Clamping plate structure for airplane airfoil test loading
By using an upper clamping plate, a lower clamping plate, and a lever structure combined with a preload loading block in the aircraft wing surface test loading, the precise application and stability of the preload were achieved, solving the problems of inaccurate and volatile preload in the existing technology and ensuring the stability of the test process.
Patent Information
- Application Number
- CN202520276371.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-20
- Publication Date
- 2026-02-27
- Estimated Expiration
- 2035-02-20
Smart Images
Figure CN223955273U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to structural mechanics performance test loading device field especially an aircraft wing surface test loading's clamping plate structure. BACKGROUND
[0002] At present, in the aircraft wing surface structure static force test scheme, the loading mode that adopts has adhesive tape - lever, pull - pressure pad - lever, vacuum chuck, air bag and clamping plate etc. mode, test loading when, wing surface structure root carries out restraint, carries out test load loading in the outer wing section. Clamping plate loading mode belongs to hard type loading mode, can exert bidirectional load, simultaneously uses clamping plate loading, most wing surfaces are not covered, facilitate damage inspection. In addition to test load, the upper and lower clamping plates exert pre - tightening force to the wing surface, and the wing surface is subjected to compression load, especially for composite wing surface, can effectively avoid some other loading modes to cause the abnormal situation such as composite laminate delamination, debonding caused by pulling load. At present, the exertion of pre - tightening force is mainly through the connecting bolt between the upper clamping plate and the lower clamping plate to exert, and the pre - tightening force value is inaccurate, and the pre - tightening force can change greatly in the test process, which affects the stability of the test process.
[0003] Therefore, it is urgent to provide a clamping plate structure for aircraft wing surface test loading. UTILITY MODEL CONTENT
[0004] In order to solve the above problems, the utility model technical scheme provides a clamping plate structure for wing surface test loading, which can realize accurate application of wing surface structure pre-tightening force, and the pre-tightening force size changes linearly with the test load.
[0005] According to the first aspect of the utility model technical scheme, a clamping plate structure for aircraft wing surface test loading is provided, comprising: an upper clamping plate, a lower clamping plate, a front connecting plate, a rear connecting plate, a front lever, a rear lever, a front pre-tightening force loading block, a rear pre-tightening force loading block, a front positioning connecting piece, a rear positioning connecting piece, a clamping plate front connecting piece, a clamping plate rear connecting piece, a front lever connecting piece, a rear lever connecting piece, a front pre-tightening force loading block positioning pin and a rear pre-tightening force loading block positioning pin.
[0006] The inner surface of the upper clamping plate is in contact with one side of the wing surface, and the inner surface of the lower clamping plate is in contact with the other side of the wing surface.
[0007] The upper clamping plate and the lower clamping plate are fixed through the front positioning connecting piece and the rear positioning connecting piece.
[0008] The front connecting plate and the rear connecting plate are respectively arranged on both sides of the upper clamping plate and the lower clamping plate and are fixed through the clamping plate front connecting piece and the clamping plate rear connecting piece.
[0009] The front lever and the rear lever are arranged above the upper clamping plate or below the lower clamping plate and are hinged with the front connecting plate and the rear connecting plate through the front lever connecting piece and the rear lever connecting piece respectively.
[0010] The front pre-tightening force loading block and the rear pre-tightening force loading block are slidingly arranged in the front lever and the rear lever, the upper ends of the front pre-tightening force loading block and the rear pre-tightening force loading block are abutted with the upper clamping plate or the lower clamping plate respectively, and the front pre-tightening force loading block positioning pin and the rear pre-tightening force loading block positioning pin position the front pre-tightening force loading block and the rear pre-tightening force loading block.
[0011] In the above scheme, the upper clamping plate and the lower clamping plate are provided with first through holes in the vertical direction, and the front positioning connecting piece and the rear positioning connecting piece pass through the first through holes and are fixed.
[0012] In the above scheme, the upper clamping plate, the front connecting plate and the rear connecting plate are provided with second through holes in the horizontal direction correspondingly, and are fixed in cooperation with the clamping plate front connecting piece and the clamping plate rear connecting piece.
[0013] In the above scheme, the lower clamping plate, the front connecting plate and the rear connecting plate are provided with standby holes in the horizontal direction correspondingly, and are adapted to the clamping plate front connecting piece and the clamping plate rear connecting piece.
