CN109455314A - A kind of pincer pressing device and the compressing method using the device - Google Patents
A kind of pincer pressing device and the compressing method using the device Download PDFInfo
- Publication number
- CN109455314A CN109455314A CN201811616127.0A CN201811616127A CN109455314A CN 109455314 A CN109455314 A CN 109455314A CN 201811616127 A CN201811616127 A CN 201811616127A CN 109455314 A CN109455314 A CN 109455314A
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- Prior art keywords
- crimper
- pressing device
- caliper
- spacecraft
- pin shaft
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- 238000003825 pressing Methods 0.000 title claims abstract description 39
- 238000000034 method Methods 0.000 title claims abstract description 15
- 210000000080 chela (arthropods) Anatomy 0.000 title claims description 8
- 230000037452 priming Effects 0.000 claims abstract description 24
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 13
- 230000006835 compression Effects 0.000 abstract description 8
- 238000007906 compression Methods 0.000 abstract description 8
- 230000008646 thermal stress Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 210000002445 nipple Anatomy 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
The present invention provides the compressing methods of a kind of pincerlike pressing device and the application device, the pressing device includes caliper, the caliper includes pedestal, pin shaft, torsional spring and crimper, two crimpers are respectively rotatably installed on pin shaft, the torsional spring is arranged on pin shaft, and two rotating arms of the torsional spring are respectively engaged in a crimper binding clip portion, which is each provided with the fixed structure for fixing rope.The compressing method of a kind of pincerlike pressing device and application apparatus of the present invention, it can implement multiple spot compression to compacting part by a priming system component and multiple calipers, priming system assembly consumption is few, firstly reduce the Space Vehicle System wasting of resources, solve the problems, such as that the multiple spot of slender rod piece and plate class member compresses, secondly thermal environment is adaptable, and the deflection of low-angle can occur around the shaft for crimper, compacting part is suitable for because of thermal deformation caused by temperature alternating, reduces and compresses a point thermal stress.
Description
Technical field
The invention belongs to spacecraft production fields, more particularly, to the compression of a kind of pincerlike pressing device and the application device
Method.
Background technique
In space mission, to adapt to the emission state enveloping space demand that rocket provides, spacecraft structure during lift-off
Part generally takes gathering compaction measure, after entering the orbit or objects outside Earth lands, then is unfolded to play spacecraft body function.
The conventional fixed-type pressing device of space industry is generally compressed point position at every place and is compressed using a priming system component or firer
Device, and for slender rod piece and plate class member, size is larger, need to be compressed in multiple spot, priming system component or firer's pressure
Tight device dosage is more, and weight and power consumption cost are big.Especially for large complicated spacecraft, priming system component or firer are compressed
Device usage quantity is restricted by the various factors of whole device, it is difficult to meet above-mentioned slender rod piece, the priming system component of plate class member is used
Amount demand.
On the other hand, in-orbit fly of spacecraft need to generally undergo the thermal environment of temperature alternating, especially for deep space exploration
Spacecraft, the flight time is long, and often, thermal environment adaptability is particularly important for temperature alternating.And slender rod piece, plate class member
Thermal expansion coefficient, often with spacecraft ontological existence difference.When thermal deformation occurring in temperature alternating environment, same compression point
On position, slender rod piece, plate class member and spacecraft ontology will generate the thermal deformation changing of the relative positions, cause compression point position big heat occur and answer
Power even causes to compress point destruction.
Summary of the invention
In view of this, the present invention is directed to propose it is a kind of pincer pressing device and application the device compressing method, with meet
When spacecraft goes up to the air, slender rod piece and plate class member compress demand.
In order to achieve the above objectives, the technical scheme of the present invention is realized as follows:
A kind of pincer pressing device, including caliper, the caliper include pedestal, pin shaft, torsional spring and crimper, and the pin shaft is solid
On the base, two crimpers are symmetrical arranged dress, which is respectively rotatably installed on pin shaft, and the torsional spring setting exists
On pin shaft, and two rotating arms of the torsional spring are respectively engaged in a crimper binding clip portion, and two crimper binding clip portions are correspondingly provided with
Clamping structure, two crimper pincers tail portions are each provided with the connection structure for fixing rope.
Further, the clamping structure is the arc-shaped groove that two crimper binding clip face sides respectively open up,
Arc-shaped groove center line is parallel with pin shaft, and after two binding clips close up, two arc-shaped grooves form circular fixation hole.
Further, the pedestal also sets up two limited posts, and two limited posts are parallel with pin shaft and are arranged in pedestal
Away from one end of binding clip, and two limited posts are symmetricly set on the two sides of two crimpers.
