CN209125407U - A kind of technique for aircraft composite fixture - Google Patents
A kind of technique for aircraft composite fixture Download PDFInfo
- Publication number
- CN209125407U CN209125407U CN201822160851.9U CN201822160851U CN209125407U CN 209125407 U CN209125407 U CN 209125407U CN 201822160851 U CN201822160851 U CN 201822160851U CN 209125407 U CN209125407 U CN 209125407U
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- Prior art keywords
- hole
- technique
- aircraft composite
- hydraulic cylinder
- sliding
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- 239000002131 composite material Substances 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 22
- 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 12
- 230000001788 irregular Effects 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
Abstract
A kind of technique for aircraft composite fixture, belongs to aircraft technical field of processing equipment.The upper surface of pedestal is provided with sliding slot, being slidably connected in sliding slot, there are two sliding blocks, hydraulic cylinder is fixed between two sliding blocks, the upper surface of each sliding block is provided with clamp system, two clamp systems are oppositely arranged, multiple tapped through holes are provided on the side wall of pedestal, tapped through hole is axially perpendicular to the axial direction of hydraulic cylinder, is threaded with threaded rod in each tapped through hole；The utility model can clamp irregular shape and adapt to the airplane parts of a variety of different models, save a large amount of fixture the space occupied；Meanwhile its structure is simple, it is easy to use.
Description
Technical field
The utility model relates to a kind of fixture, especially a kind of technique for aircraft composite fixture belongs to aircraft process equipment
Technical field.
Background technique
Composite material has thermal stability good, specific strength height and the big advantage of specific modulus.Currently, the major part that aircraft includes
Bearing member is all made of composite material, to be cut after composite molding, drilling, turning, the machinings such as milling could be at
For fabricated part, often to fix composite material using fixture in mechanical processing process, since airplane parts are mostly not
Regular shape and type is more, the fixture for needing to manufacture and design a large amount of different model carrys out retaining element, and model specification is more, uses
Inconvenience increases the manufacturing cost of airplane parts.
Summary of the invention
The purpose of this utility model is to provide a kind of technique for aircraft composite fixture, it can clamp irregular shape and
The airplane parts for adapting to a variety of different models save a large amount of fixture the space occupied；Meanwhile its structure is simple, it is easy to use.
Realize above-mentioned purpose, the utility model takes following technical proposals: a kind of technique for aircraft composite fixture, including base
Seat, hydraulic cylinder, two sliding blocks, two clamp systems and multiple threaded rods；
The upper surface of the pedestal is provided with sliding slot, and being slidably connected in the sliding slot, there are two sliding blocks, described in two
Sliding block between be fixed with hydraulic cylinder, the upper surface of the sliding block is provided with clamp system, clamping described in two
Mechanism is oppositely arranged, and multiple tapped through holes are provided on the side wall of the pedestal, and the tapped through hole is axially perpendicular to liquid
The axial direction of cylinder pressure is each threaded with threaded rod in the tapped through hole.
Compared with prior art, the utility model has the beneficial effects that
1, the utility model multiple fixtures can be set side by side, and be threadedly coupled by threaded rod, clamp irregular shape
The airplane parts of shape, it is easy to use；
2, the clamp system of the utility model can suitably increase and rotate gripping block, the aircraft zero suitable for different model
Part.
Detailed description of the invention
Fig. 1 is the overall structure axonometric drawing of the technique for aircraft composite fixture of the utility model；
Fig. 2 is clamp system broken away view shown in FIG. 1.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, to the technical solution in the utility model carry out it is clear,
It being fully described by, it is clear that described embodiment is only a part of the embodiment of utility model, instead of all the embodiments,
Based on the embodiments of the present invention, obtained by those of ordinary skill in the art without making creative efforts
Every other embodiment, fall within the protection scope of the utility model.
