CN217786529U - Civil aircraft wing root jumbo size wallboard butt joint structure test device - Google Patents
Civil aircraft wing root jumbo size wallboard butt joint structure test device Download PDFInfo
- Publication number
- CN217786529U CN217786529U CN202221938218.8U CN202221938218U CN217786529U CN 217786529 U CN217786529 U CN 217786529U CN 202221938218 U CN202221938218 U CN 202221938218U CN 217786529 U CN217786529 U CN 217786529U
- Authority
- CN
- China
- Prior art keywords
- wall plate
- butt joint
- clamping
- joint structure
- test device
- 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.)
- Active
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application discloses civil aircraft wing root jumbo size wallboard butt joint structure test device, test device includes: the test piece, support component and two coupling assembling. The test piece had an outer wing sidewall panel and a central wing sidewall panel. Two coupling assembling centre gripping respectively in the outer wing lateral wall board and the central wing lateral wall board of testpieces, two coupling assembling connects respectively in two chucks of testing machine. The supporting component is supported on any one of the connecting components so as to level two of the connecting components. The application of the test device has the advantages that the supporting parts are added, the connecting assemblies on the two sides can be leveled, the influence of gaps and assembly errors on tests is reduced, and the centering performance of loading of large-size test pieces is guaranteed. The stress state simulation device solves the problem that the stress distribution is uneven due to non-centering in the test process of the butt joint structure of the large-size wall plate, and can simulate the stress state of the butt joint structure of the large-size wall plate of the wing root more accurately.
Description
Technical Field
The utility model relates to an aircraft wing root jumbo size wallboard butt-joint structural test technical field especially relates to a civil aircraft wing root jumbo size wallboard butt-joint structural test device.
Background
At present, a large number of complex composite material reinforced wall plate butt joint structures exist in the wing root connecting area of advanced civil aircraft wings, the structures are main bearing structures of the aircraft, and the connecting relation is complex. Under the action of flight load, the wing root key connection area of the wing is under the action of tensile load, and in order to verify the bearing performance of the large-size wall plate butt joint structure of the wing root key connection area and a related numerical analysis method, experimental verification research needs to be carried out.
During testing, the testing machine is typically connected to the test piece by a connection assembly. However, for a large-size test piece, the phenomenon of uneven stress distribution caused by unreasonable clamping and loading schemes is easy to occur; meanwhile, the connecting assembly is difficult to avoid hole site errors, assembly errors and the like, the test piece cannot be ensured to be in a correct tension state, and the centering performance of the loading of the test piece of the butt joint structure of the large-size wing root wallboard cannot be ensured, so that the test data is not accurate enough.
SUMMERY OF THE UTILITY MODEL
The utility model provides a civil aircraft wing root jumbo size wallboard butt joint structure test device has solved the uneven phenomenon of centering and stress distribution among the jumbo size wallboard butt joint structure test process, can simulate wing root jumbo size wallboard butt joint structure stress state more accurately.
In order to realize the purpose of the utility model, the application provides the following technical scheme:
the application provides a civil aircraft wing root jumbo size wallboard butt joint structure test device includes:
a trial having an outer wing sidewall panel and a central wing sidewall panel;
the two connecting assemblies are respectively clamped on an outer wing side wall plate and a central wing side wall plate of the test piece and are respectively connected with two chucks of the testing machine;
a support member supported from either of the connection assemblies to level both of the connection assemblies.
Optionally, the connecting assembly comprises a clamping assembly and a clamping joint, the clamping assembly is clamped on an outer wing side wall plate or a central wing side wall plate of the test piece, and the clamping joint is hinged to the clamping assembly and a chuck of the testing machine respectively;
the supporting part is supported on any one clamping joint.
Optionally, the clamping joint has a supporting mating surface perpendicular to the test piece;
the support component is supported on the support mating surface.
Optionally, a support matching groove is arranged on the support matching surface;
the end of the support member extends into the support mating groove.
Optionally, the civil aircraft wing root large-size wall plate butt joint structure test device comprises two support parts, wherein the two support parts are respectively connected to the support matching surfaces of the two clamping connectors;
the support member has an extended state and a retracted state.
