An inclined airtight floor strength test loading structure inside the main landing gear bay of an aircraft

Abstract

The present application specifically relates to a loading structure for the strength test of the inclined airtight floor in the main landing gear bay of an aircraft. The design is to support with a fixed bottom plate, connect the edges of the inclined airtight floor with a framework composed of a central wing simulation plate, a horizontal airtight floor simulation plate, a vertical skin simulation plate, and an inclined skin simulation plate hinged together. A lateral shear load is reciprocally applied by a loading actuator, and the loading airbag is constrained by the bottom constraint edge, top constraint edge, vertical constraint edge, and inclined constraint edge on the central wing simulation plate, horizontal airtight floor simulation plate, vertical skin simulation plate, and inclined skin simulation plate in cooperation with a loading cover plate. The airtight load is applied by the loading airbag, and the loading cover plate is hinged to the top constraint edge, vertical constraint edge, and inclined constraint edge, which can avoid the problem of mutual interference between the airtight load loading and the lateral shear load loading, and ensure the accurate loading of the airtight load and lateral shear load on the inclined airtight floor.

Description

Technical Field

[0001] This application belongs to the technical field of the strength test of the inclined airtight floor in the main landing gear bay of an aircraft, and particularly relates to a loading structure for the strength test of the inclined airtight floor in the main landing gear bay of an aircraft. Background Technique

[0002] Inside the main landing gear bay of an aircraft, the inclined airtight floor is trapezoidal, arranged in the airtight area, with its lower side edge connected to the central wing, its upper side edge connected to the horizontal airtight floor, and its two vertical and inclined side edges connected to the fuselage skin. During operation, it bears the airtight load and the lateral shear load generated by the inconsistent deformation of the central wing and the horizontal airtight floor.

[0003] To cope with the damage caused by the lateral shear load, the relaxation method is mostly used to release the deformation of the inclined airtight floor. The longitudinal beam of the inclined airtight floor is divided into multiple blocks along the span direction, and rubber is used as the sealing strip to ensure airtightness. On the basis of ensuring the airtight load, the connection with the central wing is weakened.

[0004] When conducting a strength test on the inclined airtight floor, it is necessary to repeatedly apply a lateral shear load under the airtight load. However, in practice, limited by the configuration of the inclined airtight floor, it is difficult to accurately apply the airtight load to it directly through air pressure, and it is difficult to overcome the problem of mutual interference between the application of the airtight load and the application of the lateral shear load.

[0005] In view of the existence of the above technical defects, this application is proposed.

[0006] It should be noted that the disclosure of the above background technical content is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0007] The purpose of this application is to provide a loading structure for the strength test of the inclined airtight floor in the main landing gear bay of an aircraft to overcome or mitigate at least one aspect of the known technical defects.

[0008] The technical solution of this application is as follows:

[0009] A loading structure for the strength test of the inclined airtight floor in the main landing gear bay of an aircraft, comprising:

[0010] A fixed bottom plate;

[0011] A central wing simulation plate, vertically connected to the fixed bottom plate, bolted to the lower side edge of the inclined airtight floor, and having a bottom constraint edge located below the lower side edge of the inclined airtight floor at its side wall; both ends of the bottom constraint edge are bent upward;

[0012] Horizontal airtight floor simulation board, bolted to the upper edge of the inclined airtight floor, and the side wall has a top restraint edge located above the lower edge of the inclined airtight floor; both ends of the top restraint edge are bent downward.

[0013] Vertical skin simulation board, hinged at both ends between the central wing simulation board and the horizontal airtight floor simulation board, bolted to the vertical edge of the inclined airtight floor, and the side wall has a vertical restraint edge located outside the vertical edge of the inclined airtight floor.

[0014] Oblique skin simulation board, hinged at both ends between the central wing simulation board and the horizontal airtight floor simulation board, bolted to the oblique edge of the inclined airtight floor, and the side wall has an oblique restraint edge located outside the oblique edge of the inclined airtight floor.

[0015] Loading airbag, arranged between the bottom restraint edge, the top restraint edge, the vertical restraint edge and the oblique restraint edge, and its air inlet nozzle and air outlet nozzle penetrate through the upwardly bent parts at both ends of the bottom restraint edge.

[0016] Loading cover plate, its bottom edge is bolted to the bottom restraint edge, and both side edges are hinged to the downwardly bent parts at both ends of the top restraint edge, and are also hinged to the vertical restraint edge and the oblique restraint edge, and the whole covers the loading airbag.

[0017] Loading actuator, whose piston rod is hinged to one end of the horizontal airtight floor simulation board close to the vertical skin simulation board.