Further, the connection structure is mounting hole corresponding with rope, the line of symmetry and mounting hole of two crimpers
Vertical and intersectant centerline.
Further, gasket is each provided between two crimpers, between torsional spring and its adjacent crimper.
Compared with the existing technology, a kind of pincerlike pressing device of the present invention has the advantage that
A kind of pincerlike pressing device of the present invention, is provided with torsional spring, torsional spring acts on lower two between two crimpers
Crimper maintains a normally open state, when compressing to spacecraft component, by rope by the binding clip portion snap-in of caliper in spacecraft component
Fixed structure on, then by rope pretightning force to spacecraft component compress, guarantee the component enveloping space conditions dictate, and
Caliper is greatly reduced relative to priming system assembly quality, reduces priming system assembly consumption using this caliper, therefore reduce boat
Its device system resource cost.
A kind of compressing method for applying pincerlike pressing device, comprising the following steps:
(1) according to spacecraft Components Shape and Characteristics of Thermal deformation set the spacecraft component to compacted position, and select
Be arranged fixed structure to compacted position, in the selected setting fixed structure to which fixed structure is respectively arranged at compacted position,
In residue to respectively be independently arranged hold-down mechanism at compacted position, by the hold-down mechanism in its corresponding point position by spacecraft component
It compresses；
(2) according to the fixed structure being arranged on spacecraft component, it is correspondingly arranged priming system component in spacecraft appropriate location,
Each priming system component is at least while corresponding with two fixed structures on the component；
(3) each fixed structure is correspondingly arranged a caliper, and the connection structure of each crimper of the caliper is correspondingly arranged
One rope is furthered two crimper tail ends by two ropes, is clamped in it by the clamping structure of the caliper and is corresponded to admittedly
Determine in structure, rope corresponds to the locking mechanism on priming system component by the fixed structure and is locked, and caliper is pre- by rope
Clamp force presses spacecraft component；
(4) when spacecraft structural member development discharges, firer's cutter of priming system component cuts off rope, and caliper, which unclamps, releases folder
Tightly, which discharges.
Further, the hold-down mechanism is the conventional fixed-type firer pressing device (4) being independently arranged.
Compared with the existing technology, a kind of compressing method for applying pincerlike pressing device of the present invention has following excellent
Gesture:
(1) multiple spot compression, priming system can be implemented to compacting part by a priming system component and multiple crimper components
Assembly consumption is few, reduces the Space Vehicle System wasting of resources, solves the problems, such as that the multiple spot of slender rod piece and plate class member compresses.
(2) thermal environment is adaptable, and the deflection of low-angle can occur around the shaft for crimper, is suitable for compacting part because of temperature
Thermal deformation caused by alternation is spent, reduces and compresses point thermal stress, be particularly suitable for pressed component and spacecraft ontology thermal expansion coefficient
Compression under having differences is implemented.
(3) composition is simple, and weight is small, separates between crimper and compacting part after unlock, and after unlock under the effect of torsion spring
It actively avoids pressed component and automatically keeps limit, ensure that the activity space of compacting part.
Detailed description of the invention
The attached drawing for constituting a part of the invention is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is a kind of pincerlike pressing device structural schematic diagram described in the embodiment of the present invention；
Fig. 2 is a kind of pincerlike pressing device schematic cross-sectional view described in the embodiment of the present invention；
Fig. 3 is tridimensional schematic diagram in a kind of pincerlike pressing device described in the embodiment of the present invention；
Fig. 4 is a kind of pincerlike pressing device opening figure described in the embodiment of the present invention；
Fig. 5 is a kind of one structural schematic diagram of compressing method embodiment of the present invention；
Fig. 6 is a kind of two structural schematic diagram of compressing method embodiment of the present invention.
Description of symbols:
1- caliper；11- pedestal；12- crimper；121- arc-shaped groove；13- gasket；14- torsional spring；15- pin shaft；16- limit
Position column；2- rope；3- priming system component；The fixed firer's pressing device of 4-；5- spacecraft component；51- fixed structure.
Specific embodiment
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
Limitation of the invention.In addition, term " first ", " second " etc. are used for description purposes only, it is not understood to indicate or imply phase
To importance or implicitly indicate the quantity of indicated technical characteristic.The feature for defining " first ", " second " etc. as a result, can
To explicitly or implicitly include one or more of the features.In the description of the present invention, unless otherwise indicated, " multiple "
It is meant that two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood by concrete condition
Concrete meaning in the present invention.