Optionally, the support member is a single piece, and the support member is selectively supported on the support mating surface of any of the clamping connectors.
Optionally, the test device for the civil aircraft wing root large-size wall plate butt joint structure further comprises a base frame, the supporting component is connected to the base frame, and the supporting component can move and be positioned along the base frame.
Optionally, the support member has a main body portion and a telescopic portion;
the telescopic part is movably connected with the main body part, the telescopic part can stretch out and draw back and be fixed along the main body part, and the end part of the telescopic part is propped against the connecting assembly.
Optionally, the clamping assembly includes a transition joint and a clamping plate group, the clamping plate group is clamped at two sides of the outer wing side wall plate or the central wing side wall plate in the thickness direction, one end of the transition joint is provided with a plurality of connecting holes, the other end of the transition joint is provided with a loading hole, each connecting hole is located on the same straight line, the loading hole is located on a perpendicular bisector of a line segment formed by connecting the connecting lines of the connecting holes, each connecting hole is connected to the clamping plate group through a transition joint connecting pin, and the loading hole is connected to the clamping joint through a loading shaft.
Through adopting above-mentioned technical scheme for this application has following beneficial effect:
the application of the test device has the advantages that the supporting parts are added, the connecting assemblies on the two sides can be leveled, the influence of gaps and assembly errors on tests is reduced, and the centering performance of loading of large-size test pieces is guaranteed. The stress state simulation device solves the problem that the stress distribution is uneven due to non-centering in the test process of the butt joint structure of the large-size wall plate, and can simulate the stress state of the butt joint structure of the large-size wall plate of the wing root more accurately.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention without limitation. It is obvious that the drawings in the following description are only some embodiments, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic perspective view of a test piece of a civil aircraft wing root large-size wall plate butt joint structure test device provided in an embodiment of the present application;
fig. 2 is another perspective view of a test piece of the civil aircraft wing root large-size wall plate butt joint structure test device provided in the embodiment of the present application;
fig. 3 is a schematic view of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in an embodiment of the present application in a testing state;
fig. 4 is a front view of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in the embodiment of the present application in a testing state;
fig. 5 is a top view of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in an embodiment of the present application in a testing state;
FIG. 6 is a schematic structural diagram of a first side clamping plate of the test device for the butt joint structure of the large-size wall plates of the civil aircraft wing root according to the embodiment of the application;
fig. 7 is a schematic structural diagram of a transition joint of a civil aircraft wing root large-size wall plate butt joint structure test device provided in the embodiment of the present application;
fig. 8 is a schematic structural diagram of a clamping joint of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in an embodiment of the present application;
fig. 9 is a schematic structural diagram of a transition joint connecting pin of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in the embodiment of the present application;
fig. 10 is a schematic structural diagram of a supporting component of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in an embodiment of the present application;
fig. 11 is an exploded view of a local structure of a civil aircraft wing root large-size wall plate butt joint structure testing device provided in an embodiment of the present application;
fig. 12 is a schematic view of a test load application manner of a civil aircraft wing root large-size wall plate butt joint structure test device provided in the embodiment of the present application;
fig. 13 is a schematic view of an off-axis stress state of a test piece of the test device for the butt joint structure of the large-size wall plate of the civil aircraft wing root provided in the embodiment of the present application.
In the figure: 1. a test piece; 11. an outer wing sidewall panel; 12. a center wing sidewall panel; 13. an inner T-shaped butt strap plate; 14. the outer side is connected with a belt plate; 2. clamping the joint; 21. a support mating surface; 3. a loading shaft; 4. a transition joint; 41. a loading hole; 42. connecting holes; 5. a transition joint connecting pin; 6. a first side clamping plate; 7. a second side clamping plate; 8. a splint connecting pin; 9. a chuck of the testing machine; 10. a support member; a. a first strain measuring point; b. a second strain measurement point.
Detailed Description
To make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the attached drawings in the embodiments of the present invention are combined below to clearly and completely describe the technical solution in the embodiments, and the following embodiments are used to illustrate the present invention, but do not limit the scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as a specific case by those skilled in the art.
