CN109178340B - Wing body butt joint wallboard for fatigue test and test method thereof - Google Patents
Wing body butt joint wallboard for fatigue test and test method thereof Download PDFInfo
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- CN109178340B CN109178340B CN201810972919.5A CN201810972919A CN109178340B CN 109178340 B CN109178340 B CN 109178340B CN 201810972919 A CN201810972919 A CN 201810972919A CN 109178340 B CN109178340 B CN 109178340B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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Abstract
The application relates to the technical field of aircraft structural design and test verification, in particular to a wing body butt joint wallboard for fatigue test and a test method thereof, wherein the wing body butt joint wallboard for the fatigue test comprises: a clamping plate, a butt strap (3), and a skin (4) and a stringer (5) for connecting the clamping plate and the butt strap (3). The clamping plates comprise a first clamping plate and a second clamping plate, the first clamping plate and the second clamping plate respectively comprise an upper clamping plate and a lower clamping plate, and the lower clamping plate is connected with the upper clamping plate through bolts; the butt joint band plate comprises an upper butt joint band plate and a lower butt joint band plate, and the lower butt joint band plate is connected with the upper butt joint band plate through bolts; the first clamping plate and the second clamping plate are symmetrically arranged at two ends of the butt joint belt plate through the skin and the stringers. The method solves the problems of complex loading condition, high cost, long period and high risk of the full-size structure test of the wing body of the airplane, improves the reliability of the butt joint structure of the wing body, reduces the cost and has great social and economic benefits.
Description
Technical Field
The application belongs to the technical field of airplane structural design and test verification, and particularly relates to a wing body butt joint wallboard for a fatigue test and a test method thereof.
Background
The wing body butt joint structure is a key force transmission channel in an airplane structure, is complex in connection form and load, and has the characteristics of high reliability and long fatigue life in an important connection area of the wing body butt joint structure through means of reasonable structural layout, material selection, exquisite detail design, proper manufacturing process, reliable anti-corrosion design and the like, and fatigue damage is avoided as far as possible in a service period. At present, the design and verification of the structure in China mostly researches the detail force transmission characteristic by combining a full-size structure test with a simulation technology to evaluate the fatigue life and the reliability of the structure. However, the full-size structure test process is complex, the cost is high, and the verification period is long; the simulation analysis has low cost and high speed, but the precision is difficult to meet the requirement.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a wing body butt joint wallboard for a fatigue test and a test method thereof, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a wing body butt-joint panel for fatigue testing, comprising:
the clamping plate comprises a first clamping plate and a second clamping plate, the first clamping plate and the second clamping plate respectively comprise an upper clamping plate and a lower clamping plate, and the lower clamping plate is connected with the upper clamping plate through bolts;
the butt joint band plate comprises an upper butt joint band plate and a lower butt joint band plate, and the lower butt joint band plate is in bolted connection with the upper butt joint band plate;
the first clamping plate and the second clamping plate are symmetrically arranged at two ends of the butt joint belt plate through skins and stringers.
Optionally, the number of the skins is two, one end of one skin is arranged between the upper clamping plate and the lower clamping plate of the first clamping plate, the other end of the one skin is arranged between the upper butt-joint strip plate and the lower butt-joint strip plate of the butt-joint strip plate, one end of the other skin is arranged between the upper clamping plate and the lower clamping plate of the second clamping plate, and the other end of the other skin is arranged between the upper butt-joint strip plate and the lower butt-joint strip plate of the butt-joint strip plate;
the stringer comprises a plurality of T-shaped parts, matched openings are formed in the corresponding ends of the upper clamping plate and the upper butt joint belt plate, one side of the stringer is attached to and fixed with the skin, and the other side of the stringer protrudes out of each opening.
Optionally, the bolt is a high lock bolt.
Optionally, the clamping plate is made of 30CrMnSiA material, the upper butt joint strip plate is a titanium alloy part, and the lower butt joint strip plate, the skin and the stringer are aluminum alloy parts.
Optionally, the length of the butt wall plate of wing body for fatigue test is 1800mm, the width is 510mm, and the maximum thickness is 52.5 mm.
Optionally, the end of the first clamping plate and the end of the second clamping plate far away from the butt-joint belt plate are trapezoidal.
A method of testing a wing body butt-joint panel for fatigue testing, based on the wing body butt-joint panel for fatigue testing as described above, comprising:
the method comprises the following steps: installing a first clamping plate of a wing body butt joint wallboard for fatigue test on an upper hydraulic chuck of a testing machine, and installing a second clamping plate on a lower hydraulic chuck of the testing machine to ensure the verticality and the centering degree of the wing body butt joint wallboard;
step two: processing the pre-applied load spectrum of the butt joint wall plate of the wing body, and inputting the pre-applied load spectrum into a control system according to a required format;
step three: controlling an upper hydraulic chuck and a lower hydraulic chuck of the testing machine through a control system, and carrying out test verification on the wing body butt joint wall plate;
step four: strain data are collected and stored through a data collection system, and the strain data are analyzed.
