counting device (8) include encoder, encoder mounting seat and counting gear, the encoder mounting seat
It is fixed on bottom plate (6), encoder is connected with the encoder mounting seat, the counting gear is installed on the encoder, and with
The gear drive (8) is connected, and drives counting gear to rotate by the gear drive (8), and then realize the volume
Code device counts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711221342.6A CN107826270B (en) | 2017-11-29 | 2017-11-29 | Multi-point clamping type locking and releasing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711221342.6A CN107826270B (en) | 2017-11-29 | 2017-11-29 | Multi-point clamping type locking and releasing mechanism |
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| Publication Number | Publication Date |
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| CN107826270A true CN107826270A (en) | 2018-03-23 |
| CN107826270B CN107826270B (en) | 2024-01-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711221342.6A Active CN107826270B (en) | 2017-11-29 | 2017-11-29 | Multi-point clamping type locking and releasing mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515771A (en) * | 2018-12-27 | 2019-03-26 | 中国科学院沈阳自动化研究所 | A kind of micro- interference relieving mechanism in space and its locking, micro- interference method for releasing |
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| US20130249229A1 (en) * | 2012-03-19 | 2013-09-26 | Macdonald Dettwiler & Associates Inc. | Spacecraft capture mechanism |
| CN203453408U (en) * | 2013-05-27 | 2014-02-26 | 成都福誉科技有限公司 | Self-locking elevating adjusting device with precision |
| US20150314893A1 (en) * | 2014-05-02 | 2015-11-05 | Macdonald Dettwiler & Associates Inc. | Spacecraft capture mechanism |
| CN105416610A (en) * | 2014-09-17 | 2016-03-23 | 波音公司 | Space structure deployment system |
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| CN204791115U (en) * | 2015-07-28 | 2015-11-18 | 田原 | Manual check lock lever counting assembly of preventer |
| CN105345643A (en) * | 2015-11-20 | 2016-02-24 | 苏州光韵达光电科技有限公司 | SMT laser mold board polishing clamp |
| CN207580198U (en) * | 2017-11-29 | 2018-07-06 | 中国科学院沈阳自动化研究所 | Multipoint clamping formula locks relieving mechanism |
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| CN109515771A (en) * | 2018-12-27 | 2019-03-26 | 中国科学院沈阳自动化研究所 | A kind of micro- interference relieving mechanism in space and its locking, micro- interference method for releasing |
| CN109515771B (en) * | 2018-12-27 | 2023-09-12 | 中国科学院沈阳自动化研究所 | Space micro-interference release mechanism and locking and micro-interference release method thereof |
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