Example one
Referring to fig. 1 to 13, an embodiment of the present application provides a testing apparatus for a butt joint structure of a large-sized wall plate of a civil aircraft wing root, including: test piece 1, support member 10 and two connection assemblies. Test piece 1 has an outer wing side panel 11 and a central wing side panel 12. Two connecting assemblies are respectively clamped on an outer wing side wall plate 11 and a central wing side wall plate 12 of the test piece, and the two connecting assemblies are respectively connected to two chucks 9 of the testing machine. The support member 10 is supported to either of the connection assemblies to level both of the connection assemblies.
In the test process, the two ends of the test piece 1 need to be clamped by the two connecting components respectively. However, the connecting assembly is inevitable to have hole site errors, assembly errors and the like, and cannot ensure that the test piece 1 is in a horizontal tension state and cannot ensure the loading centering performance of the test piece 1 of the large-size wall plate butt joint structure. In view of the above, in the embodiment of the application, it is designed that the supporting component 10 can be supported on the connecting component with a low position, and the two connecting components are leveled, so that the influence of a gap and an assembly error is reduced, the centering performance of the loading of the large-size wall plate butt joint structure test piece 1 is ensured, and the test accuracy is improved.
Referring to fig. 1 and 2, in the embodiment of the present application, the test piece 1 may be selected to have a large-sized structure. Trial 1 may be comprised of inboard T-butt strap 13, outboard side panel 11 (including skin and stringers), center wing side panel 12 (including skin and stringers), outboard tie strap 14 and tie bolts. The test piece 1 is a large-size wing wall plate butt joint structure, has the characteristics of high ultimate load, large size and the like, belongs to a composite material detail part level large-scale test, can accurately verify the bearing capacity of the large-size wing wall plate butt joint structure of a wing root connecting area, and provides important test data support for design and model selection of the wing root butt joint structure and a finite element analysis method.
In a possible embodiment, the connection assembly comprises a clamping assembly clamped to the outer or central wing panel 11 or 12 of the test piece 1 and a clamping sub 2 hinged to the clamping assembly and to the collet 9 of the testing machine, respectively. The support member 10 is supported on any one of the clamp fittings 2.
In this embodiment, the clamping connector 2 is directly supported on the chuck 9 of the testing machine, and the supporting part 10 directly applies supporting force to the clamping connector 2 for the end position of the connecting component, so that the whole connecting component is more favorably leveled. So that the components of the two connecting assemblies are on the same horizontal line.
In the experimental process, the test piece 1 adopts a horizontal loading scheme. The test piece 1 had a long plate shape. The test piece 1 is fixed transversely, and the plane of the test piece 1 is vertical to the horizontal plane. Chuck 9 of testing machine has last support arm and lower support arm, the centre gripping connects 2 to have along longitudinal extension's perforating hole, and the centre gripping connects 2 parts to stretch into between last support arm and the lower support arm, the pivot run through support arm, lower support arm and the perforating hole sets up. The supporting part 10 is parallel to the rotating shaft and abuts against the clamping joint 2, the height of the clamping joint 2 is adjusted, the rotating shaft extends vertically, a certain guiding effect is achieved, and the supporting part 10 can effectively lift the height of the low connecting assembly.
In a possible embodiment, both clamping connectors 2 have a support mating surface 21 perpendicular to the test piece 1, and the support part 10 is supported on the support mating surface 21. In this embodiment, the support mating surface 21 is the lower surface side of the clamp connector 2 in the test state, and can effectively lift the clamp connector 2 to a certain height.
In a possible embodiment, a support fitting groove is provided on the support fitting surface 21, and the end of the support member 10 extends into the support fitting groove. The support matching groove is formed in the support matching surface 21, so that the top of the support part 10 is limited in the support matching groove, and the support part 10 is prevented from changing positions in the experiment process. And the supporting position of the supporting component 10 can be well defined by arranging the supporting matching groove on the supporting matching surface 21, so that the test accuracy is improved, and the supporting component 10 can be conveniently assembled in place as soon as possible.
