CN220525553U - Fatigue test device for large-size wing root connection structure of civil aircraft - Google Patents
Fatigue test device for large-size wing root connection structure of civil aircraft Download PDFInfo
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- CN220525553U CN220525553U CN202321209706.XU CN202321209706U CN220525553U CN 220525553 U CN220525553 U CN 220525553U CN 202321209706 U CN202321209706 U CN 202321209706U CN 220525553 U CN220525553 U CN 220525553U
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 89
- 238000012360 testing method Methods 0.000 claims abstract description 73
- 210000001503 joint Anatomy 0.000 claims description 26
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 18
- 230000008569 process Effects 0.000 abstract description 10
- 238000006073 displacement reaction Methods 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 4
- 238000012795 verification Methods 0.000 abstract description 2
- 238000004088 simulation Methods 0.000 description 5
- 238000001228 spectrum Methods 0.000 description 5
- 238000005452 bending Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010998 test method Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 210000005069 ears Anatomy 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change 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
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The utility model discloses a fatigue test device for a large-size wing root connection structure of a civil aircraft, and belongs to the technical field of aircraft structural design and test verification. The test device comprises: the fatigue test piece comprises a first wing side wall plate and a second wing side wall plate, wherein each wing side wall plate comprises a skin unit and a T-shaped stringer unit, and the skin unit and the T-shaped stringer unit are fixedly connected through an inner butt strap plate and an outer connecting strap plate; two sets of centre gripping bearing structure set up respectively in test piece both ends, and both structures are the same, include: the upper clamping plate, the lower clamping plate, the connecting joint and the supporting gasket are clamped on two sides of the end part of the test piece. The utility model provides a fatigue test device for a large-size wing root connecting structure of a civil aircraft, which effectively improves the transverse shaking and end displacement phenomena of a test piece in the single-axis fatigue test process by providing a clamping and supporting scheme for the fatigue test of the large-size test piece of the civil aircraft wing root connecting structure, and obtains good centering of the fatigue test piece.
Description
Technical Field
The utility model belongs to the technical field of aircraft structural design and test verification, and particularly relates to a fatigue test device for a large-size wing root connection structure of a civil aircraft.
Background
The civil wing root connecting structure is one of main bearing structures of the aircraft, and is complex in loading. Meanwhile, tens of thousands of times of service enable the civil wing root connecting structure to bear the fatigue load effect, and the fatigue performance and the fatigue test method are critical to the safe service and structural design of the aircraft.
In order to ensure that the wing root connecting structure has high reliability and long fatigue life, the detail force transmission characteristics are researched through experiments and numerical simulation technology of full-size structures in China at present, and the fatigue life and reliability of the wing root connecting structure are evaluated. However, the full-size structure test is costly and the test process is complex; the accuracy of numerical simulation analysis techniques is difficult to meet. In addition, the conventional fatigue test is mostly aimed at test piece-level and element-level test pieces, and the test method is less for large-scale detail-level test pieces.
In the prior art, a fatigue test piece with a large-size wallboard butt joint structure is fixed by a hydraulic chuck, and for a test piece with a thicker thickness, the end is inevitably slipped along the loading direction in the fatigue test piece process, so that the loading effect of the fatigue test is affected.
Disclosure of Invention
In order to solve the problems, the utility model provides the fatigue test device for the large-size wing root connecting structure of the civil aircraft, and the clamping and supporting scheme of the fatigue test of the large-size test piece of the wing root connecting structure of the civil aircraft is provided, so that the transverse shaking and end displacement phenomena of the test piece in the single-axis fatigue test process are effectively improved. Specifically, the utility model designs the clamping plate structure and the supporting gasket structure aiming at the large-size fatigue test piece of the civil aircraft wall plate, forms a set of fatigue test device and a loading clamping scheme of the large-size wing root connecting structure of the civil aircraft, solves the problem of applying the fatigue test load of the large-size wall plate of the civil aircraft, and improves the transverse shaking problem of the fatigue test piece in the test process.