[0018] According to at least one embodiment of the present application, in the above-mentioned inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, a plurality of gussets are arranged between the fixed bottom plate and the central wing simulation board;

[0019] A plurality of gussets are arranged between the central wing simulation board and the bottom restraint edge;

[0020] A plurality of gussets are arranged between the horizontal airtight floor simulation board and the top restraint edge;

[0021] A plurality of gussets are arranged between the vertical skin simulation board and the vertical edge;

[0022] A plurality of gussets are arranged between the oblique skin simulation board and the oblique edge.

[0023] According to at least one embodiment of the present application, in the above-mentioned inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, both ends of the vertical skin simulation board and the oblique skin simulation board are hinged between the central wing simulation board and the horizontal airtight floor simulation board through a rotating shaft.

[0024] According to at least one embodiment of the present application, in the inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, a plurality of reinforcing ribs are connected to the loading cover plate, and both ends are connected by pull plates, which are matched with a single-ear and double-ear structure. By using spherical plain bearings, they are hinged to the downwardly bent parts at both ends of the top constraint edge, and are also hinged to the vertical constraint edge and the inclined constraint edge.

[0025] According to at least one embodiment of the present application, the inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft further includes:

[0026] A dynamometer is connected to the piston rod of the loading actuator, which is matched with a single-ear and double-ear structure. By using a pin shaft, it is hinged to one end of the horizontal airtight floor simulation plate close to the vertical skin simulation plate.

[0027] The present application has at least the following beneficial technical effects:

[0028] There is provided an inclined airtight floor strength test loading structure in the main landing gear bay of an aircraft. Its design uses a fixed bottom plate for support, and a framework formed by hinging a central wing simulation plate, a horizontal airtight floor simulation plate, a vertical skin simulation plate, and an inclined skin simulation plate connects the edges of the inclined airtight floor. A lateral shear load is applied reciprocally by a loading actuator, and the bottom constraint edge, top constraint edge, vertical constraint edge, and inclined constraint edge on the central wing simulation plate, horizontal airtight floor simulation plate, vertical skin simulation plate, and inclined skin simulation plate cooperate with the loading cover plate to constrain the loading airbag. An airtight load is applied by the loading airbag, and the loading cover plate is hinged to the top constraint edge, vertical constraint edge, and inclined constraint edge, which can avoid the problem that the airtight load loading and the lateral shear load loading interfere with each other, and ensure the accurate loading of the airtight load and the lateral shear load on the inclined airtight floor. Description of the Drawings

[0029] Figure 1 is a schematic diagram of the inclined airtight floor strength test loading structure in the main landing gear bay provided by the embodiment of the present application;

[0030] Figure 2 is Figure 1 a lateral partial schematic diagram of

[0031] Figure 3 is Figure 2 a sectional view of

[0032] Figure 4 is a schematic diagram of the fixed bottom plate and the central wing simulation plate provided by the embodiment of the present application;

[0033] Figure 5 is a schematic diagram of the inclined airtight floor provided by the embodiment of the present application;

[0034] Figure 6It is a schematic diagram of the horizontal airtight floor simulation board provided by the embodiment of the present application;

[0035] Figure 7 It is a schematic diagram of the vertical skin simulation board provided by the embodiment of the present application;

[0036] Figure 8 It is a schematic diagram of the inclined skin simulation board provided by the embodiment of the present application;

[0037] Figure 9 It is a schematic diagram of the loading airbag provided by the embodiment of the present application;

[0038] Figure 10 It is a schematic diagram of the loading cover plate and its reinforcing ribs provided by the embodiment of the present application;

[0039] Figure 11 It is a schematic diagram of the pull plate provided by the embodiment of the present application;

[0040] Wherein:

[0041] 1 - fixed bottom plate; 2 - central wing simulation board; 3 - inclined airtight floor; 4 - horizontal airtight floor simulation board; 5 - vertical skin simulation board; 6 - inclined skin simulation board; 7 - loading airbag; 8 - loading cover plate; 9 - loading actuator; 10 - dynamometer; 11 - rotating shaft; 12 - reinforcing rib; 13 - pull plate.

[0042] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and should not be construed as a limitation of this patent. Detailed implementation manners

[0043] To make the technical solutions of the present application and their advantages clearer, the technical solutions of the present application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application and not to limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0044] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The terms indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate relative directions or positional relationships, rather than implying that the device or component must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. Therefore, it should not be construed as a limitation to this application. The terms "first", "second", "third", and similar terms used in the description of this application are only for descriptive purposes to distinguish different components, and cannot be construed as indicating or implying relative importance. The similar terms such as "a", "an", or "the" used in the description of this application should not be construed as an absolute limitation on the quantity, but should be understood as having at least one. The similar terms such as "comprising" or "including" used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0045] In addition, it should be noted that, unless otherwise clearly specified and limited, the similar terms such as "installed", "connected", "joined", etc. used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0046] The following will further elaborate on this application in conjunction with the attached Figures 1 to 11 drawings.