[0014] In the above scheme, the front lever and the rear lever are provided with sliding grooves which are upwardly opened, and the front pre-tightening force loading block and the rear pre-tightening force loading block are slidingly arranged in the sliding grooves.
[0015] In the above scheme, the bottom width of the sliding groove is greater than the opening width, and the front pre-tightening force loading block and the rear pre-tightening force loading block are attached to the side wall of the sliding groove.
[0016] In the above scheme, the sliding groove extends to form a lateral opening on the opposite side of the front lever and the rear lever.
[0017] In the above scheme, the side surface of the front lever and the rear lever is provided with a clamping groove which penetrates through, the direction of the clamping groove is the same as the direction of the sliding groove, the front pre-tightening force loading block and the rear pre-tightening force loading block are provided with positioning holes at the height corresponding to the clamping groove, and the front pre-tightening force loading block positioning pin and the rear pre-tightening force loading block positioning pin pass through the clamping groove and the positioning hole and are positioned.
[0018] In the above scheme, the upper end of the front pre-tightening force loading block and the rear pre-tightening force loading block is pointed.
[0019] In the above scheme, the front end of the front lever and the rear end of the rear lever are further provided with end test load loading holes.
[0020] The utility model discloses beneficial effects:
[0021] The utility model discloses a kind of clamping plate structures of aircraft airfoil test loading, upper clamping plate and lower clamping plate are respectively arranged on the upper and lower of airfoil, and the abutment of clamping plate is realized by front and rear connecting structure, lever structure and pre-tightening force loading block. Before test, pre-tightening force loading block slides in lever, the ratio of adjustable pre-tightening force relative to test load, then positioning pin is used to position locking. In test process, the pre-tightening force of airfoil changes along with the change of test load, and pre-tightening force value is clear and accurate to apply, guarantee the stability of loading process. BRIEF DESCRIPTION OF DRAWINGS
[0022] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or prior art, the drawings needed to be used in the following embodiment or prior art description will be simply introduced, and obviously, the drawings in the following description are only some embodiments of the utility model, and other drawings can be obtained according to the structure shown in the drawings without creative labor for those skilled in the art.
[0023] Figure 1 It is the schematic diagram of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0024] Figure 2 It is the schematic diagram of the upper clamping plate of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0025] Figure 3 It is the schematic diagram of the lower clamping plate of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0026] Figure 4a It is the schematic diagram of the front connecting plate of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0027] Figure 4b It is the schematic diagram of the rear connecting plate of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0028] Figure 5 It is the schematic diagram of the front lever of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0029] Figure 6 It is the schematic diagram of the front lever of the clamping plate structure of aircraft airfoil test loading of the utility model;
[0030] Figure 7 It is the schematic diagram of the airfoil loading in embodiment 1 of the aircraft airfoil test loading of the utility model;
[0031] Figure 8 It is the schematic diagram of the airfoil loading in embodiment 2 of the aircraft airfoil test loading of the utility model.
[0032] Wherein, the upper clamping plate 1, the lower clamping plate 2, the front connecting plate 3, the rear connecting plate 4, the front lever 5, the rear lever 6, the front pre-tightening force loading block 7, the rear pre-tightening force loading block 8, the front positioning connecting piece 9, the rear positioning connecting piece 10, the clamping plate front connecting piece 11, the clamping plate rear connecting piece 12, the front lever connecting piece 13, the rear lever connecting piece 14, the front pre-tightening force loading block positioning pin 15, the rear pre-tightening force loading block positioning pin 16, the sliding groove 17, the clamping groove 18, the test load loading hole 19.
[0033] The realization, functional features and advantages of the utility model will be further explained in combination with embodiments with reference to the drawings. DETAILED DESCRIPTION
[0034] The exemplary embodiments will be described in detail hereinbelow with reference to the drawings. In the following description, the same numbers in different drawings represent the same or similar elements unless otherwise represented. The embodiments described in the following exemplary embodiments do not represent all the embodiments consistent with the present disclosure. Rather, they are merely examples of devices and methods consistent with some aspects of the present disclosure as detailed in the appended claims.
[0035] The terms "first", "second", and the like in the specification and claims of the present disclosure are used to distinguish like objects, not necessarily in a particular order or sequence. It should be understood that the data thus used can be interchanged, where appropriate, so that the embodiments of the present disclosure described herein can be carried out in other than the order shown or described herein.