According to the technical scheme of the utility model, the fatigue test device for the large-size wing root connecting structure of the civil aircraft is provided, two ends of the fatigue test device for the large-size wing root connecting structure of the civil aircraft are respectively connected with an external test machine, wherein the fatigue test device for the large-size wing root connecting structure of the civil aircraft comprises:
the fatigue test piece comprises a first wing side wall plate and a second wing side wall plate, wherein each wing side wall plate comprises a skin unit and a T-shaped stringer unit, and the first wing side wall plate and the second wing side wall plate are fixedly connected through an inner butt joint band plate and an outer connecting band plate;
two sets of centre gripping bearing structure set up in respectively single reinforced wallboard butt joint structure fatigue test piece two tip, both structures are the same, all include: the device comprises an upper clamping plate, a lower clamping plate, a connecting joint for clamping the upper clamping plate and the lower clamping plate and a supporting gasket arranged between the upper clamping plate, the lower clamping plate and the connecting joint, wherein the upper clamping plate and the lower clamping plate are clamped at two sides of the end part of the fatigue test piece of the butt joint structure of the single reinforced wallboard.
Further, two skin units and two T-shaped stringer units are disposed opposite each other, the T-shaped stringer units being disposed over the skin units.
Further, the T-shaped stringer unit comprises a horizontal portion and a ridge portion perpendicular to the horizontal portion, a gradient transition structure is arranged at the position of a connecting band plate between the clamping support structure and the outer side, a first clamping gap is formed between the ridge portion and the horizontal portion, and the inner side butt joint band plate is clamped in the clamping gaps of the two stringer structures which are oppositely arranged and used for fixedly connecting the first wing side wall plate and the second wing side wall plate.
Further, a plurality of fixing pin holes corresponding to each other are formed in the inner butt-joint band plate, the skin unit, the T-shaped stringer unit and the outer connecting band plate, and a plurality of bolts penetrate through the fixing pin holes for fixing.
Further, the upper clamping plate and the lower clamping plate have the same structure and are all of a variable thickness gradient structure, and the variable thickness gradient structure comprises: a first thickness portion and a second thickness portion, the thickness of the first thickness portion being greater than the thickness of the second thickness portion, and the thickness of the first thickness portion-the thickness of the second thickness portion = the thickness/2 of the single stiffened wall panel butt structure fatigue test piece end.
Further, the first thickness portions of the upper clamping plate and the lower clamping plate are attached to each other, and the end portion of the fatigue test piece of the butt joint structure of the single-reinforcement wall plate is clamped between the second thickness portions of the upper clamping plate and the lower clamping plate.
Further, the first thickness portion is provided with a first through hole.
Further, a plurality of clamping plate connecting pin holes and a second clamping gap are formed in the second thickness portion, and the second clamping gap is clamped on the second side of the ridge portion. A plurality of cleat connecting pins pass through the cleat connecting pin holes.
Further, the connecting joint comprises a testing machine connecting end and an upper lug and a lower lug which are connected with each other, wherein the testing machine connecting end is used for connecting an external testing machine; the upper lug and the lower lug are respectively provided with a second through hole, the upper lug and the lower lug are respectively clamped on the upper clamping plate and the lower clamping plate, and the first through hole and the second through hole are aligned with each other.
Further, the spacing between the upper and lower tabs is slightly greater than the sum of the thicknesses of the first thickness portions of both the upper and lower clamping plates.
Further, a third through hole is formed in the support pad.
Further, the fatigue test device for the civil aircraft large-size wing root connecting structure further comprises two loading shafts which are respectively arranged in the first through hole, the second through hole and the third through hole of the two groups of clamping support structures in a penetrating manner; the diameter of the loading shaft is obtained through simulation of a virtual test, and the strength of the loading shaft meets the test load requirement of 1.5 times.
The utility model has the beneficial effects that:
(1) The utility model provides a clamping plate and loading shaft loading scheme for fatigue test of a large-size test piece of an civil wing root connecting structure, which can be used for avoiding the problem of sliding of an end head along a loading direction when a large-size and large-thickness fatigue test piece is clamped by hydraulic pressure, and obtaining a more reliable loading effect.
(2) The utility model provides a lateral support scheme of an end head of a fatigue test of a large-size test piece of an civil wing root connecting structure, which obtains good centering of the fatigue test piece, simultaneously reduces the distortion phenomenon of test results caused by transverse shaking as much as possible, and effectively improves the transverse shaking and end head displacement phenomena of the test piece in the process of single-axis fatigue test.