Optionally, the testing machine has a specification of 100 t.
Optionally, the load spectrum in the second step is a random spectrum, and the maximum load is 800 kN.
Optionally, the strain data in step four includes the applied load and the displacement of the fuselage relative to the wall panel.
The invention has at least the following beneficial technical effects:
the utility model provides a wing body butt joint wallboard for fatigue test, carried out the optimal design to aircraft actual structure, guaranteed through the splint structure that it need not to design other anchor clamps instrument when experimental, both reduced the design cost, greatly reduce experimental installation again, dismantle and inspect required work load, reduce the human cost, this wing body butt joint wallboard form is simple, it is complicated to have solved aircraft wing fuselage full-scale structural test loading condition, with high costs, the cycle length is big with the risk problem, the reliability of wing body butt joint structure has been improved.
Drawings
FIG. 1 is a front view of the body butt wall panel of the present application for fatigue testing;
FIG. 2 is a rear view of the body butt wall panel of the present application for fatigue testing;
FIG. 3 is a schematic view of the upper clamping plate of the butt-jointed wall plate of the wing body for fatigue test according to the present application;
FIG. 4 is a schematic view of the lower clamping plate of the butt-jointed wall plate of the wing body for fatigue test according to the present application;
FIG. 5 is a schematic view of the upper butt strap of the present butt wall panel for a wing body for fatigue testing;
FIG. 6 is a schematic view of the lower butt strap of the present butt wall panel for a wing body for fatigue testing;
FIG. 7 is a front view of the skin of the body butt-jointed panel of the present application for fatigue testing;
FIG. 8 is a side view of the skin of the body butt-jointed panel of the present application for fatigue testing;
FIG. 9 is a schematic view of a stringer according to an embodiment of the present invention for a body butt panel for fatigue testing;
FIG. 10 is a cross-sectional view of FIG. 8;
FIG. 11 is a schematic view of a stringer according to another embodiment of the present butt-jointed panel for wing body for fatigue testing;
FIG. 12 is a schematic view of a stringer according to another embodiment of the present butt-jointed panel for wing body for fatigue testing;
FIG. 13 is a high lock bolt layout of the body butt wall panel of the present application for fatigue testing;
FIG. 14 is a front view of the test machine of the present application for a wing body butt wall panel for fatigue testing;
FIG. 15 is a side view of the test machine of the present application for a wing body butt wall panel for fatigue testing;
wherein:
1-a first splint; 2-a second splint; 3-butt joint of the strip plates; 4-covering; 5-stringer.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application will be described in further detail with reference to fig. 1 to 15.
The application provides a wing body butt joint wallboard for fatigue test includes: plywood, butt strap 3, and skins 4 and stringers 5 for connecting the plywood and butt strap 3.
Specifically, the clamping plates comprise a first clamping plate 1 and a second clamping plate 2, the first clamping plate 1 and the second clamping plate 2 respectively comprise an upper clamping plate and a lower clamping plate, and the lower clamping plate is connected with the upper clamping plate through bolts; the butt joint belt plate 3 comprises an upper butt joint belt plate and a lower butt joint belt plate, and the lower butt joint belt plate is connected with the upper butt joint belt plate through bolts; the first clamping plate 1 and the second clamping plate 2 are symmetrically arranged at two ends of the butt-joint strip plate 3 through a skin 4 and a stringer 5.
In the embodiment, the number of the skins 4 is two, the thickness of the skins is changed in a step shape, one end of one skin 4 is arranged between the upper clamping plate and the lower clamping plate of the first clamping plate 1 and fixed through a bolt, the other end of the one skin 4 is arranged between the upper butt joint strip plate and the lower butt joint strip plate of the butt joint strip plate 3 and fixed through a bolt, one end of the other skin 4 is arranged between the upper clamping plate and the lower clamping plate of the second clamping plate 2 and fixed through a bolt, and the other end of the other skin 4 is arranged between the upper butt joint strip plate and the lower butt joint strip plate of the butt joint strip plate 3 and fixed through a bolt; stringer 5 includes a plurality ofly, is the T type, offers assorted opening through last splint and the corresponding end of last butt joint band plate, 5 one side of stringer and the laminating of covering 4 and pass through the bolt fastening, and the opposite side is outstanding in each opening. In this embodiment, it is preferable that 6 stringers 5 are provided, and 3 stringers 5 are provided on each side to connect each plywood and the butt-jointed strip plate 3, the stringers 5 shown in fig. 11 are provided at the middle position, and the stringers 5 shown in fig. 12 and 13 are provided at the upper and lower sides, respectively.