[0036] Furthermore, the terms "comprise" and "have", and any variations thereof, are intended to cover a non-exclusive inclusion, for example, a process, method, system, product, or apparatus that comprises a list of steps or units is not necessarily limited to those clearly listed steps or units, but can include other steps or units not clearly listed or inherent to such processes, methods, products, or apparatus.
[0037] Plural, including two or more.
[0038] And / or, it should be understood that the term "and / or" used in the present disclosure is merely a description of the association relationship of the associated objects, which means that there can be three relationships. For example, A and / or B can represent the three cases of A alone, A and B together, and B alone.
[0039] As Figures 1-3 , Figure 4a , Figure 4b , Figure 5 and Figure 6As shown, the utility model technical scheme one embodiment provides a kind of cardboard structure of aircraft airfoil test loading, it include: upper card 1, lower card 2, front connecting plate 3, rear connecting plate 4, front lever 5, rear lever 6, front pre-tightening force loading block 7, rear pre-tightening force loading block 8, front positioning connecting piece 9, rear positioning connecting piece 10, card front connecting piece 11, card rear connecting piece 12, front lever connecting piece 13, rear lever connecting piece 14, front pre-tightening force loading block positioning pin 15 and rear pre-tightening force loading block positioning pin 16.
[0040] The inner surface of upper card 1 is in contact with one side of the airfoil, and the inner surface of lower card 2 is in contact with the other side of the airfoil; upper card 1 and lower card 2 are arranged vertically and fixed by front positioning connecting piece 9 and rear positioning connecting piece 10; front connecting plate 3 and rear connecting plate 4 are arranged on both sides of the front and rear of upper card 1 and lower card 2 respectively and fixed by card front connecting piece 11 and card rear connecting piece 12; front lever 5 and rear lever 6 are arranged above upper card 1 or below lower card 2 and hinged with front connecting plate 3 and rear connecting plate 4 respectively by front lever connecting piece 13 and rear lever connecting piece 14; front pre-tightening force loading block 7 and rear pre-tightening force loading block 8 are slidingly arranged in front lever 5 and rear lever 6, and the upper ends of front pre-tightening force loading block 7 and rear pre-tightening force are respectively in abutment with upper card 1 or lower card 2; front pre-tightening force loading block positioning pin 15 and rear pre-tightening force loading block positioning pin 16 position front pre-tightening force loading block 7 and rear pre-tightening force loading block 8.
[0041] The utility model sets up upper card 1 and lower card 2 on the upper and lower of airfoil respectively, and realizes the hinge with front lever 5 and rear lever 6 by front connecting plate 3, rear connecting plate 4, front positioning connecting piece 9 and rear positioning connecting piece 10; front pre-tightening force loading block 7 and rear pre-tightening force loading block 8 are slidingly arranged in front lever 5 and rear lever 6, and the upper ends of front pre-tightening force loading block 7 and rear pre-tightening force are respectively in abutment with upper card 1 or lower card 2; by sliding in lever, the pre-tightening force of airfoil can be accurately applied.
[0042] Specifically, before test, front pre-tightening force loading block 7 and rear pre-tightening force loading block 8 slide in front lever 5 and rear lever 6, the ratio of pre-tightening force to test load can be adjusted, and then front pre-tightening force loading block positioning pin 15 and rear pre-tightening force loading block positioning pin 16 are used for positioning and locking. During test, the pre-tightening force of airfoil changes with the change of test load, and the pre-tightening force value is clear and accurate, which ensures the stability of loading process.
[0043] Upper card 1 and lower card 2 are provided with first through hole in vertical direction, and front positioning connecting piece 9 and rear positioning connecting piece 10 pass through first through hole to fix upper card 1 and lower card 2. Preferably, front positioning connecting piece 9 and rear positioning connecting piece 10 are bolts.
[0044] The upper clamping plate 1, the front connecting plate 3 and the rear connecting plate 4 are provided with second through holes corresponding in the horizontal direction, which are matched with the clamping plate front connecting piece 11 and the clamping plate rear connecting piece 12. Preferably, the clamping plate front connecting piece 11 and the clamping plate rear connecting piece 12 are bolts, which are fixed by penetrating the upper clamping plate 1 and the front connecting plate 3 or the upper clamping plate 1 and the rear connecting plate 4. Further, the lower clamping plate 2, the front connecting plate 3 and the rear connecting plate 4 are provided with spare holes corresponding in the horizontal direction, which are matched with the clamping plate front connecting piece 11 and the clamping plate rear connecting piece 12.