Drawings
FIG. 1 is a schematic diagram of an overall structure of a fatigue test of a butt joint structure of a large-size wallboard of an civil wing according to an embodiment of the present utility model;
FIG. 2 is a schematic view of a fatigue test piece of a butt joint structure of a single reinforced wallboard according to an embodiment of the present utility model;
FIG. 3 is a schematic view of an upper/lower clamp plate according to an embodiment of the present utility model;
FIG. 4 is a schematic view of a connector according to an embodiment of the present utility model;
FIG. 5 is a load axis schematic diagram according to an embodiment of the present utility model;
FIG. 6 is a schematic view of a support pad according to an embodiment of the present utility model;
FIG. 7 is a schematic view of a clamp support structure according to an embodiment of the utility model;
fig. 8 is a schematic diagram of misalignment in fatigue test of a large-sized wallboard butt joint structure of an civil wing without using an embodiment of the present utility model.
Detailed Description
Reference will now be made in detail to exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, the same numbers in different drawings refer to the same or similar elements, unless otherwise indicated. The implementations described in the following exemplary examples are not representative of all implementations consistent with the present disclosure. Rather, they are merely examples of apparatus and methods consistent with some aspects of the present disclosure as detailed in the accompanying claims.
The terms first, second and the like in the description and in the claims, are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments of the disclosure described herein may be capable of being practiced otherwise than as specifically illustrated and described.
Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
A plurality, including two or more.
And/or, it should be understood that for the term "and/or" used in this disclosure, it is merely one association relationship describing associated objects, meaning that there may be three relationships. For example, a and/or B may represent: a exists alone, A and B exist together, and B exists alone.
According to the technical scheme of the utility model, the fatigue test device for the large-size wing root connecting structure of the civil aircraft is characterized in that two ends of the fatigue test device for the large-size wing root connecting structure of the civil aircraft are respectively connected with an external test machine, wherein the fatigue test device for the large-size wing root connecting structure of the civil aircraft comprises:
the fatigue test piece comprises a first wing side wall plate and a second wing side wall plate, wherein each wing side wall plate comprises a skin unit and a T-shaped stringer unit, and the first wing side wall plate and the second wing side wall plate are fixedly connected through an inner butt joint band plate and an outer connecting band plate;
two sets of centre gripping bearing structure set up in respectively single reinforced wallboard butt joint structure fatigue test piece two tip, both structures are the same, all include: the device comprises an upper clamping plate, a lower clamping plate, a connecting joint for clamping the upper clamping plate and the lower clamping plate and a supporting gasket arranged between the upper clamping plate, the lower clamping plate and the connecting joint, wherein the upper clamping plate and the lower clamping plate are clamped at two sides of the end part of the fatigue test piece of the butt joint structure of the single reinforced wallboard.
Further, two skin units and two T-shaped stringer units are disposed opposite each other, the T-shaped stringer units being disposed over the skin units.
Further, the T-shaped stringer unit comprises a horizontal portion and a ridge portion perpendicular to the horizontal portion, a gradient transition structure is arranged at the position of a connecting band plate between the clamping support structure and the outer side, a first clamping gap is formed between the ridge portion and the horizontal portion, and the inner side butt joint band plate is clamped in the clamping gaps of the two stringer structures which are oppositely arranged and used for fixedly connecting the first wing side wall plate and the second wing side wall plate.
Further, a plurality of fixing pin holes corresponding to each other are formed in the inner butt-joint band plate, the skin unit, the T-shaped stringer unit and the outer connecting band plate, and a plurality of bolts penetrate through the fixing pin holes for fixing.
Further, the upper clamping plate and the lower clamping plate have the same structure and are all of a variable thickness gradient structure, and the variable thickness gradient structure comprises: a first thickness portion and a second thickness portion, the thickness of the first thickness portion being greater than the thickness of the second thickness portion, and the thickness of the first thickness portion-the thickness of the second thickness portion = the thickness/2 of the single stiffened wall panel butt structure fatigue test piece end.
Further, the first thickness portions of the upper clamping plate and the lower clamping plate are attached to each other, and the end portion of the fatigue test piece of the butt joint structure of the single-reinforcement wall plate is clamped between the second thickness portions of the upper clamping plate and the lower clamping plate.
Further, the first thickness portion is provided with a first through hole.
Further, a plurality of clamping plate connecting pin holes and a second clamping gap are formed in the second thickness portion, and the second clamping gap is clamped on the second side of the ridge portion. A plurality of cleat connecting pins pass through the cleat connecting pin holes.