[0047] An inclined airtight floor strength test loading structure in the main landing gear bay of an aircraft, comprising:

[0048] A fixed bottom plate 1, which can be fixed to the floor by anchor bolts;

[0049] A central wing simulation plate 2, vertically connected to the fixed bottom plate 1, bolt-connected to the lower side edge of the inclined airtight floor 3, and having a bottom restraint edge located below the lower side edge of the inclined airtight floor 3 at its side wall; both ends of the bottom restraint edge are bent upward;

[0050] A horizontal airtight floor simulation plate 4, bolt-connected to the upper side edge of the inclined airtight floor 3, and having a top restraint edge located above the lower side edge of the inclined airtight floor 3 at its side wall; both ends of the top restraint edge are bent downward;

[0051] The vertical skin simulation plate 5 is hinged at both ends between the central wing simulation plate 2 and the horizontal airtight floor simulation plate 4, and is bolted to the vertical edge of the inclined airtight floor 3. The side wall has a vertical constraint edge located outside the vertical edge of the inclined airtight floor 3;

[0052] The inclined skin simulation plate 6 is hinged at both ends between the central wing simulation plate 2 and the horizontal airtight floor simulation plate 4, and is bolted to the inclined edge of the inclined airtight floor 3. The side wall has an inclined constraint edge located outside the inclined edge of the inclined airtight floor 3;

[0053] The loading airbag 7 is arranged between the bottom constraint edge, the top constraint edge, the vertical constraint edge, and the inclined constraint edge. Its air inlet nozzle and exhaust nozzle penetrate through the upward bent parts at both ends of the bottom constraint edge;

[0054] The loading cover plate 8 has its bottom edge bolted to the bottom constraint edge, and its two side edges are hinged to the downward bent parts at both ends of the top constraint edge, and are also hinged to the vertical constraint edge and the inclined constraint edge, and the whole covers the loading airbag 7;

[0055] The loading actuator 9 has its piston rod hinged to one end of the horizontal airtight floor simulation plate 4 close to the vertical skin simulation plate 5, and its cylinder body can be fixed on the strut.

[0056] Using the aircraft main landing gear bay inclined airtight floor strength test loading structure disclosed in the above embodiment for the strength test, the airtight load of a predetermined magnitude can be applied to the inclined airtight floor 3 by inflating the loading airbag 7, and the lateral shear load can be reciprocally applied to the inclined airtight floor 3 by the telescopic movement of the piston rod of the loading actuator 9 along the water tank direction.

[0057] For the aircraft main landing gear bay inclined airtight floor strength test loading structure disclosed in the above embodiment, those skilled in the art can understand that its design is supported by the fixed bottom plate 1, and the edges of the inclined airtight floor 3 are connected by a framework formed by hinging the central wing simulation plate 2, the horizontal airtight floor simulation plate 4, the vertical skin simulation plate 5, and the inclined skin simulation plate 6. The lateral shear load is reciprocally applied by the loading actuator 9, and the loading airbag 7 is constrained by the bottom constraint edge, the top constraint edge, the vertical constraint edge, and the inclined constraint edge on the central wing simulation plate 2, the horizontal airtight floor simulation plate 4, the vertical skin simulation plate 5, and the inclined skin simulation plate 6 in cooperation with the loading cover plate 8. The airtight load is applied by the loading airbag 7, and the loading cover plate 8 is hinged to the top constraint edge, the vertical constraint edge, and the inclined constraint edge, which can avoid the problem of mutual interference between the airtight load loading and the lateral shear load loading, and ensure the accurate loading of the airtight load and the lateral shear load on the inclined airtight floor 3.

[0058] In some alternative embodiments, in the above-mentioned inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, a plurality of gussets are provided between the fixed bottom plate 1 and the central wing simulation plate 2;

[0059] A plurality of gussets are provided between the central wing simulation plate 2 and the bottom constraint edge;

[0060] A plurality of gussets are provided between the horizontal airtight floor simulation plate 4 and the top constraint edge;

[0061] A plurality of gussets are provided between the vertical skin simulation plate 5 and the vertical edge to strengthen the structure.

[0062] In some alternative embodiments, in the above-mentioned inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, both ends of the vertical skin simulation plate 5 and the inclined skin simulation plate 6 are hinged between the central wing simulation plate 2 and the horizontal airtight floor simulation plate 4 through a rotating shaft 11 to ensure smooth operation of the structural deformation.