Advantageously, in this embodiment, the skins 4 and the stringers 5 in the load transfer area and the upper butt-joint band plate, the skins 4, the stringers 5 and the lower butt-joint plate in the butt-joint area are fixed by CFBL1007AP high-locking bolts, the diameters and the lengths of the skins 4, the stringers 5 and the lower butt-joint band plate in the butt-joint area are reasonably arranged along with position changes, the butt-joint area, the load transfer area and the clamping area of the wing body butt-joint wall plate are integrated by reasonably arranging the high-locking bolts, the structural design form is novel, and the test loading boundary condition is simplified.
Advantageously, in this embodiment, the first clamping plate 1 and the second clamping plate 2 are made of 30CrMnSiA, the upper butt-joint strap plate is made of Ti-6Al-4V titanium alloy, the lower butt-joint strap plate is made of 2024-T351 aluminum alloy, the variable-thickness skin 4 is made of 2024HDT-T351 aluminum alloy, and the stringer 5 is made of 2026-T351 aluminum alloy.
Advantageously, in this embodiment, the length of the wing body butt-joint wall plate for the fatigue test is 1800mm, the width is 510mm, and the maximum thickness is 52.5mm, so that the maximum test piece size that can be accommodated by a 100t testing machine is met, a clamp tool does not need to be redesigned during the test, and the design cost and the labor cost are reduced.
Advantageously, in this embodiment, the end of the first clamping plate 1 and the second clamping plate 2 away from the butt joint strip plate 3 is trapezoidal, and the design of the upper clamping plate and the lower clamping plate is convenient for reducing the overall weight of the wallboard structure, and is beneficial to test installation, disassembly and inspection.
Based on the wing body butt joint wallboard for the fatigue test, the application also provides a test method of the wing body butt joint wallboard for the fatigue test.
Before this test was performed, the process of machining the wing body butt wall panel test piece included: considering the reliability factor of the aircraft structure, combining the actual aircraft wing body butt joint structure and simulation analysis to simplify the aircraft wall plate structure, neglecting the sweepback angle and ensuring the transfer ratio of the structure; according to the wing body butt joint wallboard, the sweep angle of an actual structure is ignored, the load transfer ratio of the stringer 5 to the skin 4 is ensured to be 1:1, and the load transfer characteristic of the actual structure is met. The materials are reasonably selected according to the actual butt-joint wall plate structure of the airplane wing body, and the materials are processed into the required structural size and form. Each part is assembled by using a high-locking bolt to form an integral wallboard test piece, the machining and assembling precision is required to be ensured, and the reliability is ensured.
In the method for testing the wing body butt joint wall plate for the fatigue test, the testing system mainly comprises a hydraulic system, a 100t testing machine, a computer control system and a corresponding data monitoring, acquiring and transmitting device.
The application provides a fatigue test's test method of wing body butt joint wallboard, specifically includes:
the method comprises the following steps: a first clamping plate 1 of a wing body butt joint wallboard for fatigue test is arranged on an upper hydraulic chuck of a testing machine, and a second clamping plate 2 is arranged on a lower hydraulic chuck of the testing machine, so that the verticality and the centering degree of the wing body butt joint wallboard are ensured;
step two: processing the pre-applied load spectrum of the butt joint wall plate of the wing body, and inputting the pre-applied load spectrum into a control system according to a required format;
step three: controlling an upper hydraulic chuck and a lower hydraulic chuck of the testing machine through a control system, and carrying out test verification on the wing body butt joint wall plate;
step four: strain data are collected and stored through a data collection system, and the strain data are analyzed.
In this embodiment, the specification of the testing machine is 100t, the load spectrum in the second step is a random spectrum, the maximum load is 800kN, and the strain data in the fourth step includes the applied load and the displacement of the wing body against the wall plate. The load and the displacement are respectively transmitted to the data monitoring and data acquisition device by the force sensor and the displacement sensor through the transmission device, so that the real-time monitoring and acquisition of the load and the displacement are realized, and the data measurement precision is higher.
The wing body butt joint wallboard for the fatigue test has the DFR value of 134MPa through calculation, and is improved by 6% compared with the original structure, namely the reliability of the structure is higher than that of the original structure, and the service life is longer.