Further, the connecting joint comprises a testing machine connecting end and an upper lug and a lower lug which are connected with each other, wherein the testing machine connecting end is used for connecting an external testing machine; the upper lug and the lower lug are respectively provided with a second through hole, the upper lug and the lower lug are respectively clamped on the upper clamping plate and the lower clamping plate, and the first through hole and the second through hole are aligned with each other.
Further, the spacing between the upper and lower tabs is slightly greater than the sum of the thicknesses of the first thickness portions of both the upper and lower clamping plates.
Further, a third through hole is formed in the support pad.
Further, the fatigue test device for the civil aircraft large-size wing root connecting structure further comprises two loading shafts which are respectively arranged in the first through hole, the second through hole and the third through hole of the two groups of clamping support structures in a penetrating manner; the diameter of the loading shaft is obtained through simulation of a virtual test, and the strength of the loading shaft meets the test load requirement of 1.5 times.
The fatigue test method for the civil aircraft large-size wing root connection structure according to the technical scheme of the utility model comprises the following steps:
s1: preparing a fatigue test piece of the butt joint structure of the single reinforced wallboard;
s2: the two groups of clamping support structures are respectively arranged at two end parts of the fatigue test piece of the butt joint structure of the single reinforced wallboard;
s3: setting zero of the external testing machine force, resetting displacement, and starting pre-test loading;
s4: starting a formal test and applying a fatigue load spectrum;
s5: when the fatigue test piece of the butt joint structure of the single reinforced wallboard breaks or fatigue cracks are detected, the test is terminated;
s6: after the measurement is finished, test data are recorded, the fatigue test piece of the butt joint structure of the single reinforced wallboard is disassembled, and a test site is arranged.
According to the end lateral support scheme of the fatigue test of the civil wing root connecting structure large-size test piece, the good centering of the fatigue test piece is effectively maintained, and meanwhile, the distortion phenomenon of test results caused by transverse shaking is reduced as much as possible. In the fatigue test, if there is misalignment of the test piece, the test piece is subjected to the tensile load F and also to the bending moment m=f×d (D is the eccentric distance).
Examples
The utility model provides a fatigue test device for a large-size wing root connection structure of a civil aircraft, which comprises: a fatigue test piece 1 with a single reinforced wallboard butt joint structure; an outer wing side wall panel 2; a central wing side wall panel 3; an inner butt-joint band plate 4; the outer side is connected with a band plate 5; an outer wing side upper clamping plate 6; an outer wing side lower clamping plate 7; a center wing upper clamping plate 8; a center wing side lower clamping plate 9; an outboard side cleat attachment pin 10; a center wing side clamp plate connecting pin 11; an outboard connection joint 12; a center wing side connection joint 13; an outboard loading axle 14; a center wing side loading shaft 15; an outboard support pad 16; the central wing side supports the pad 17. The overall structure of the fatigue test device for the large-size wing root connecting structure of the civil aircraft is shown in figure 1.
The single stiffened panel butt structure fatigue test piece 1 is shown in fig. 2 and includes an outboard side and a center side. The test piece consisted of an outer wing sidewall panel 2, a center wing sidewall panel 3, an inboard butt strap 4 and an outboard butt strap 5.
As shown in FIG. 3, the upper clamping plate 6 on the outer wing side is provided with a through hole a with the diameter slightly larger than that of the loading shaft, meanwhile, the thickness has obvious gradient change, one side with the thickness is connected with a testing machine, and the thinner side is clamped on the upper side of the fatigue test piece 1 of the butt joint structure of the single reinforced wallboard through a plurality of clamping plate connecting pins. The difference of the thicknesses of the two sides is half of the thickness of the test piece to be tested. The outer wing lower clamp 7, the center wing upper clamp 8 and the center wing lower clamp 9 are similar.
As shown in fig. 4, the outboard connector 12 has a through hole b having a diameter slightly larger than the loading shaft. The center wing side connection joint 13 is similar thereto. The connecting joints 12 and 13 are connected with the tested piece 1 on one side through the upper clamping plates 6-9, the lower clamping plates 14 and 15 and connected with the testing machine on one side.
The outboard loading shaft 14 is shown in fig. 5, and the center wing loading shaft 15 is similar thereto. The diameter of the shaft is obtained through simulation of a virtual test, and the strength of the shaft meets the test load requirement of 1.5 times.