[0063] In some alternative embodiments, in the above-mentioned inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, a plurality of reinforcing ribs 12 are connected to the loading cover plate 8, and both ends are in a single-double ear structure and are hinged to the downward-bending parts at both ends of the top constraint edge and the vertical constraint edge and the inclined constraint edge through spherical plain bearings to ensure smooth operation of the structural deformation.

[0064] In some alternative embodiments, in the above-mentioned inclined airtight floor strength test loading structure in the main landing gear bay of the aircraft, it further includes:

[0065] A dynamometer 10 is connected to the piston rod of the loading actuator 9, and is in a single-double ear structure and is hinged to one end of the horizontal airtight floor simulation plate 4 close to the vertical skin simulation plate 5 through a pin shaft, and can measure the lateral shear load of the inclined airtight floor 3.

[0066] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the various embodiments can be referred to each other.

[0067] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. An inclined airtight floor strength test loading structure inside the main landing gear bay of an aircraft, characterized in that, Comprising: Fixed bottom plate (1); Central wing simulation plate (2), vertically connected to the fixed bottom plate (1), bolt - connected to the lower side edge of the inclined airtight floor (3), and the side wall has a bottom restraint edge located below the lower side edge of the inclined airtight floor (3); Both ends of the bottom restraint edge are bent upwards; Horizontal airtight floor simulation plate (4), bolt - connected to the upper side edge of the inclined airtight floor (3), and the side wall has a top restraint edge located above the lower side edge of the inclined airtight floor (3); both ends of the top restraint edge are bent downwards; Vertical skin simulation plate (5), with both ends hinged between the central wing simulation plate (2) and the horizontal airtight floor simulation plate (4), bolt - connected to the vertical edge of the inclined airtight floor (3), and the side wall has a vertical restraint edge located outside the vertical edge of the inclined airtight floor (3); Oblique skin simulation plate (6), with both ends hinged between the central wing simulation plate (2) and the horizontal airtight floor simulation plate (4), bolt - connected to the oblique edge of the inclined airtight floor (3), and the side wall has an oblique restraint edge located outside the oblique edge of the inclined airtight floor (3); Loading airbag (7), arranged between the bottom restraint edge, the top restraint edge, the vertical restraint edge, and the oblique restraint edge, and its air inlet nozzle and exhaust nozzle penetrate through the upward - bent parts at both ends of the bottom restraint edge; Loading cover plate (8), with its bottom edge bolt - connected to the bottom restraint edge, and both side edges hinged to the downward - bent parts at both ends of the top restraint edge, and also hinged to the vertical restraint edge and the oblique restraint edge, and the whole covers the loading airbag (7); Loading actuator (9), whose piston rod is hinged to one end of the horizontal airtight floor simulation plate (4) close to the vertical skin simulation plate (5).

2. The loading structure for the strength test of the inclined airtight floor in the main landing gear compartment of an aircraft according to claim 1, characterized in that Multiple corner pieces are arranged between the fixed bottom plate (1) and the central wing simulation plate (2); Multiple corner pieces are arranged between the central wing simulation plate (2) and the bottom restraint edge; Multiple corner pieces are arranged between the horizontal airtight floor simulation plate (4) and the top restraint edge; Multiple corner pieces are arranged between the vertical skin simulation plate (5) and the vertical edge; Multiple corner pieces are arranged between the oblique skin simulation plate (6) and the oblique edge.

3. The loading structure for the strength test of the inclined airtight floor in the main landing gear compartment of an aircraft according to claim 1, characterized in that Both ends of the vertical skin simulation plate (5) and the oblique skin simulation plate (6) are hinged between the central wing simulation plate (2) and the horizontal airtight floor simulation plate (4) through a rotating shaft (11).

4. The loading structure for the strength test of the inclined airtight floor in the main landing gear compartment of an aircraft according to claim 1, characterized in that Multiple reinforcing ribs (12) are connected to the loading cover plate (8), and both ends are hinged to the downward - bent parts at both ends of the top restraint edge, and also hinged to the vertical restraint edge and the oblique restraint edge through a single - double ear structure in cooperation with a draw plate (13) and using a spherical plain bearing.

5. The loading structure for the strength test of the inclined airtight floor in the main landing gear compartment of an aircraft according to claim 1, characterized in that It further comprises: The dynamometer (10) is connected to the piston rod of the loading actuator (9), and is hinged to one end of the horizontal airtight floor simulation plate (4) close to the vertical skin simulation plate (5) by using a pin shaft in a single and double ear structure.

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