In a possible embodiment, the civil aircraft wing root large-size wall plate butt joint structure test device can comprise two support parts 10, and the two support parts 10 are respectively connected to the support matching surfaces 21 of the two clamping connectors 2. The support member 10 has an extended state and a retracted state.
In this embodiment, the support member 10 is installed on the connection assembly on both sides, the support member 10 can be perpendicular to the support mating surface 21, the support member 10 can be stretched and positioned, and the experimenter can adjust the support member 10 to stretch and contract in any length and fix. In the actual test, two support members 10 are used alternatively, and the support member 10 on the lower side connecting assembly elongates to support the corresponding clamping fitting 2. The support member 10 on the side attachment assembly positioned high remains retracted.
The end of the support member 10 may be fixed to the clamp fitting 2. The clamping connector 2 can be provided with a connecting seat, the end part of the supporting component 10 is connected onto the connecting seat, and the supporting component 10 can be detachably arranged, so that the replacement and maintenance are convenient.
In another possible embodiment, the support member 10 is a single piece, and the support member 10 is selectively supported on the support mating surface 21 of any one of the clamping terminals 2. In this embodiment, the support member 10 is a separate fitting structure, which facilitates separate storage. The experimenter can manually place the support member 10 in the retracted state at the target position, and then control the support member 10 to extend so that the top end abuts against the support matching surface 21. The clamping joint 2 can apply downward force to the telescopic component at the same time, so that the supporting component 10 keeps a vertical state and is not easy to shake and skew.
In a possible embodiment, the civil aircraft wing root large-size wall plate butt joint structure test device further comprises a base frame, wherein the supporting component 10 is connected to the base frame, and the supporting component 10 can move and be positioned along the base frame.
In this embodiment, the chassis can be installed on the base platform, and the chassis is located test piece 1 directly below, and the chassis extends the setting parallel to test piece 1. The position at which the support member 10 is supported, such as on the clamp fitting 2 of different connection assemblies, or on different positions of the support mating surface 21, can be adjusted by sliding the support member 10.
The chassis may comprise a slide track to which the support member 10 may be slidably connected, the support member 10 moving the position of the adjustable support along the slide track. And a plurality of threaded holes can be formed in the sliding rail along the length direction, after the position of the supporting part 10 is adjusted, the sliding rail is connected to the corresponding threaded hole in the position of the supporting part 10 through a bolt in a threaded manner, and a screwed bolt can abut against the supporting part 10 to fix the position of the supporting part 10. Alternatively, the support member 10 may not be fixed by bolts, and may be held in place by pressure applied by the connecting assembly.
The underframe may also include a screw mechanism, the screw mechanism includes a screw and a guide rod, the support member 10 may be in threaded connection with the screw, and the guide rod is sleeved with the support member 10 through a through hole, and the position of the support member 10 is adjustable by driving the screw to rotate.
In one possible embodiment, the support member 10 has a main body portion and a telescoping portion. The telescopic part is movably connected with the main body part, the telescopic part can stretch out and draw back and be fixed along the main body part, and the end part of the telescopic part is propped against the connecting assembly.
The support member 10 may be a telescopic cylinder, a linear motor or other telescopic mechanism. When the support member 10 is a telescopic cylinder, the body of the telescopic cylinder is the main body, and the telescopic rod of the telescopic cylinder is the telescopic part.
In one possible embodiment, shown in figure 11, the clamping assembly comprises a transition joint 4 and clamping plate groups 6, 7 which are clamped on both sides in the thickness direction of the outer or central wing side panel 11 or 12 and to which the test pieces 1 are connected by a plurality of clamping plate connecting pins 8. Referring to fig. 7, one end of the transition joint 4 is provided with a plurality of connecting holes 42, the other end of the transition joint is provided with a loading hole 41, the connecting holes 42 are located on the same straight line, the loading hole 41 is located on a perpendicular bisector of a line segment formed by connecting the connecting holes 42, the connecting holes 42 are respectively connected to the clamping plate group through transition joint connecting pins 5, and the loading hole 41 is connected to the clamping joint 2 through a loading shaft 3.