[0045] The upper and lower ends of the front connecting plate 3 and the rear connecting plate 4 are provided with third through holes, which are used for hinging with the front lever 5 and the rear lever 6. When the front lever 5 and the rear lever 6 are hinged with the front connecting plate 3 and the rear connecting plate 4 below the lower clamping plate 2, the front connecting plate 3 and the rear connecting plate 4 are connected with the upper clamping plate 1 through the second through holes; when the front lever 5 and the rear lever 6 are hinged with the front connecting plate 3 and the rear connecting plate 4 above the upper clamping plate 1, the front connecting plate 3 and the rear connecting plate 4 are connected with the lower clamping plate 2 through the spare holes. In this way, when the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 exert pre-tightening force, the upper clamping plate 1 and the lower clamping plate 2 are only fixed at the ends without other connecting structures, which ensures that the upper clamping plate 1 and the lower clamping plate 2 generate precise pre-tightening force.
[0046] The front lever 5 and the rear lever 6 are provided with upwardly opening sliding grooves 17, and the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 are slidingly arranged in the sliding grooves 17. Preferably, the bottom width of the sliding groove 17 is greater than the opening width, and the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 are attached to the side walls of the sliding groove. The sliding groove 17 extends to form a lateral opening on the opposite side of the front lever 5 and the rear lever 6. In this way, the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 can be installed into the sliding groove 17 from the opening, and since the bottom size of the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 is the largest, they will not slide out during the sliding process. Further, the bottom of the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 has a stepped structure, and the sliding groove 17 also has a stepped structure, so that the protruding part of the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 can be clamped with the sliding groove 17.
[0047] The side surface of the front lever 5 and the rear lever 6 is provided with a clamping groove 18 penetrating through, and the direction of the clamping groove 18 is the same as that of the sliding groove 17. The front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 are provided with positioning holes at a height corresponding to the clamping groove 18, and the front pre-tightening force loading block positioning pin 15 and the rear pre-tightening force loading block positioning pin 16 penetrate through the clamping groove 18 and the positioning hole. The front pre-tightening force loading block positioning pin 15 and the rear pre-tightening force loading block positioning pin 16 are used for fixing the position of the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8.
[0048] Preferably, the upper end of the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 is pointed, so that the position of applying force to the airfoil is more accurate.
[0049] The front end of the front lever 5 and the rear end of the rear lever 6 are further provided with an end test load loading hole 19, and a test load is applied at the test load loading hole 19 during the test.
[0050] Embodiment 1
[0051] As shown in Figure 7 Fig. 1, the wing surface is loaded downward, and a downward test load F1 is applied at the test load loading hole of the front lever 5, and a downward test load F2 is applied at the test load loading hole of the rear lever 6, wherein the size and the point of action of the resultant force of F1 and F2 are determined by the test scheme, and the resultant force of F1 and F2 is the test total load applied to the wing surface.
[0052] According to the principle of the lever, the wing surface pre-tightening force P1 formed by F1 is F1 x L1 / L2, and the wing surface pre-tightening force P2 formed by F2 is F2 x L3 / L4, and the size and the point of action of the resultant force of P1 and P2 are determined.
[0053] Embodiment 2
[0054] As shown in Figure 8 Fig. 2, the wing surface is loaded upward, and on the basis of Embodiment 1, the front lever 5, the rear lever 6, the front pre-tightening force loading block 7 and the rear pre-tightening force loading block 8 are installed to the upper part, and the front connecting plate 3 and the rear connecting plate 4 are connected with the lower clamping plate 2, and upward loads are applied at the test load loading holes of the front lever 5 and the rear lever 6. The calculation method of the pre-tightening force is the same as that of Embodiment 1, which will not be described here.
[0055] It should be noted that in this document, the terms "comprising", "containing", or any other variant thereof are intended to cover non-exclusive inclusions, so that a process, method, article or apparatus that includes a list of elements not only includes those elements, but also includes other elements not explicitly listed, or inherent to such a process, method, article or apparatus. Without more limitations, the element defined by the statement "comprising a" does not exclude the presence of additional identical elements in the process, method, article or apparatus that includes the element.
