CN107132032A - A kind of fuselage wallboard fatigue test clamper - Google Patents
A kind of fuselage wallboard fatigue test clamper Download PDFInfo
- Publication number
- CN107132032A CN107132032A CN201710200403.4A CN201710200403A CN107132032A CN 107132032 A CN107132032 A CN 107132032A CN 201710200403 A CN201710200403 A CN 201710200403A CN 107132032 A CN107132032 A CN 107132032A
- Authority
- CN
- China
- Prior art keywords
- joint
- testpieces
- fuselage wallboard
- angle
- fatigue test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Abstract
The invention discloses a kind of fuselage wallboard fatigue test clamper, belong to aircraft fatigue experimental design field.Including gripping section (1), joint (2), angle box (3), gripping section (1) is arranged on the end face of joint (2), the other end of joint (2) is connected with two angle boxes (3), any angle box (3) includes two vertical plate faces, one of plate face is fixed on the joint (2), another plate face of two angle boxes (3) is parallel to each other and leaves gap, for clamp assay part, the gripping width adapts to testpieces size.The present invention makes fuselage wallboard testpieces obtain preferable power transmission effect under Tensile or Compressive Loading effect, and testpieces failure mode can realize the loading to different fuselage wallboard sizes closer to true by the size of alignment jig.
Description
Technical field
The invention belongs to aircraft fatigue experimental design field, and in particular to a kind of fuselage wallboard fatigue test clamper.
Background technology
Fuselage wallboard needs to carry out fatigue test in the stages such as type selecting, repairings.For size very big testpieces, typically make
Loaded with pressurized strut, experimental scale is big, testing expenses are high.And the testpieces of the wallboard for one frame position containing three stringers, make
Dynamic cylinder load test is complicated, costly, directly can be loaded with 10-50 tons of fatigue tester.Because test machine clamping is wide
Degree is limited, and testpieces can not be clamped directly, it is therefore desirable to design switching fixture.
The content of the invention
In order to solve the above problems, the present invention proposes a kind of fuselage wallboard fatigue test clamper, is particularly suitable for use in three
The fatigue test of different in width fuselage wallboard in the range of one frame position of stringer.
Fuselage wallboard fatigue test clamper of the present invention mainly includes gripping section, joint and angle box, and gripping section, which is arranged on, to be connect
On the end face of head, the other end of joint is connected with two angle boxes, and any angle box includes two vertical plate faces, wherein
One plate face is fixed on the joint, and another plate face of two angle boxes is parallel to each other and leaves gap, for clamp assay
Part, the gripping width adapts to testpieces size.
Preferably, gripping section is integrally formed with joint.
Preferably, the angle box also includes the reinforcement being arranged between two plate faces.
Preferably, two plate faces of the angle box are provided with through hole, are connected respectively with joint and testpieces by bolt
Connect.
The beneficial effect that the present invention is produced：Manufacture and design simple, practical function notable.Pass through the design and peace of this fixture
Dress, makes fuselage wallboard testpieces obtain preferable power transmission effect under Tensile or Compressive Loading effect, testpieces failure mode is closer
Truly, and the loading to different fuselage wallboard sizes can be realized by the size of alignment jig.This fixture can extensive use
In the Tensile or Compressive Loading fatigue test of airframe wallboard testpieces.
Brief description of the drawings
Fig. 1 is the front view of a preferred embodiment of fuselage wallboard fatigue test clamper of the present invention.
Fig. 2 is the angle box structural representation of embodiment illustrated in fig. 1.
Wherein, 1 is gripping section, and 2 be joint, and 3 be angle box, and 31 be reinforcement, and 32 be through hole.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
The present invention proposes a kind of fuselage wallboard fatigue test clamper, is particularly suitable for use in the range of three stringers, one frame position
The fatigue test of different in width fuselage wallboard.
As shown in figure 1, fuselage wallboard fatigue test clamper of the present invention mainly includes gripping section 1, joint 2 and angle box 3, folder
Hold section 1 to be arranged on the end face of joint 2, the other end of joint 2 is connected with two angle boxes 3, and any angle box 3 includes two
Individual vertical plate face, one of plate face is fixed on the joint 2, and another plate face of two angle boxes is parallel to each other and left
Gap, for clamp assay part, the gripping width adapts to testpieces size.
In the present embodiment, gripping section 1 is integrally formed with joint 2.
In the present embodiment, the angle box 3 also includes the reinforcement 31 being arranged between two plate faces, with reference to Fig. 2, shown two
Individual plate face is mutually perpendicular to, and reinforcement 31 is the gusset of right-angle structure, and two vertical edges of gusset are separately fixed at reinforcement 31
In two plate faces, for example, weld or be integrally formed, it is illustrated that described in reinforcement be at least three, be separately positioned on the two of angle box 3
End and middle, reinforcement and angle box board medial arc transition.