The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
As shown in Figs 1-4, a kind of pincerlike pressing device, including caliper 1, the caliper 1 include pedestal 11, pin shaft 15, torsional spring
14 and crimper 12, the pin shaft 15 be fixedly mounted on the base 11, two crimpers 12 are symmetrical arranged, and two crimpers 12 are respective
It is rotatably installed on pin shaft 15, the torsional spring 14 is arranged on pin shaft 15, and 14 two rotating arms of the torsional spring are respectively engaged in one
A 12 binding clip portion of crimper, under torsional spring 14 acts on, two binding clip portions are always-on, and two 12 binding clip portions of crimper are correspondingly provided with
Clamping structure, it is preferred that the clamping structure is the arc-shaped groove that two 12 binding clip face sides of crimper respectively open up
121,121 center line of arc-shaped groove is parallel with pin shaft 15, and after two binding clips close up, two arc-shaped grooves 121 form circle
Fixation hole.Two crimpers 12 clamp tail portion and are each provided with the connection structure for fixing rope 2, and the connection structure is and restricts
The corresponding mounting hole of rope, the line of symmetry and mounting hole vertical and intersectant centerline of two crimpers 12, mounting hole is interior to be equipped with for pacifying
Fill the cable nipple of rope 2.
In the present embodiment, the pedestal 11 also sets up two limited posts 16, two limited posts 16 it is parallel with pin shaft 15 and
One end that pedestal 11 deviates from binding clip is set, and two limited posts 16 are symmetricly set on the two sides of two crimpers 12.The structure
Two 12 opening angles of crimper are defined, prevents in the crimper opening procedure and other positions is dry on spacecraft structure
It relates to.
In the present embodiment, gasket is each provided between two crimpers 12, between torsional spring 14 and its adjacent crimper 12
13。
Embodiment one, as shown in figure 5, illustrating so that spacecraft component is long and narrow class formation part as an example, a kind of pincerlike pressure of application
The compressing method of tight device, comprising the following steps:
(1) according to the long and narrow class spacecraft Components Shape and Characteristics of Thermal deformation, in each long side two of the spacecraft component
End and middle are respectively arranged one to compacted position, and totally six to compacted position, and six to compacted position about spacecraft
Component central axes are symmetrical arranged, and to guarantee the stability of spacecraft component, wait for that fixed structure is respectively arranged at compacted position at this
51；
(2) according to the fixed structure being arranged on spacecraft component, priming system component is correspondingly arranged in spacecraft appropriate location
3, each priming system component 3 is at least while corresponding with two fixed structures 51 on the component；
(3) each fixed structure is correspondingly arranged a caliper 1, and the cable nipple of each crimper 12 of the caliper 1 is corresponding
One rope 2 is set, two 12 tail ends of crimper are furthered by two ropes 2, the binding clip portion of two crimpers 12 closes up, and leads to
The clamping structure for crossing the caliper 1 is clamped in it and corresponds on fixed structure 51, at this point, 1 two crimper line of symmetries of caliper vertically navigate
Its device component compacted position place guarantees in end face, the i.e. longitudinal deformation direction quadrature arrangement with spacecraft component of crimper 12
Crimper 12 adapts to the component thermal deformation, and rope 2 passes through the locking mechanism locking on the corresponding priming system component 3 of the fixed structure 51
Fixed, caliper 1 is pressed two ends of spacecraft component by rope pretightning force；
(4) when spacecraft structural member development discharges, rope 2,1 pine of caliper are cut off by firer's cutter of priming system component 3
Unwind except clamping, which discharges.
The present embodiment one is that spacecraft component compresses all by caliper --- rope, which compresses, to be completed, according to actual needs, can also
Using the caliper --- rope compress and conventional fixed-type firer pressing device combination complete, such as spacecraft component be compared with
When wide plate construction, using the fixed larger pressing force of firer's pressing device, and with this caliper --- rope compress combination reach
To stable compression and it is suitable for big thermal deformation demand.