The outboard support pad 16 is shown in fig. 6 with a hole c of slightly larger diameter than the loading shaft and the center wing support pad 17 is similar thereto. The transverse shaking and end displacement phenomena of the test piece in the single-axis fatigue test process can be effectively improved.
When the test is implemented, the fatigue testing machine is connected with the fatigue testing piece 1 of the butt joint structure of the single reinforced wallboard through two sets of connecting components. The two sets of connecting components are respectively clamped on the outer wing side wall plate and the central wing side wall plate of the fatigue test piece; simultaneously, two sets of coupling assembling are connected respectively in two chucks of fatigue testing machine.
Taking the outboard connection as an example, fig. 7. The outboard connection assembly includes a connection joint 12, a loading shaft 14, a clamping assembly, and a support pad 16. The clamping assembly comprises upper and lower clamping plates 6, 7 and a clamping plate connecting pin 10. Wherein the connection joint 12 has binaural characteristics d and e, respectively. When the fixture such as the connecting joint and the clamping assembly is manufactured, in order to realize assembly and manufacturing tolerance, the distance between the two ears d and e of the connecting joint 12 is slightly larger than the width of the clamping assembly of the fatigue test piece, and a gap exists between the two ears d and e.
In the uniaxial fatigue loading process, the transverse shaking phenomenon of the test piece is caused by the existence of the gap, so that the test piece is subjected to bending moment action and one side of the test piece is pulled and the other side of the test piece is pressed, and finally the fatigue test result deviates from the real test result, as shown in fig. 8, the test piece is subjected to the tensile load F action and also subjected to the bending moment M=F×D (D is the eccentric distance).
In order to solve the problem, support gaskets 16 with different thicknesses are designed and prepared in the connecting assembly, and the support gaskets 16 with proper thicknesses are selected to be respectively placed at the gaps of the outer wing side connecting joint and the clamping assembly and the gaps of the central wing side connecting joint and the same side of the clamping assembly during test, so that the fatigue test piece is kept well to be neutral, and meanwhile, the distortion phenomenon of test results caused by transverse shaking is reduced as much as possible.
The fatigue test can be carried out on a hydraulic servo fatigue testing machine, is suitable for fatigue tests of constant amplitude spectrum, program block spectrum, flying spectrum and the like, and ensures the mounting coaxiality of test pieces during the test.
The test steps are as follows:
1. after the test piece is assembled and clamped, the force of the tester is zeroed, and then the displacement is zeroed;
2. the pre-test loading is started. And unloading to zero step by step according to 10 percent, 20 percent and 30 percent of the test load after the test load is kept for 3 seconds. Loading and unloading twice, checking the state of each strain gauge, and eliminating the connection gap;
3. starting a formal test and applying a fatigue load spectrum;
4. the test is terminated when either of the following occurs:
(1) breaking the test piece, and recording the cycle number as fatigue life;
(2) and if the fatigue crack can be detected, the method of visual inspection by using a magnifying glass is adopted, and the cycle number at the moment is recorded as the fatigue life.
5. After the measurement is finished, test data are recorded, test pieces are disassembled, and a test site is tidied.
The test device and the test method are verified by a laboratory, the test result accords with the expectation, and the effectiveness of the test device and the test method is proved.
From the above description of the embodiments, it will be apparent to those skilled in the art that the above implementation may be implemented by means of software plus necessary general purpose hardware platform, or of course by means of hardware, but in many cases the former is a preferred embodiment. Based on such understanding, the technical solution of the present utility model may be embodied essentially or in a part contributing to the prior art in the form of a software product stored in a storage medium (e.g. ROM/RAM, magnetic disk, optical disk) comprising instructions for causing a terminal (which may be a mobile phone, a computer, a server, an air conditioner, or a network device, etc.) to perform the method according to the embodiments of the present utility model.
The embodiments of the present utility model have been described above with reference to the accompanying drawings, but the present utility model is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present utility model and the scope of the claims, which are to be protected by the present utility model.