In this embodiment, the extending direction of the loading hole 41 is perpendicular to the extending direction of the through hole. The number of the coupling holes 42 may be three or determined according to the actual size of the test piece.
During test implementation, the test piece 1 is large in size, in order to reduce the phenomenon that the test piece 1 is unevenly loaded due to loading as much as possible, the transition joint 4 structure is designed, one end, close to the test piece 1, of the transition joint 4 is connected to the clamping plate group through a plurality of transition joint connecting pins 5, the other end of the transition joint 4 is connected to the clamping joint 2 through the loading shaft 3, force output by the loading shaft 3 is evenly dispersed to different positions of the test piece 1, the phenomenon that stress and strain distribution inside the test piece is uneven due to concentrated loading force is reduced, and even loading of the test piece 1 with the large-size wallboard butt joint structure is achieved.
Example two
The second embodiment of the application provides a test method of the civil aircraft wing root large-size wall plate butt joint structure test device in the first embodiment of the application, which comprises the steps of determining the eccentric distance D of the test device, supporting the supporting component 10 on one side of the connecting component with a low position, and adjusting the height of the supporting component 10 to enable the supporting component 10 to jack the corresponding connecting component to the height corresponding to the eccentric distance D.
Alternatively, the eccentricity distance D is estimated by the following formula:
wherein E is the modulus of elasticity, I z Is the moment of inertia, F is the pre-experimental loading force, ε test1 Is a pre-test value of a first strain point a test2 A pre-test value, y, for a second strain point b 1 Is the distance from the first strain measuring point a to the neutral axis of the side surface of the test piece, y 2 The distance from the second strain measuring point b to the neutral axis of the side surface of the test piece. The first strain measuring points a and the second strain measuring points b are symmetrically distributed on two sides of the test piece 1 along the width direction.
In a specific structure, the clamping plate group is provided with a first side clamping plate 6 and a second side clamping plate 7, the first side clamping plate 6 and the second side clamping plate 7 are positioned at two sides of an outer wing side wall plate 11 or a central wing side wall plate 12, and a plurality of fixing holes are arranged on the first side clamping plate 6 and the second side clamping plate 7 so as to be connected with corresponding parts of a large-size test piece 1 through clamping plate connecting pins 8. The transition joint 4 is provided with a clamping groove, the end part of the clamping plate group is inserted into the clamping groove, each connecting hole 42 penetrates through the transition joint 4, and a plurality of transition joint connecting pins 5 penetrate through the corresponding connecting holes 42 and the clamping plate group. The loading shaft 3 of the transition joint 4 is connected to the clamping joint 2. In the test process, the position of the movable supporting part 10 can be adjusted according to the test condition so as to enable the movable supporting part to be abutted against the clamping joint 2 on the lower side.
The large-sized wall plate butt joint structural test piece 1 was subjected to mechanical load application in the loading manner shown in fig. 12. Due to the machining tolerance and the assembly tolerance of the large-size wallboard butt joint structure test piece 1, the transition joint 4, the transition joint connecting pin 5, the loading shaft 3 and the like, the situation that the central wing side loading shaft 3 and the outer wing side loading shaft 3 are not in the same horizontal line exists in the test piece 1 adopting horizontal loading. In order to keep the test piece 1 in a horizontal load state during the test, the lower side of the test piece 1 is jacked up by using the supporting member 10, as shown in fig. 12. At the same time, in order to make the stress of the test piece 1 more uniform, the test load F jz Decomposition to F by transition joint 4 x1 ，F x2 ，F x3 The calculation formula is as follows:
meanwhile, as the loading shafts 3 on the central wing side and the outer wing side are not on the same horizontal line, the material is stretched by an eccentric shaft, and the stress state can be simplified as shown in fig. 13. At the symmetrical first strain measuring point a and second strain measuring point b, the strain thereof is the strain epsilon caused by the loading force F F And strain epsilon caused by bending moment M = F.D (D is eccentric distance) caused by eccentricity M The two parts are respectively as follows:
wherein A is the area of the longitudinal section corresponding to the first strain measuring point a to the second strain measuring point b, E is the elastic modulus, I z And y is the distance from the strain measuring point to the neutral axis of the side surface of the test piece.