Specific embodiment 1: the utility model discloses a kind of technique for aircraft composite fixture as shown in Fig. 1 ~ Fig. 2,
Including pedestal 1, the clamp system 5 of sliding block 3, two of hydraulic cylinder 2, two and multiple threaded rods 4；
The upper surface of the pedestal 1 is provided with sliding slot 1-1, is slidably connected in the sliding slot 1-1 there are two sliding block 3,
It is fixed with hydraulic cylinder 2 between sliding block 3 described in two, the upper surface of the sliding block 3 is provided with clamp system 5, and two
A clamp system 5 is oppositely arranged, and multiple tapped through hole 1-2, the screw thread are provided on the side wall of the pedestal 1
Through-hole 1-2 is axially perpendicular to the axial direction of hydraulic cylinder 2, is threaded with threaded rod 4 in each tapped through hole 1-2.
Specific embodiment 2: as shown in Fig. 2, present embodiment is made furtherly to specific embodiment one
Bright, each clamp system 5 is including fastening bolt 5-1, gripping block 5-2, jackscrew 5-5, two connecting plate 5-3 and four
Slide bar 5-4；
Through-hole 5-21 is provided on the side wall of the gripping block 5-2, the through-hole 5-21's is axially parallel to screw thread
The axial direction of through-hole 1-2 is installed with fastening bolt 5-1, the fastening bolt 5-1 and two connecting plate 5- in the through-hole 5-21
Internal thread hole 5-31 that 3 centers are equipped with is threadedly coupled, and connecting plate 5-3 described in two is arranged in the two sides of gripping block 5-2, and two
The vertical chute 5-32, the vertical chute 5-32 of connecting plate 5-3 described in two are provided on the side wall of the connecting plate 5-3
On be vertically slidably connected there are two slide bar 5-4, and between each the connecting plate 5-3 and corresponding two slide bar 5-4
It is fixedly connected by jackscrew 5-5, the lower end of slide bar 5-4 described in four is each attached on sliding block 3.
Specific embodiment 3: as shown in Fig. 2, present embodiment is made furtherly to specific embodiment two
It is bright, rubber pad 5-22 is respectively and fixedly provided on gripping block 5-2 described in two opposite side wall；The rubber pad 5-22 avoids damaging
The surface of technique for aircraft composite.
Specific embodiment 4: as shown in Fig. 2, present embodiment is made furtherly to specific embodiment two
Bright, each fastening bolt 5-1 interlude is polished rod, and the both ends outer wall of fastening bolt 5-1 has oppositely oriented screw thread.
Specific embodiment 5: as shown in Figure 1, present embodiment is made furtherly to specific embodiment one
Bright, one of sliding block 3 of two sliding blocks 3 is fixedly connected with the cylinder body bottom end of hydraulic cylinder 2, described in remaining one
Sliding block 3 is fixedly connected with the outer end of the cylinder rod of hydraulic cylinder 2.
When the utility model is used, according to the length of technique for aircraft composite, appropriate number of grip device of taking, and according to
It is secondary to be arranged side by side, by the corresponding screw-in tapped through hole 1-2 of multiple threaded rods 4, fix fixture arranged side by side；
Technique for aircraft composite is placed between the clamp system 5 being oppositely arranged, successively starts hydraulic cylinder 2, as gripping block 5-2
On rubber pad 5-22 clamp technique for aircraft composite when, hydraulic cylinder 2 stops working, clamp work terminate.
When technique for aircraft composite is higher and surface is inclined-plane, need to adjust the angle of clamp system 5, upward sliding to conjunction
Suitable height, successively tightens jackscrew 5-5, unscrews fastening bolt 5-1, makes to generate seam between two connecting plate 5-3 and gripping block 5-2
Gap rotates the angle of gripping block 5-2, is bonded the surface of technique for aircraft composite, screws fastening bolt 5-1, make two connecting plate 5-3
It is fastened between gripping block 5-2, clamping work terminates.
It is obvious to a person skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and
And without departing substantially from the spirit or essential attributes of the utility model, it can realize that this is practical new in the form of others dress body
Type.Therefore, in all respects, the present embodiments are to be considered as illustrative and not restrictive, this is practical new
The range of type is indicated by the appended claims rather than the foregoing description, it is intended that containing the condition of equivalent for falling in claim
All changes in justice and range are embraced therein.It should not treat any reference in the claims as limiting
Related claim.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
The other embodiments being understood that.