In the present embodiment, two plate faces of the angle box 3 are provided with through hole 32, for through bolt, it is possible to understand that
It is that joint and testpieces correspondence position are also equipped with through hole, and angle box 3 is bolted with joint 2 and testpieces respectively.
The applicable fatigue tester of invention is 10-50 tons, and applicable experiment loading range is ± 15KN.Testpieces passes through
M10 bolt is arranged on the angle box of fixture.It is that the loading to testpieces can be achieved to loading axis tension and compression by testing machine, experiment
When, first testpieces is installed on two angle boxes of fixture in Fig. 1 by M10 bolt, tighten the torque of bolt for 17.5 ±
1.8 Ns of rice are adjusted according to the frictional force of test requirements document, and bolt arrangement is as shown in Figure 2.Two angle boxes by bolt with
Joint is connected, and the torque for tightening bolt is respectively 30.5 ± 3.0 Ns of rice, and gripping section is finally clamped in into fatigue tester respectively
Upper and lower chuck on or be fixed on base.It is that the loading to testpieces can be achieved to loading axis tension and compression by testing machine.Experiment
After part loaded segment and fixture clamping, load transmission is cut offer mainly by skin-friction force and bolt.Clamp material is used
30CrMnS iA, it is ensured that fixture does not produce destruction and is permanently deformed in process of the test.
The beneficial effect that the present invention is produced：Manufacture and design simple, practical function notable.Pass through the design and peace of this fixture
Dress, makes fuselage wallboard testpieces obtain preferable power transmission effect under Tensile or Compressive Loading effect, testpieces failure mode is closer
Truly, and the loading to different fuselage wallboard sizes can be realized by the size of alignment jig.This fixture can extensive use
In the Tensile or Compressive Loading fatigue test of airframe wallboard testpieces.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (4)
1. a kind of fuselage wallboard fatigue test clamper, it is characterised in that：Including gripping section (1), joint (2) and angle box (3), folder
Hold section (1) to be arranged on the end face of joint (2), the other end of joint (2) is connected with two angle boxes (3), any angle
Box (3) includes two vertical plate faces, and one of plate face is fixed on the joint (2), another plate of two angle boxes (3)
Face is parallel to each other and leaves gap, and for clamp assay part, the gripping width adapts to testpieces size.
2. fuselage wallboard fatigue test clamper as claimed in claim 1, it is characterised in that：Gripping section (1) and joint (2) one
Shaping.
3. fuselage wallboard fatigue test clamper as claimed in claim 1, it is characterised in that：The angle box (3) also includes setting
Reinforcement (31) between two plate faces.
4. fuselage wallboard fatigue test clamper as claimed in claim 1, it is characterised in that：Two plate faces of the angle box (3)
Through hole (32) is provided with, is bolted respectively with joint (2) and testpieces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710200403.4A CN107132032A (en) | 2017-03-30 | 2017-03-30 | A kind of fuselage wallboard fatigue test clamper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710200403.4A CN107132032A (en) | 2017-03-30 | 2017-03-30 | A kind of fuselage wallboard fatigue test clamper |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107132032A true CN107132032A (en) | 2017-09-05 |
Family
ID=59715839
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710200403.4A Pending CN107132032A (en) | 2017-03-30 | 2017-03-30 | A kind of fuselage wallboard fatigue test clamper |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107132032A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109649682A (en) * | 2018-10-31 | 2019-04-19 | 中国飞机强度研究所 | A kind of 3 points of wingbar curved Buckling Fatigue Testing fixtures |
| CN110254748A (en) * | 2019-05-27 | 2019-09-20 | 中国飞机强度研究所 | A kind of connector-wall panel structure static pressure experimental rig |
| CN113776930A (en) * | 2021-09-01 | 2021-12-10 | 中国航发北京航空材料研究院 | Combined material T type connecting piece is drawn, is pressed experimental universal fixturing |
-
2017
- 2017-03-30 CN CN201710200403.4A patent/CN107132032A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109649682A (en) * | 2018-10-31 | 2019-04-19 | 中国飞机强度研究所 | A kind of 3 points of wingbar curved Buckling Fatigue Testing fixtures |
| CN109649682B (en) * | 2018-10-31 | 2022-08-09 | 中国飞机强度研究所 | Three-point bending and buckling fatigue test fixture for wing beam |
| CN110254748A (en) * | 2019-05-27 | 2019-09-20 | 中国飞机强度研究所 | A kind of connector-wall panel structure static pressure experimental rig |
| CN110254748B (en) * | 2019-05-27 | 2023-02-10 | 中国飞机强度研究所 | Connector-wallboard structure static compression test device |
| CN113776930A (en) * | 2021-09-01 | 2021-12-10 | 中国航发北京航空材料研究院 | Combined material T type connecting piece is drawn, is pressed experimental universal fixturing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170905 |