Strain at the first strain measuring point a is epsilon 1 ＝ε F +ε M Strain epsilon at the second strain point b 2 ＝ε F -ε M . The strain test results epsilon of the first strain test point a and the second strain test point b can be obtained through pre-tests test1 And ε test2 Substituting the above equation can estimate the eccentricity D as follows:
from the above analysis, it can be seen that the supporting member 10 is used to balance the hole site error and the assembly error of the loading shaft 3, the transition joint connecting pin 5, and each connecting hole 42 of the transition joint, and the like, and ensure the horizontal tension state of the test piece 1, with the jacking height D of the supporting member 10.
In order to ensure the test safety, the set of test device can bear 2-3 times of test estimated breaking load through strength check, in order to ensure the strength of the connecting pin of the transition joint and the loading shaft, alloy steel is adopted to manufacture the loading shaft 3, super-strong steel is adopted to manufacture the connecting pin of the transition joint, and a strain gage is pasted in the examination area of the test piece 1 to record test data. In order to obtain more accurate test data, the strain gauge is pasted at a bypass load position where the large-size wall plate butt joint structure is connected with the force transmission of the fastener.
The following exemplary provides a static test sequence for a butt structure of a large-sized test piece 1:
(1) Pre-testing, namely loading the test piece 1 to 30% of damage load step by step according to the 5% of damage load step difference, unloading the test piece step by step according to the 10% of damage load step difference, and inspecting the stress condition of the test piece 1 and the operation conditions of a clamp, loading equipment and a measuring instrument;
(2) Loading to 65% failure load according to the loading grade difference of 5% failure load;
(3) Loading to 67% of the destructive load according to the 2% of the destructive load grade difference, and keeping the load until the data recording is completed;
(4) Loading to 70% of the destruction load according to the 3% of the destruction load level difference, and keeping the load until the data recording is completed;
(5) After the breaking load is loaded to 100% breaking load according to the 5% breaking load grade difference, the load is preserved for 3 seconds until the data recording is finished;
(6) If the data are not damaged, continuously increasing the damage load according to 5% of each stage, and keeping the load until the data record is finished until the damage is caused; when the test piece 1 was loaded to 120% failure load, the loading was stopped without failure.
The set of test device passes laboratory verification, obtains ideal test results and proves the effectiveness of the test device.
The preferred embodiments of the present application disclosed above are intended only to aid in the explanation of the application. The preferred embodiments are not exhaustive and do not limit the application to the precise embodiments described. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the application and the practical application, to thereby enable others skilled in the art to best understand and utilize the application. The application is limited only by the claims and their full scope and equivalents.
Claims (9)
1. The utility model provides a civil aircraft wing root jumbo size wallboard butt joint structure test device which characterized in that includes:
a trial having an outer wing sidewall panel and a central wing sidewall panel;
the two connecting assemblies are respectively clamped on an outer wing side wall plate and a central wing side wall plate of the test piece and are respectively connected with two chucks of the testing machine;
a support member supported from either of the connection assemblies to level both of the connection assemblies.
2. The civil aircraft wing root large-size wall plate butt joint structure test device as claimed in claim 1, wherein the connecting assembly comprises a clamping assembly and a clamping joint, the clamping assembly is clamped on the outer wing side wall plate or the central wing side wall plate of the test piece, and the clamping joint is hinged to the clamping assembly and a chuck of the testing machine respectively;
the support member is supported on any one of the clamping joints.
3. The civil aircraft wing root large-size wall plate butt joint structure test device of claim 2, wherein the clamping joint is provided with a supporting matching surface perpendicular to the test piece;
the support component is supported on the support mating surface.
4. The civil aircraft wing root large-size wall plate butt joint structure test device of claim 3, wherein a support matching groove is formed on the support matching surface;
the end of the support member extends into the support mating groove.
5. The civil aircraft wing root large-size wall plate butt joint structure test device is characterized by comprising two support parts, wherein the two support parts are respectively connected to support matching surfaces of two clamping connectors;
the support member has an extended state and a retracted state.