As shown in fig. 6, fixed fire is arranged at the larger position of spacecraft stress when spacecraft component is long and narrow class plate
Work pressing device 4, the present embodiment is larger to compacted position by stress of each middle position of long side of spacecraft component, then is navigating
The independent fixed firer's pressing device 4 of its each middle position of long side of device component setting, utilizes fixed firer's pressing device 4
It is capable of providing larger pressing force, meets larger pressing force demand in the mobile composition of the wider plate class member, meanwhile, the spacecraft structure
Part other wait at compacted position such as end positions that caliper still to be used to compress mode, 4 He of conventional fixed-type firer pressing device
Compression mode is carried out using multiple pincerlike pressing devices and combines combined application, improves mechanical environment capacity, and be suitable for heat
Deformation；When spacecraft structural member development, the fixed unlock of firer's pressing device 4 is unclamped, firer's cutter cutting of priming system component 3
Rope 2, caliper 1, which unclamps to release, to be clamped, spacecraft structural member development release.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (7)
1. it is a kind of pincer pressing device, it is characterised in that: including caliper (1), the caliper (1) include pedestal (11), pin shaft (15),
Torsional spring (14) and crimper (12), the pin shaft (15) are packed on pedestal (11), and two crimpers (12) are symmetrical arranged, this two
A crimper (12) is respectively rotatably installed on pin shaft (15), and the torsional spring (14) is arranged on pin shaft (15), and the torsional spring
(14) two rotating arms are respectively engaged in crimper (12) binding clip portion, and two crimper (12) binding clip portions are correspondingly provided with clamping
Structure, two crimper (12) pincers tail portions are each provided with the connection structure for fixing rope (2).
2. a kind of pincerlike pressing device according to claim 1, it is characterised in that: the clamping structure is two crimpers
(12) arc-shaped groove (121) that binding clip face side respectively opens up, arc-shaped groove (121) center line and pin shaft (15) are flat
Row, after two binding clips close up, two arc-shaped grooves (121) form circular fixation hole.
3. a kind of pincerlike pressing device according to claim 1, it is characterised in that: the pedestal (11) also sets up two limits
Position column (16), two limited posts (16) are parallel with pin shaft (15) and one end in pedestal (11) away from binding clip is arranged, and two
Limited post (16) is symmetricly set on the two sides of two crimpers (12).
4. a kind of pincerlike pressing device according to claim 1, it is characterised in that: the connection structure is corresponding with rope
Mounting hole, the line of symmetry and mounting hole vertical and intersectant centerline of two crimpers (12).
5. a kind of pincerlike pressing device according to claim 1, it is characterised in that: between two crimpers (12), turn round
Gasket (13) are each provided between spring (14) and its adjacent crimper (12).
6. it is a kind of application as described in claim any one of 1-5 pincer pressing device compressing method, it is characterised in that: including with
Lower step:
(1) according to spacecraft component (5) shape and Characteristics of Thermal deformation set the spacecraft component to compacted position, and selected set
Set fixed structure (51) to compacted position, in selected setting fixed structure (51) to which fixation is respectively arranged at compacted position
Structure (51) is incited somebody to action by the hold-down mechanism in its corresponding point position in residue to respectively be independently arranged hold-down mechanism at compacted position
Spacecraft component compresses；
(2) according to the fixed structure (51) being arranged on spacecraft component (5), priming system group is correspondingly arranged in spacecraft appropriate location
Part (3), each priming system component are at least while corresponding with two fixed structures on the component；
(3) each fixed structure is correspondingly arranged a caliper (1), the connection structure of each crimper (12) in the caliper (1)
A rope (2) are correspondingly arranged, two crimper (12) tail ends are furthered by two ropes (2), pass through the folder of the caliper (1)
Locking structure is clamped in it and corresponds on fixed structure, and rope (2) corresponds to the locking machine on priming system component (3) by the fixed structure
Structure is locked, and caliper (1) is pressed spacecraft component by rope pretightning force；
(4) when spacecraft structural member development discharges, firer's cutter of priming system component (3) cuts off rope (2), and caliper (1) unclamps
It releases and clamps, spacecraft structural member development release.
7. a kind of compressing method for applying pincerlike pressing device according to claim 6, it is characterised in that: the compacting machine
Structure is the conventional fixed-type firer pressing device (4) being independently arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811616127.0A CN109455314A (en) | 2018-12-27 | 2018-12-27 | A kind of pincer pressing device and the compressing method using the device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811616127.0A CN109455314A (en) | 2018-12-27 | 2018-12-27 | A kind of pincer pressing device and the compressing method using the device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109455314A true CN109455314A (en) | 2019-03-12 |
Family
ID=65615219
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811616127.0A Pending CN109455314A (en) | 2018-12-27 | 2018-12-27 | A kind of pincer pressing device and the compressing method using the device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109455314A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111409876A (en) * | 2020-04-09 | 2020-07-14 | 北京控制工程研究所 | Tool box device for locking multi-degree-of-freedom mechanism |
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| US20030041702A1 (en) * | 2001-08-31 | 2003-03-06 | Kang Hsin Fa | Automobile brake cable positioning pliers |
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