The utility model provides a wing body butt joint wallboard for fatigue test, structural design is ingenious, and light in weight, the integrated design of butt joint district and clamping area is convenient for develop the experiment on the testing machine, simplifies wallboard structural test and verifies the flow, reduces the complexity of wing body butt joint wallboard test boundary simulation. The problems of complex loading conditions, high cost, long period and high risk of the full-size structure test of the wing body of the airplane are solved, the reliability of the wing body butt joint structure is improved, the cost is reduced, and great social and economic benefits are achieved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A wing body butt-joint wall plate for fatigue test is characterized by comprising:
the clamping plate comprises a first clamping plate (1) and a second clamping plate (2), the first clamping plate (1) and the second clamping plate (2) both comprise an upper clamping plate and a lower clamping plate, and the lower clamping plate is connected with the upper clamping plate through bolts;
the butt joint belt plate (3) comprises an upper butt joint belt plate and a lower butt joint belt plate, and the lower butt joint belt plate is in bolted connection with the upper butt joint belt plate;
the first clamping plate (1) and the second clamping plate (2) are symmetrically arranged at two ends of the butt joint strip plate (3) through a skin (4) and a stringer (5);
the number of the skins (4) is two, one end of one skin (4) is arranged between an upper clamping plate and a lower clamping plate of the first clamping plate (1), the other end of the other skin is arranged between an upper butt joint belt plate and a lower butt joint belt plate of the butt joint belt plate (3), one end of the other skin (4) is arranged between an upper clamping plate and a lower clamping plate of the second clamping plate (2), and the other end of the other skin is arranged between an upper butt joint belt plate and a lower butt joint belt plate of the butt joint belt plate (3);
the stringer (5) comprises a plurality of T-shaped stringers, matched notches are formed in the corresponding ends of the upper clamping plate and the upper butt joint strip plate, one side of the stringer (5) is attached to and fixed with the skin (4), and the other side of the stringer protrudes out of each notch;
the end, far away from the butt joint belt plate (3), of the first clamping plate (1) and the second clamping plate (2) is trapezoidal.
2. The wing body butt wall plate for fatigue testing of claim 1, wherein the bolt is a high lock bolt.
3. The wing body butt joint panel for fatigue test according to claim 1, wherein the clamping plate is 30CrMnSiA material, the upper butt joint strap plate is a titanium alloy piece, and the lower butt joint strap plate, the skin (4) and the stringer (5) are aluminum alloy pieces.
4. The butt wall plate for a wing body for fatigue test according to claim 1, wherein the butt wall plate for a wing body for fatigue test has a length of 1800mm, a width of 510mm and a maximum thickness of 52.5 mm.
5. A method of testing a butt-jointed wall panel for a wing body for fatigue testing according to any one of claims 1 to 4, comprising:
the method comprises the following steps: a first clamping plate (1) of a wing body butt joint wallboard for fatigue test is arranged on an upper hydraulic chuck of a testing machine, and a second clamping plate (2) is arranged on a lower hydraulic chuck of the testing machine, so that the verticality and the centering degree of the wing body butt joint wallboard are ensured;
step two: processing the pre-applied load spectrum of the butt joint wall plate of the wing body, and inputting the pre-applied load spectrum into a control system according to a required format;
step three: controlling an upper hydraulic chuck and a lower hydraulic chuck of the testing machine through a control system, and carrying out test verification on the wing body butt joint wall plate;
step four: strain data are collected and stored through a data collection system, and the strain data are analyzed.
6. The method of testing a wing body butt wall plate for fatigue testing according to claim 5, wherein the testing machine has a specification of 100 t.
7. The method of claim 5, wherein in step two the load spectrum is a random spectrum with a maximum load of 800 kN.
8. The method of claim 5, wherein the strain data in step four comprises applied loads and displacements of the body butt wall panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810972919.5A CN109178340B (en) | 2018-08-24 | 2018-08-24 | Wing body butt joint wallboard for fatigue test and test method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810972919.5A CN109178340B (en) | 2018-08-24 | 2018-08-24 | Wing body butt joint wallboard for fatigue test and test method thereof |
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| CN109178340A CN109178340A (en) | 2019-01-11 |
| CN109178340B true CN109178340B (en) | 2022-03-29 |
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| CN110704951B (en) * | 2019-09-29 | 2021-10-15 | 中国直升机设计研究所 | Helicopter tail section fatigue test load spectrum compilation method |
| CN114965025B (en) * | 2022-05-13 | 2023-04-14 | 哈尔滨工业大学 | Test fixture for nondestructive compression test of double-layer hollow thin plate |
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| US4540420A (en) * | 1984-07-23 | 1985-09-10 | Wharton E B | Dehumidifier for flexible envelopes |
| CN101561459A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Damage-tolerance testing method for lower wall panel of airplane outboard wing |
| CN205679383U (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft stringer wallboard tension test part |
| CN206648810U (en) * | 2017-03-30 | 2017-11-17 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fuselage stringer banjo fixing butt jointing test fixture |
| CN206920256U (en) * | 2017-04-06 | 2018-01-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of composite material spar docking structure shearing performance test device |
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