Claims (10)
1. The utility model provides a people's machine jumbo size wing root connection structure fatigue test device, outside test machine is connected respectively at people's machine jumbo size wing root connection structure fatigue test device both ends, its characterized in that, people's machine jumbo size wing root connection structure fatigue test device includes:
the fatigue test piece comprises a first wing side wall plate and a second wing side wall plate, wherein each wing side wall plate comprises a skin unit and a T-shaped stringer unit, and the first wing side wall plate and the second wing side wall plate are fixedly connected through an inner butt joint band plate and an outer connecting band plate;
two sets of centre gripping bearing structure set up in respectively single reinforced wallboard butt joint structure fatigue test piece two tip, both structures are the same, all include: the device comprises an upper clamping plate, a lower clamping plate, a connecting joint for clamping the upper clamping plate and the lower clamping plate and a supporting gasket arranged between the upper clamping plate, the lower clamping plate and the connecting joint, wherein the upper clamping plate and the lower clamping plate are clamped at two sides of the end part of the fatigue test piece of the butt joint structure of the single reinforced wallboard.
2. The fatigue test device for the large-size wing root connection structure of civil aircraft according to claim 1, wherein the T-shaped stringer unit comprises a horizontal portion and a ridge portion perpendicular to the horizontal portion, a gradient transition structure is arranged at a position of a clamping support structure and an outer-side connection band plate, a first clamping gap is arranged between a first side and the horizontal portion of the ridge portion, and the inner-side butt-joint band plate is clamped in the clamping gaps of the two stringer structures which are oppositely arranged.
3. The fatigue test device for the large-size wing root connection structure of civil aircraft according to claim 1, wherein a plurality of fixing pin holes corresponding to each other are formed in the inner butt-joint band plate, the skin unit, the T-shaped stringer unit and the outer connecting band plate, and a plurality of bolts pass through the fixing pin holes for fixing.
4. The civil aircraft large-size wing root connection structure fatigue test device according to claim 2, wherein the upper clamping plate and the lower clamping plate are identical in structure and are of variable thickness gradient structure, and the device comprises: a first thickness portion and a second thickness portion, the thickness of the first thickness portion being greater than the thickness of the second thickness portion, and the thickness of the first thickness portion-the thickness of the second thickness portion = the thickness/2 of the single stiffened wall panel butt structure fatigue test piece end,
the first thickness parts of the upper clamping plate and the lower clamping plate are attached to each other, and the end part of the fatigue test piece of the butt joint structure of the single-reinforcement wall plate is clamped between the second thickness parts of the upper clamping plate and the lower clamping plate.
5. The fatigue testing device for large-size wing root connection structure of civil aircraft according to claim 4, wherein the first thickness portion is provided with a first through hole.
6. The fatigue testing device for the large-size wing root connection structure of civil aircraft according to claim 4, wherein the second thickness portion is provided with a plurality of clamping plate connection pin holes and a second clamping slit, and the second clamping slit is clamped on the second side of the ridge portion.
7. The fatigue test device for the large-size wing root connection structure of civil aircraft according to claim 5, wherein the connection joint comprises a tester connection end and an upper lug and a lower lug which are connected with each other, and the tester connection end is used for connecting an external tester; the upper lug and the lower lug are respectively provided with a second through hole, the upper lug and the lower lug are respectively clamped on the upper clamping plate and the lower clamping plate, and the first through hole and the second through hole are aligned with each other.
8. The civil aircraft large-size wing root connecting structure fatigue test device according to claim 7, wherein a distance between the upper ear piece and the lower ear piece is slightly larger than a sum of thicknesses of the first thickness portions of the upper and lower clamping plates.
9. The fatigue testing device for the large-size wing root connection structure of civil aircraft according to claim 7, wherein the support pad is provided with a third through hole.
10. The fatigue testing device for the large-size wing root connection structure of the civil aircraft according to claim 9, wherein the fatigue testing device for the large-size wing root connection structure of the civil aircraft further comprises two loading shafts respectively penetrating through the first through hole, the second through hole and the third through hole of the two groups of clamping support structures; the strength of the loading shaft meets the test load requirement of 1.5 times.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321209706.XU CN220525553U (en) | 2023-05-18 | 2023-05-18 | Fatigue test device for large-size wing root connection structure of civil aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321209706.XU CN220525553U (en) | 2023-05-18 | 2023-05-18 | Fatigue test device for large-size wing root connection structure of civil aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220525553U true CN220525553U (en) | 2024-02-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321209706.XU Active CN220525553U (en) | 2023-05-18 | 2023-05-18 | Fatigue test device for large-size wing root connection structure of civil aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220525553U (en) |
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2023
- 2023-05-18 CN CN202321209706.XU patent/CN220525553U/en active Active
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