Claims (5)
1. a kind of technique for aircraft composite fixture, it is characterised in that: including pedestal (1), hydraulic cylinder (2), two sliding blocks (3), two
A clamp system (5) and multiple threaded rods (4)；
The upper surface of the pedestal (1) is provided with sliding slot (1-1), and being slidably connected in the sliding slot (1-1), there are two sliding blocks
(3), hydraulic cylinder (2) are fixed between sliding block (3) described in two, the upper surface of each sliding block (3) is provided with folder
Tight mechanism (5), clamp system (5) described in two are oppositely arranged, and it is logical that multiple screw threads are provided on the side wall of the pedestal (1)
Hole (1-2), the tapped through hole (1-2) are axially perpendicular to the axial direction of hydraulic cylinder (2), each tapped through hole (1-2)
Inside it is threaded with threaded rod (4).
2. a kind of technique for aircraft composite fixture according to claim 1, it is characterised in that: each clamp system
It (5) include fastening bolt (5-1), gripping block (5-2), jackscrew (5-5), two connecting plates (5-3) and four slide bars (5-4)；
It is provided with through-hole (5-21) on the side wall of the gripping block (5-2), the through-hole (5-21) is axially parallel to spiral shell
The axial direction of line through-hole (1-2), the through-hole (5-21) is interior to be installed with fastening bolt (5-1), the fastening bolt (5-1) and two
The internal thread hole (5-31) that a connecting plate (5-3) center is equipped with is threadedly coupled, and the setting of connecting plate (5-3) described in two is clamping
The two sides of block (5-2), being vertically slidably connected on connecting plate (5-3) described in two, there are two slide bar (5-4), and each institute
It is fixedly connected between the connecting plate (5-3) stated and corresponding two slide bars (5-4) by jackscrew (5-5), slide bar described in four
The lower end of (5-4) is each attached on sliding block (3).
3. a kind of technique for aircraft composite fixture according to claim 2, it is characterised in that: gripping block described in two
Rubber pad (5-22) is respectively and fixedly provided on (5-2) opposite side wall.
4. a kind of technique for aircraft composite fixture according to claim 2, it is characterised in that: each fastening bolt
(5-1) interlude is polished rod, and the both ends outer wall of fastening bolt (5-1) has oppositely oriented screw thread.
5. a kind of technique for aircraft composite fixture according to claim 1, it is characterised in that: two sliding blocks (3)
One of sliding block (3) be fixedly connected with the cylinder body bottom end of hydraulic cylinder (2), sliding block (3) described in remaining one with it is hydraulic
The outer end of the cylinder rod of cylinder (2) is fixedly connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822160851.9U CN209125407U (en) | 2018-12-22 | 2018-12-22 | A kind of technique for aircraft composite fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822160851.9U CN209125407U (en) | 2018-12-22 | 2018-12-22 | A kind of technique for aircraft composite fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209125407U true CN209125407U (en) | 2019-07-19 |
Family
ID=67249152
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822160851.9U Active CN209125407U (en) | 2018-12-22 | 2018-12-22 | A kind of technique for aircraft composite fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209125407U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110893590A (en) * | 2019-12-10 | 2020-03-20 | 中航沈飞民用飞机有限责任公司 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
| CN112692611A (en) * | 2020-12-31 | 2021-04-23 | 保定向阳航空精密机械有限公司 | Quick adjustment formula flat-nose pliers |
-
2018
- 2018-12-22 CN CN201822160851.9U patent/CN209125407U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110893590A (en) * | 2019-12-10 | 2020-03-20 | 中航沈飞民用飞机有限责任公司 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
| CN112692611A (en) * | 2020-12-31 | 2021-04-23 | 保定向阳航空精密机械有限公司 | Quick adjustment formula flat-nose pliers |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240125 Address after: No.3, Hanan Third Road, core area of Hanan industrial new town, Pingfang District, Harbin City, Heilongjiang Province Patentee after: GUANGLIAN AVIATION INDUSTRY Co.,Ltd. Country or region after: China Address before: 311, Chuangye building, No.18, Gaoxin 2nd Road, Nanchang hi tech Industrial Development Zone, Jiangxi 330000 Patentee before: Guanglian Airlines (Nanchang) Co.,Ltd. Country or region before: China |