[0056] The above-mentioned embodiment serial numbers of the utility model only serve for description, and do not represent the advantages and disadvantages of the embodiments.
[0057] Through the description of the above embodiments, those skilled in the art can clearly understand that the above-mentioned implementation methods can be realized by means of software and the necessary general hardware platform, of course, they can also be realized by hardware, but in many cases the former is a better implementation method. Based on such understanding, the technical solutions of the present application can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes a plurality of instructions for causing a terminal (which can be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in each embodiment of the present application.
[0058] The embodiments of the present application are described above in combination with the drawings, but the present application is not limited to the above-mentioned specific embodiments, and the above-mentioned specific embodiments are only illustrative and not restrictive. Those skilled in the art can make many forms under the inspiration of the present application without departing from the scope of the present application and the protection scope of the claims.
Claims
1. A test loading card structure for an aircraft airfoil, characterized by, The application relates to a wing plate clamping device. The inner surface of the upper clamping plate is in contact with one side of a wing surface, and the inner surface of the lower clamping plate is in contact with the other side of the wing surface. The upper clamping plate and the lower clamping plate are arranged in a vertical mode and are fixed through the front positioning connecting piece and the rear positioning connecting piece. The front connecting plate and the rear connecting plate are arranged on the two sides of the front part and the rear part of the upper clamping plate and the lower clamping plate respectively and are fixed through the clamping plate front part connecting piece and the clamping plate rear part connecting piece. The front lever and the rear lever are arranged above the upper clamping plate or below the lower clamping plate and are hinged with the front connecting plate and the rear connecting plate through the front lever connecting piece and the rear lever connecting piece. The front pre-tightening force loading block and the rear pre-tightening force loading block are arranged in the front lever and the rear lever in a sliding mode, the upper ends of the front pre-tightening force loading block and the rear pre-tightening force loading block are in abutment with the upper clamping plate or the lower clamping plate respectively, and the front pre-tightening force loading block positioning pin and the rear pre-tightening force loading block positioning pin position the front pre-tightening force loading block and the rear pre-tightening force loading block. The upper clamping plate and the lower clamping plate are provided with first through holes in a vertical direction, and the front positioning connecting piece and the rear positioning connecting piece pass through the first through holes and are fixed.
2. The test loading panel structure for an aircraft airfoil as defined in claim 1, wherein, The upper clamping plate, the front connecting plate and the rear connecting plate are provided with second through holes in a horizontal direction, and are fixed in cooperation with the clamping plate front part connecting piece and the clamping plate rear part connecting piece.
3. The test loading panel structure for an aircraft airfoil as defined in claim 1, wherein, The lower clamping plate, the front connecting plate and the rear connecting plate are provided with spare holes in a horizontal direction, and are matched with the clamping plate front part connecting piece and the clamping plate rear part connecting piece.
4. The test loading panel structure for an aircraft airfoil as defined in claim 1, wherein, The front lever and the rear lever are provided with upwardly-open sliding grooves, and the front pre-tightening force loading block and the rear pre-tightening force loading block are arranged in the sliding grooves in a sliding mode.
5. The test loading panel structure for an aircraft airfoil as defined in claim 1, wherein, The bottom width of the sliding groove is greater than the opening width, and the front pre-tightening force loading block and the rear pre-tightening force loading block are attached to the side wall of the sliding groove.
6. The test loading panel structure for an aircraft airfoil as defined in claim 5, wherein, The sliding groove extends to form a lateral opening on the opposite side of the front lever and the rear lever.
7. The test loading panel structure for an aircraft airfoil as defined in claim 5 wherein, The side surface of the front lever and the rear lever is provided with a clamping groove penetrating through the same, the direction of the clamping groove is the same as that of the sliding groove, the front pre-tightening force loading block and the rear pre-tightening force loading block are provided with positioning holes at a height corresponding to the clamping groove, and the front pre-tightening force loading block positioning pin and the rear pre-tightening force loading block positioning pin are positioned through the clamping groove and the positioning hole.
8. The test loading panel structure for an aircraft airfoil as defined in claim 5, wherein, The upper end of the front pre-tightening force loading block and the rear pre-tightening force loading block is pointed.
9. The test loading panel structure for an aircraft airfoil as defined in claim 1 wherein, The front end part of the front lever and the rear end part of the rear lever are further provided with end part test load loading holes.
10. The test loading panel structure for an aircraft airfoil as defined in claim 1, wherein,