6. The civil aircraft wing root large-size wall plate butt joint structure test device of claim 3, wherein the supporting component is a single piece and can be selectively supported on the supporting matching surface of any clamping connector.
7. The civil aircraft wing root large-size wall plate butt joint structure test device of claim 1, further comprising a base frame, wherein the support component is connected to the base frame, and the support component can move and be positioned along the base frame.
8. The civil aircraft wing root large-size wall plate butt joint structure test device of claim 1, wherein the support member is provided with a main body part and a telescopic part;
the telescopic part is movably connected with the main body part, the telescopic part can stretch out and draw back and be fixed along the main body part, and the end part of the telescopic part is propped against the connecting assembly.
9. The civil aircraft wing root large-size wall plate butt joint structure test device according to claim 2, wherein the clamping assembly comprises a transition joint and a clamping plate group, the clamping plate group is clamped at two sides of the outer wing side wall plate or the central wing side wall plate in the thickness direction, one end of the transition joint is provided with a plurality of connecting holes, the other end of the transition joint is provided with a loading hole, the connecting holes are located on the same straight line, the loading hole is located on a perpendicular bisector of a line segment formed by the connecting lines of the connecting holes, the connecting holes are respectively connected to the clamping plate group through transition joint connecting pins, and the loading hole is connected to the clamping joint through the loading shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221938218.8U CN217786529U (en) | 2022-07-25 | 2022-07-25 | Civil aircraft wing root jumbo size wallboard butt joint structure test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221938218.8U CN217786529U (en) | 2022-07-25 | 2022-07-25 | Civil aircraft wing root jumbo size wallboard butt joint structure test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217786529U true CN217786529U (en) | 2022-11-11 |
Family
ID=83941594
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221938218.8U Active CN217786529U (en) | 2022-07-25 | 2022-07-25 | Civil aircraft wing root jumbo size wallboard butt joint structure test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217786529U (en) |
-
2022
- 2022-07-25 CN CN202221938218.8U patent/CN217786529U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102288483B (en) | Supporting clamp for compression stabilization experiment of reinforced wallboard and supporting coefficient testing method for end socket | |
| US8857265B2 (en) | System and method for aligning a test article with a load | |
| CN111579361A (en) | Test fixture and method for three-point bending and four-point bending of rock | |
| US6880409B2 (en) | Curved panel shear test apparatus | |
| CN110726636B (en) | Four-axis centering adjustment system and method for biaxial tensile testing machine | |
| CN115060484A (en) | Testing device and testing method for civil aircraft wing root large-size wall plate butt joint structure | |
| CN113335560B (en) | Complex load box section or barrel section test device and method | |
| CN210108832U (en) | A novel direct tensile test device for concrete sample | |
| CN217786529U (en) | Civil aircraft wing root jumbo size wallboard butt joint structure test device | |
| CN210269445U (en) | Multidimensional loading comprehensive test system | |
| CN111965049A (en) | Device and method for testing shearing performance of honeycomb structure in tensile loading mode | |
| CN219369435U (en) | Hydraulic asphalt concrete trabecula bending creep test equipment | |
| CN114646450B (en) | Balance loading device with double fixed supporting parts | |
| CN113340737A (en) | Rigidity test equipment suitable for different structural members and test method thereof | |
| CN112629813B (en) | Wind-tunnel balance load calibration loading head | |
| CN210616260U (en) | Fatigue test fixture for typical angle-shaped connecting piece of bulkhead | |
| CN113670812A (en) | Loading device for researching bonding performance of FRP cloth and concrete interface | |
| CN112903475A (en) | Device and method for testing bending and twisting strength of I-shaped stringer test piece | |
| CN218567091U (en) | Shaft concrete temperature stress testing machine | |
| CN219434502U (en) | Wood structure tooth connection test device | |
| CN215727313U (en) | Tensile mechanical property testing device for metal foil plate | |
| CN111665072B (en) | Bidirectional movable bridge deck static load test device | |
| CN110658066B (en) | Axial compression test device for cross beam structure | |
| US11513045B2 (en) | Tension testing apparatus | |
| CN108693110B (en) | Slippage testing device and FRP sheet and concrete bonding test system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |