Aircraft landing gear drop test device and test method

Abstract

The invention discloses an aircraft landing gear drop test device and method, and relates to the technical field of aircraft landing test devices.The aircraft landing gear drop test device comprises a platform, and a supporting structure is arranged on the platform; the rack is movably connected with the supporting structure so as to ascend and descend relative to the supporting structure. Moreover, a mounting seat is arranged on the rack so as to be connected with the undercarriage; the connecting seat is arranged on the platform and is arranged below the rack; the test box body is detachably connected to the connecting base, and the test box body is provided with a first cavity with an upward opening so as to contain a pavement material. According to the undercarriage drop test device and the undercarriage drop test method, different pavement materials can be loaded in the first cavity of the test box body, so that different pavement structures are formed, and the undercarriage drop test device can perform simulation experiments on various pavement working conditions.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft landing test devices, and in particular to an aircraft landing gear drop shock test device and a test method. Background Art

[0002] The landing gear is an important load-bearing component of an aircraft, and plays a vital role in the safety of the aircraft during takeoff and landing. In order to ensure the flight safety of the aircraft, during the design and production of the aircraft, a drop shock test is usually used to obtain its dynamic response and impact load during the landing process.

[0003] The existing landing gear drop test equipment generally uses a metal surface as the impact surface, and collects the collision performance of the landing gear by hitting the metal surface with the landing gear. However, the landing location of the aircraft is mostly in areas with complex terrain environments such as concrete, grass, and gravel, which is undoubtedly quite different from the landing surface of the drop test, resulting in the limited authenticity and reliability of the existing drop test, which in turn affects the accuracy of the test results and the evaluation of the landing gear structural performance. Summary of the invention

[0004] The purpose of the present application is to provide an aircraft landing gear drop shock test device and a test method. The aircraft landing gear drop shock test device improves the test equipment so that the test equipment has the ability to simulate different road surfaces such as metal ground, grass, and concrete ground, so as to solve the problem that there is a large difference between the landing surface of the existing aircraft landing gear drop shock test device and the landing surface of the real scene.

[0005] In order to achieve the above purpose, this application adopts the following technical solutions:

[0006] An aircraft landing gear drop shock test device, comprising:

[0007] platform;

[0008] A supporting structure is arranged on the platform;

[0009] A platform is movably connected to the support structure so as to be lifted and lowered relative to the support structure; and a mounting seat is provided on the platform so as to connect the landing gear;

[0010] A test assembly, used to bear the impact of the landing gear, wherein the test assembly comprises:

[0011] A connecting seat is provided on the platform and arranged below the stand;

[0012] The test box body is detachably connected to the connection seat, and the test box body is provided with a first cavity with an upward opening for containing the pavement material.

[0013] In some embodiments, the test component further comprises:

[0014] The frame body is detachably enclosed on the outer side of the test box body and protrudes from the test box body, thereby forming a second cavity with an upward opening with the test box body to hold the pavement material.

[0015] In some embodiments, the frame body comprises:

[0016] A plurality of first frame members, wherein the plurality of first frame members are sequentially connected along the circumference of the test box body and extend upwardly toward the first cavity, thereby forming a second cavity with an upward opening with the test box body;

[0017] A plurality of second frame members are detachably connected to two adjacent first frame members, so that the two adjacent first frame members are connected and fixed.

[0018] In some embodiments, the test component further comprises:

[0019] The test block is detachably connected to the connection seat, and the test block is a metal block. The test block and one of the test box bodies are connected to the same connection seat.

[0020] In some embodiments, there are multiple mounting seats, which are respectively arranged at the front and rear sides of the stand, and there are multiple test assemblies, which are respectively arranged at the front and rear sides of the stand.

[0021] In some embodiments, the support structure includes at least two support columns, the two support columns are arranged opposite to each other, and the stand is disposed between the two support columns and is movably connected to the support columns.

[0022] In some embodiments, the support column is connected to a plurality of first support members, the plurality of first support members are respectively arranged on the front side and the rear side of the support column, and the first support members are inclined to the support column and extend to be connected to the platform; and,

[0023] The support column is also connected to a second support member, which is arranged on both sides of the support column opposite to the stand, and the second support member is inclined to the support column and extends to be connected to the platform.

[0024] In some embodiments, the platform is detachably connected to a first counterweight block to adjust the levelness of both ends of the platform connected to the support column.

[0025] In some embodiments, a first counterweight seat is disposed on the top or bottom of the platform, and the first counterweight block is detachably connected to the first counterweight seat.

[0026] In some embodiments, a second counterweight block is connected to the frame to adjust the horizontality of the front and rear sides of the frame; a second counterweight seat is provided on the front and rear sides of the frame, and the second counterweight block is detachably connected to the second counterweight seat.

[0027] In some embodiments, the support structure is provided with a slide rail arranged along the length direction of the support structure, and the stand is connected with a pulley, and the pulley can slide on the slide rail.

[0028] In some embodiments, there are multiple slide rails, and the multiple slide rails are arranged in the circumference of the support structure; there are multiple pulleys, and each of the slide rails is slidably connected to at least one pulley.

[0029] In some embodiments, a plurality of guide grooves are provided on the platform, and the support column and the test assembly are both detachably connected to the guide grooves.

[0030] Based on the above-mentioned aircraft landing gear drop shock test device, the present application also provides a test method, comprising the following steps:

[0031] Installing the landing gear on the mounting seat of the gantry;

[0032] Lift the platform to make it suspended in the air; adjust the platform to make it in and maintain a horizontal state, and install a sensor on the platform that maintains a horizontal state, so that the sensor is connected to a signal acquisition device;

[0033] The pavement material is placed in the first cavity to form a first pavement structure, and the test assembly having the first pavement structure is arranged below the stand;

[0034] The platform is adjusted to a preset launch height, and the platform is released, so that the platform falls with the landing gear, so that the landing gear hits the first road surface structure; the sensor senses the signal and transmits the signal to the signal acquisition device for data acquisition.

[0035] In some embodiments, the frame body is connected to the test box body, and the pavement material is placed in the second cavity to form a second pavement structure, and the test assembly with the second pavement structure is arranged below the stand.

[0036] In some embodiments, a test block is connected to the test box to form a metal pavement structure, and the test assembly having the metal pavement structure is arranged below the stand.

[0037] Compared with the prior art, the aircraft landing gear drop shock test device and test method of the present application embodiment have the following beneficial effects:

[0038] The aircraft landing gear drop shock test device and test method of the present application are configured with a test box body that is detachably connected to a connecting seat, and can hold different road materials in the first cavity of the test box body. By replacing the corresponding test box body, different road surface structures such as cement road surface, gravel road surface, etc. can be formed. This enables the aircraft landing gear drop shock test device to conduct simulation experiments on a variety of road conditions, greatly improving the adaptability of the landing gear design.

[0039] Moreover, the aircraft landing gear drop shock test device and test method add a frame body to the outside of the test box body, so that the test components can form a second cavity, and the depth of the second cavity is different from the depth of the first cavity. In this way, the aircraft landing gear drop shock test device and test method can use the second cavity to form road surface structures of different thicknesses, so that the aircraft landing gear drop shock test device and test method have the function of simulating real complex road conditions, further improving the adaptability of the landing gear design.

[0040] Moreover, the aircraft landing gear drop shock test device and test method adjust the horizontality of the two ends of the connection between the test platform and the support column through the first counterweight block, and adjust the horizontality of the front and rear sides of the test platform through the second counterweight block. In this way, under the combined action of the first counterweight block and the second counterweight block, the test platform can adjust its horizontality in the pitch direction and the horizontality in the roll direction, so that it can maintain a horizontal state in the pitch direction and the roll direction, avoiding the test platform from tilting or rolling due to the adjustment of a single counterweight, and effectively improving the efficiency of the test platform leveling.

[0041] Moreover, the aircraft landing gear drop shock test device and test method are provided with a plurality of guide grooves on the platform, and the support columns and the test components are detachably connected to the guide grooves, so that the support columns and the test components can move along the guide grooves, thereby making the distance between two relatively arranged support columns and the distance between each test component adjustable, so that the aircraft landing gear drop shock test device can be universally applicable to test benches of different specifications and sizes, and has high versatility.

[0042] Moreover, the aircraft landing gear drop shock test device and test method provide a first slide rail and a second slide rail on the support column, which cooperate with the first pulley and the second pulley connected to the test stand, so that the test stand can be limited in position by the first pulley and the second pulley, ensuring that the test stand can maintain a consistent posture when it is raised or lowered relative to the support column. The test stand has high repeatable positioning accuracy, which is conducive to repeated testing of the aircraft landing gear drop shock test device and test method, and effectively improves test accuracy and test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1is a schematic diagram of an aircraft landing gear drop shock test device in this application;

[0044] Figure 2 yes Figure 1 A magnified view of middle;

[0045] Figure 3 yes Figure 1 Enlarged view of middle B;

[0046] Figure 4 yes Figure 1 Enlarged view of middle C;

[0047] Figure 5 is a schematic diagram of the test box in this application;

[0048] Figure 6 It is a schematic diagram of the cooperation between the test box body and the frame body in this application;

[0049] Figure 7 is a schematic diagram of the adapter board in this application;

[0050] Figure 8 It is a schematic diagram of the coordination between the scaffold and the support column in this application;

[0051] Fig. 9 It is a schematic diagram of the steps of executing the test method of the aircraft landing gear drop shock test device in this application;

[0052] Fig.10 It is a schematic diagram of the steps of executing another test method of the aircraft landing gear drop shock test device in the present application;

[0053] Fig.11 It is a schematic diagram of the steps of executing another test method of the aircraft landing gear drop shock test device in the present application.

[0054] In the figure, 100 is an aircraft landing gear drop shock test device; 200 is a landing gear; 1 is a platform; 2 is a support column; 3 is a test bench; 4 is a mounting seat; 5 is a test assembly; 5a is a connecting seat; 5b is a test box body; 50b is a first cavity; 5c is a frame body; 50c is a second cavity; 51c is a first frame member; 52c is a second frame member; 6 is a hook; 7 is an electromagnet; 8 is an adapter plate; 9 is an adapter hole; 10 is a connecting hole; 11 is a first support member; 12 is a second support member; 13 is a first counterweight block; 14 is a first counterweight seat; 15 is a second counterweight block; 16 is a second counterweight seat; 17 is a first slide rail; 18 is a first pulley; 19 is a second slide rail; 20 is a second pulley; 21 is a guide groove; 22 is an energy absorption box. DETAILED DESCRIPTION

[0055] The specific implementation methods of the present application are further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present application but are not intended to limit the scope of the present application.

[0056] In the description of the present application, it should be understood that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it may be directly connected to the other element or indirectly connected to the other element. The terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be a direct connection or an indirect connection through an intermediate medium, it may be internal connectivity between two elements or an interactive relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0057] In the description of the present application, it should be understood that the terms "height", "up", "down", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc. used in the present application to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application.

[0058] In the description of this application, it should be understood that the terms "first" and "second" are used in this application for descriptive purposes only, and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "first" and "second" may explicitly or implicitly include one or more of the features.

[0059] refer to Figure 1-8 The present application implements an aircraft landing gear drop shock test device 100, comprising a platform 1, on which a support structure is arranged, wherein the support structure of the present embodiment is two vertically arranged support columns 2, and the two support columns 2 are arranged opposite to each other. A stand 3 is arranged between the two support columns 2.

[0060] In this embodiment, the stand 3 is formed by splicing a plurality of rods, and its outer contour is a rectangular parallelepiped structure. In this embodiment, the left side and the right side are distinguished by the direction indicated by the long side of the rectangular parallelepiped, and the side facing the operator when the operator faces the stand 3 (the left side of the operator is in the same direction as the left side of the stand 3) is defined as the front side, and the side opposite thereto is defined as the rear side, and the upper side and the lower side of the stand 3 when it is generally working normally are defined to distinguish the upper and lower sides.

[0061] refer to Figure 1-2 The left and right sides of the platform 3 are movably connected to the two support columns 2, so that the platform 3 can be guided by the length direction of the support columns 2 and can be raised and lowered relative to the two support columns 2. The front and rear sides of the platform 3 are respectively provided with mounting seats 4 to connect the landing gear 200. The number of landing gears 200 can be configured according to the design of the aircraft, such as two or four. According to the number of landing gears 200, the mounting seats 4 will also be configured on the front and rear sides of the platform 3 in corresponding numbers. In this embodiment, Figure 1 The aircraft landing gear drop test device 100 shown is provided with four mounting seats 4 , wherein two mounting seats 4 are arranged at the front side of the platform 3 , and two mounting seats 4 are arranged at the rear side of the platform 3 .

[0062] A test assembly 5 is installed on the platform 1 to bear the impact of the landing gear 200. The test assembly 5 includes a connection seat 5a and a test box body 5b, wherein the connection seat 5a is set on the platform 1 and arranged between the two support columns 2 and below the bench 3; the test box body 5b is detachably connected to the connection seat 5a, and the test box body 5b is provided with a first cavity 50b with an upward opening to hold the pavement material. Of course, the position where the test assembly 5 is arranged should be compatible with the landing gear 200 to ensure that the landing gear 200 can hit the test assembly 5 or the pavement material filled in the test assembly 5 as the bench 3 falls.

[0063] The lifting and lowering of the platform 3 relative to the support column 2 can be achieved by an external crane. The hook 6 of the crane is connected and fixed to the platform 3 by an electromagnet 7 or a snap connection. The platform 3 can be lifted and lowered along the length direction of the support column 2 by retracting the hook 6 or releasing the hook 6 by the crane.

[0064] By setting up the test component 5, the aircraft landing gear drop shock test device 100 can use the first cavity 50b to construct a variety of different pavement structures. For example, cement is filled in the first cavity 50b to form a cement pavement structure, or soil and grass are filled in the first cavity 50b to form a grass pavement structure, or metal is filled in the first cavity 50b to form a metal pavement structure.

[0065] In this embodiment, the number of test assemblies 5 corresponds to the number of landing gears 200. Figure 1When four landing gears 200 are installed on the test bench 3, four test assemblies 5 are correspondingly installed on the platform 1, wherein two test assemblies 5 are arranged at the front side of the test bench 3, and two test assemblies 5 are arranged at the rear side of the test bench 3. When multiple test assemblies 5 are arranged on the platform 1, the aircraft landing gear drop shock test device 100 can cooperate with multiple test assemblies 5 to form a composite road surface structure. For example, cement is filled in two test assemblies 5 to form a cement road surface structure, and soil and grass are filled in the other two test assemblies 5 to form a grass road surface structure. In this way, the aircraft landing gear drop shock test device 100 can simulate the landing conditions of an aircraft in different real road conditions, and provide more accurate and effective data for the design of the landing gear 200.

[0066] It should be noted that the support structure does not necessarily adopt a structure in which two support columns 2 are arranged relative to each other. In other examples, the support structure may also adopt only one support column 2 to be inserted into the stand 3, and the stand 3 can also be lifted and lowered relative to the support structure along the length direction of the support structure. Of course, the support structure may also adopt three or more support columns 2 to cooperate and provide guidance for the lifting and lowering of the stand 3. The setting principle is the same as that of the present embodiment, and will not be repeated here.

[0067] refer to Figure 1-6 As an example of this embodiment, the test assembly 5 may further include a frame body 5c, which is detachably enclosed on the outside of the test box body 5b and protrudes from the test box body 5b, thereby forming a second cavity 50c with an upward opening with the test box body 5b to accommodate the pavement material.

[0068] By adding the frame body 5c, the aircraft landing gear drop shock test device 100 can use the first cavity 50b and the second cavity 50c to construct a variety of different pavement structures, for example, the first cavity 50b is filled with cement to form a cement pavement structure, or the second cavity 50c is filled with soil and grass to form a grass pavement structure. Of course, the first cavity 50b can also be filled with soil and grass to form a grass pavement structure with different thicknesses, and the second cavity 50c can also be filled with cement to form a cement pavement structure with different thicknesses.

[0069] It should be noted that the test box body 5b and the frame body 5c are both detachable connection designs, and the two do not necessarily have to be used at the same time. In this way, when multiple test components 5 are arranged on the platform 1, the aircraft landing gear drop shock test device 100 can also use multiple test components 5 to cooperate, so as to form road conditions of varying heights. For example, only the test box body 5b is connected between two test components 5 to form a road surface structure with the same height as the first cavity 50b, and the frame body 5c is attached to the outside of the test box body 5b of the other two test components 5 to form a road surface structure with the same height as the second cavity 50c. Moreover, the aircraft landing gear drop shock test device 100 can also fill different road surface materials in each test component 5 to form simulated road conditions with varying heights and different road surface structures.

[0070] In order to facilitate the connection of the frame body 5c to the outer side of the test box body 5b, refer to Figure 6 As an example of this embodiment, the frame body 5c may include a plurality of first frame members 51c and a plurality of second frame members 52c, wherein the plurality of first frame members 51c are sequentially connected along the circumference of the test box body 5b and extend upwardly toward the first cavity 50b, thereby forming a second cavity 50c with an opening facing upward with the test box body 5b; and the plurality of second frame members 52c are detachably connected to two adjacent first frame members 51c to connect and fix the two adjacent first frame members 51c.

[0071] When the outer contour of the test box body 5b is a square structure, the first frame member 51c can be a flat plate structure, so that the first frame member 51c can fit the outer contour of the test box body 5b to prevent the pavement material from leaking out. The first frame member 51c and the test box body 5b, and the second frame member 52c and the first frame member 51c can be connected and fixed by bolts, which will not be repeated here.

[0072] Considering that after the metal body is filled in the first cavity 50b and / or the second cavity 50c, the metal body may be deformed due to the impact of the landing gear 200, making it inconvenient to remove the metal body after the test, as an example of this embodiment, the test assembly 5 of this embodiment may also include a test block (not shown in the figure), which is detachably connected to the connecting seat 5a, and the test block is a metal block, and the same connecting seat 5a connects the test block to one of the test box bodies 5b.

[0073] When the aircraft landing gear drop shock test device 100 needs to use a metal pavement structure for testing, the operator can remove the test box 5b from the connecting seat 5a, and install a test block on the corresponding connecting seat 5a, using the test block as a test tool. Since the test block is generally an integrated structure to ensure that the test block will not be damaged by the landing gear 200, the operator can easily remove the test block from the connecting seat 5a after the impact test.

[0074] In order to facilitate the operator to disassemble and replace the test box body 5b and the test block, an adapter plate 8 may be connected to the connecting seat 5a, and a plurality of adapter holes 9 may be provided on the adapter plate 8. Correspondingly, the test box body 5b and the test block may be provided with connecting holes 10 that can be connected to the adapter holes 9, so that when the operator replaces the test box body 5b and the test block, the test box body 5b and the adapter plate 8, the test block and the adapter plate 8 can be locked and fixed by bolts.

[0075] refer to Figure 1 As an example of this embodiment, the support column 2 is connected to two first support members 11, and the two first support members 11 are respectively arranged at the front and rear sides of the support column 2, and the first support members 11 are inclined to the support column 2 and extend to connect with the platform 1; and the support column 2 is also connected to a second support member 12, and the second support member 12 is arranged on the left and right sides of the support column 2 opposite to the stand 3, and the second support member 12 is also inclined to the support column 2 and extends to connect with the platform 1.

[0076] When the stand 3 is raised or lowered relative to the support column 2, due to a certain matching error between the stand 3 and the support column 2, the stand 3 may exert forces on the front and rear sides and the left and right sides of the support column 2, causing deformation of the support column 2. Through the cooperation of the two first support members 11 and the one second support member 12, a triangular prism structure can be formed on the peripheral side of the support column 2, so that the force exerted by the stand 3 on the support column 2 is dispersed and transmitted to the first support member 11 and the second support member 12, so as to ensure the structural stability of the support column 2.

[0077] It is understandable that before the aircraft landing gear drop shock test device 100 performs the impact test, the platform 3 needs to be adjusted to a horizontal state to simulate the flight landing state of the aircraft. Generally speaking, the platform 3 needs to be balanced in the pitch direction and the roll direction to maintain a horizontal state.

[0078] refer to Figure 1-2 As an example of this embodiment, the first counterweight 13 is detachably connected to the platform 3 to adjust the level of both ends of the platform 3 connected to the support column 2, that is, the level of the left and right sides of the platform 3. According to the inclination of the platform 3, appropriate first counterweights 13 are arranged in the corresponding direction to keep the left and right sides of the platform 3 level. Of course, the number of first counterweights 13 arranged is related to factors such as the weight of the first counterweight 13, the weight of the platform 3, the installation position of the first counterweight 13, and the inclination of the platform 3. The operator can configure it according to the actual situation, which will not be repeated here.

[0079] As an example of this embodiment, a first counterweight seat 14 may be provided at the bottom of the platform 3, and the first counterweight block 13 may be detachably connected to the first counterweight seat 14 by bolt connection or the like. There may be multiple first counterweight seats 14, and multiple first counterweight seats 14 are arranged in the left and right directions of the platform 3, so that the first counterweight block 13 can select a suitable first counterweight seat 14 for installation according to the inclination of the platform 3. Of course, the first counterweight seat 14 may also be provided at the top of the platform 3.

[0080] Considering that the counterweight is only placed on the top or bottom of the platform 3, when adjusting the platform 3, the unbalanced amounts of the platform 3 in the pitch direction and the roll direction are easily coupled together, making the adjustment of the platform 3 difficult, time-consuming and labor-intensive. Figure 1 As an example of this embodiment, a second counterweight 15 may be connected to the platform 3 to adjust the horizontality of the front and rear sides of the platform 3. Under the combined action of the second counterweight 15 and the first counterweight 13, the platform 3 can synchronously adjust its balance in the pitch direction and the roll direction, so that the platform 3 can be quickly adjusted and maintained in a horizontal state.

[0081] As an example of this embodiment, the front and rear sides of the platform 3 are both provided with second counterweight seats 16, and the second counterweight block 15 is detachably connected to the second counterweight seat 16. At this time, the second counterweight block 15 is arranged vertically, and the force point between the second counterweight block 15 and the platform 3 is only the structural member used to connect the second counterweight block 15 and the platform 3, such as a bolt, so that the weight of the second counterweight block 15 can be concentrated on a local position of the platform 3, so that the second counterweight block 15 can more effectively adjust the horizontality of the platform 3. Of course, the number of second counterweight seats 16 can also be multiple, and multiple second counterweight seats 16 are arranged on the front and rear sides of the platform 3, so that the second counterweight block 15 can select a suitable second counterweight seat 16 for installation according to the inclination of the platform 3.

[0082] It should be noted that the first counterweight seat 14 and the second counterweight seat 16 can be structures installed separately on the platform 3, or they can be structures of the platform 3 itself. For example, in this embodiment, the first counterweight seat 14 is a rod of the platform 3, and the second counterweight seat 16 is a mounting plate installed on the platform 3.

[0083] refer to Figure 8As an example of this embodiment, the support structure may be provided with a slide rail arranged along the length direction of the support structure, wherein the number of the slide rails may be multiple, and the multiple slide rails are arranged in the circumference of the support structure; the number of pulleys is correspondingly multiple, and at least one pulley is slidably connected to each slide rail. Specifically, in this embodiment, a first slide rail 17 arranged along the length direction of the support column 2 is provided on the side opposite to the platform 3, and a first pulley 18 is connected to the platform 3, and the first pulley 18 can slide on the first slide rail 17 to realize the movable connection between the platform 3 and the support column 2, so that the platform 3 can be raised and lowered along the length direction of the support column 2.

[0084] Since there may be a certain matching error between the gantry 3 and the support column 2, as an example of this embodiment, the front and rear sides of the support column 2 may also be respectively provided with second slide rails 19 arranged along the length direction of the support column 2, and a second pulley 20 is connected to the gantry 3, and the second pulley 20 can slide on the second slide rail 19. The second pulley 20 cooperates with the first pulley 18, and the second pulley 20 and the first pulley 18 can form a triangular force system to limit the possibility of the gantry 3 moving circumferentially toward the support column 2. The same support column 2 may be provided with multiple first pulleys 18 and multiple second pulleys 20, and the multiple first pulleys 18 and multiple second pulleys 20 are arranged along the length direction of the support column 2. When the first pulley 18 and the second pulley 20 are connected to the first slide rail 17 and the second slide rail 19 respectively, the stand 3 will be constrained so that it can only move along the length direction of the support column 2 and cannot move in the circumferential direction of the support column 2. This allows the stand 3 to always remain in a horizontal state and maintain a consistent posture when it is repeatedly raised and lowered relative to the support column 2.

[0085] When performing a drop test on the landing gear 200, the test bench 3 may have a variety of different specifications to adapt to aircraft of different sizes. Figure 3 As an example of this embodiment, a plurality of guide grooves 21 may be provided on the platform 1, and the support column 2 and the test assembly 5 may be detachably connected to the guide grooves 21. By providing a plurality of guide grooves 21 on the platform 1, and making the support column 2 and the test assembly 5 detachably connected to the guide grooves 21, the support column 2 and the test assembly 5 can move along the guide grooves 21, and thus the spacing between two relatively arranged support columns 2 and the spacing between each test assembly 5 can be adjusted, and the aircraft landing gear drop shock test device 100 can also be adapted to the benches 3 of different sizes, and has high versatility.

[0086] Based on the above-mentioned aircraft landing gear drop shock test device 100, this embodiment also provides a test method for a landing gear 200 drop shock test, referring to Fig. 9 , specifically including the following steps:

[0087] S1. Install landing gears 200 on the mounting seat 4 on the front side of the platform 3 and the mounting seat 4 on the rear side of the platform 3, respectively, so that the front side of the platform 3 is rotatably connected to two landing gears 200, and the rear side of the platform 3 is rotatably connected to two landing gears 200; and each landing gear 200 is provided with an energy absorbing box 22, and the energy absorbing box 22 is in contact with the platform 3;

[0088] S2, installing an electromagnet 7 on the hook 6 of the crane, and adsorbing the top of the gantry 3 by the electromagnet 7, so that the hook 6 is connected and fixed to the gantry 3; controlling the crane to lift the gantry 3, so that the gantry 3 is suspended in the air, at this time, the gantry 3 has no contact with the support column 2;

[0089] S3, adjust the stand 3 so that the stand 3 is in and remains in a horizontal state, and install a sensor on the stand 3 that remains in a horizontal state, so that the sensor is connected to the signal acquisition device, for example, an acceleration sensor is fixedly installed at the center of gravity of the stand 3, and a wire displacement sensor is installed below the center of gravity of the stand 3, wherein the wire end of the wire displacement sensor is fixed to the stand 3, and the other end is fixed to the platform 1;

[0090] S4, placing pavement materials, such as cement, in the first cavity 50b to form a first pavement structure, and arranging the test assembly 5 having the first pavement structure below the stand 3;

[0091] S5. Adjust the platform 3 to a preset launch height, and cut off the power to the electromagnet 7 to release the platform 3, so that the platform 3 and the landing gear 200 fall down, and the landing gear 200 hits the first road surface structure. At this time, the sensor senses signals, such as the acceleration signal of the platform 3, the displacement signal of the landing gear 200, and the impact load signal borne by the landing gear 200, and transmits these signals to the signal acquisition device for data acquisition.

[0092] It is understandable that in step S3, when the aircraft landing gear drop test device 100 is equipped with the first counterweight 13 and the second counterweight 15, the first counterweight 13 and the second counterweight 15 can be configured on the platform 3 accordingly, and the positions of the first counterweight 13 and the second counterweight 15 can be adjusted to make the platform 3 in a horizontal state. In addition, when the aircraft landing gear drop test device 100 is equipped with the first pulley 18, the second pulley 20 and the corresponding slide rail, the first pulley 18 and the second pulley 20 can be adjusted to make the first pulley 18 contact with the first slide rail 17, the second pulley 20 contact with the second slide rail 19, and the first pulley 18 and the second pulley 20 can be locked to keep the platform 3 in a horizontal state.

[0093] According to the different test requirements of landing gear 200, refer to Fig.10As an example of this embodiment, in step S4, this test method can connect the frame body 5c to the test box body 5b, and load the pavement material in the second cavity 50c to form a second pavement structure, and arrange the test assembly 5 with the second pavement structure under the stand 3.

[0094] It is understandable that each test assembly 5 can flexibly configure its own cavity depth and road material according to test requirements, and form a complex simulated road condition through the combination of the first cavity 50b and the second cavity 50c.

[0095] Of course, reference Fig.11 As an example of this embodiment, in step S4, the test method can also connect the test block to the test box body 5b to form a metal pavement structure, and arrange the test assembly 5 with the metal pavement structure under the test bench 3, thereby providing a metal pavement structure that is easy to disassemble for the landing gear 200 drop shock test.

[0096] In summary, the embodiment of the present application provides an aircraft landing gear drop shock test device 100 and a test method. By setting a test box body 5b that is detachably connected to the connecting seat 5a, the first cavity 50b of the test box body 5b can be used to hold different pavement materials, and by replacing the corresponding test box body 5b, different pavement structures can be formed, such as cement pavement, gravel pavement, etc., so that the aircraft landing gear drop shock test device 100 can conduct simulation experiments on various pavement conditions, greatly improving the adaptability of the design of the landing gear 200.

[0097] It should be noted that in the above step S4, different test components 5 of the same aircraft landing gear drop shock test device 100 can adopt different structures to form different simulated road conditions. For example, one test component 5 only adopts a test box body 5b, another test component 5 adopts a matching structure of a test box body 5b and a frame body 5c, and another test component 5 adopts a test block.

[0098] Moreover, the aircraft landing gear drop shock test device 100 and the test method of the present embodiment add a frame body 5c to the outside of the test box body 5b, so that the test component 5 can form a second cavity 50c, and the depth of the second cavity 50c is different from the depth of the first cavity 50b. In this way, the aircraft landing gear drop shock test device 100 and the test method can use the second cavity 50c to form road surface structures of different thicknesses, so that the aircraft landing gear drop shock test device 100 and the test method have the function of simulating real complex road conditions, further improving the adaptability of the design of the landing gear 200.

[0099] Moreover, the aircraft landing gear drop shock test device 100 and the test method of the present embodiment adjust the horizontality of the two ends of the platform 3 connected to the support column 2 through the first counterweight block 13, and adjust the horizontality of the front and rear sides of the platform 3 through the second counterweight block 15. In this way, under the combined action of the first counterweight block 13 and the second counterweight block 15, the platform 3 can adjust its horizontality in the pitch direction and the horizontality in the roll direction, so that it can maintain a horizontal state in the pitch direction and the roll direction, avoiding the platform 3 from tilting or rolling due to the adjustment of a single counterweight, and effectively improving the efficiency of the leveling of the platform 3.

[0100] Moreover, the aircraft landing gear drop shock test device 100 and the test method of this embodiment are provided with a plurality of guide grooves 21 on the platform 1, and the support columns 2 and the test assemblies 5 are detachably connected to the guide grooves 21, so that the support columns 2 and the test assemblies 5 can move along the guide grooves 21, thereby making the distance between two relatively arranged support columns 2 and the distance between each test assembly 5 adjustable, so that the aircraft landing gear drop shock test device 100 can be universally applicable to test stands 3 of different sizes and has high versatility.

[0101] Moreover, the aircraft landing gear drop shock test device 100 and the test method of the present embodiment set the first slide rail 17 and the second slide rail 19 on the support column 2, and cooperate with the first pulley 18 and the second pulley 20 connected to the test stand 3, so that the test stand 3 can be limited in position by the first pulley 18 and the second pulley 20, ensuring that the test stand 3 can maintain a consistent posture when it is raised or lowered relative to the support column 2. The repeatable positioning accuracy of the test stand 3 is high, which is conducive to the aircraft landing gear drop shock test device 100 and the test method to perform repeated tests, and effectively improve the test accuracy and test efficiency.

[0102] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principles of the present application. These improvements and substitutions should also be regarded as the scope of protection of the present application.

Claims

1. An aircraft landing gear drop shock test device, characterized in that: include: platform; A supporting structure is arranged on the platform; A stand, movably connected to the support structure so as to be raised and lowered relative to the support structure; Furthermore, a mounting seat is provided on the platform to connect the aircraft landing gear; A test assembly, used to bear the impact of the landing gear, wherein the test assembly comprises: A connecting seat is provided on the platform and arranged below the stand; The test box body is detachably connected to the connection seat, and the test box body is provided with a first cavity with an upward opening for containing the pavement material.

2. The aircraft landing gear drop shock test device according to claim 1, characterized in that: The test component also includes: The frame body is detachably enclosed on the outer side of the test box body and protrudes from the test box body, thereby forming a second cavity with an upward opening with the test box body to hold the pavement material.

3. The aircraft landing gear drop shock test device according to claim 2, characterized in that: The frame body comprises: A plurality of first frame members, wherein the plurality of first frame members are sequentially connected along the circumference of the test box body and extend upwardly toward the first cavity, thereby forming a second cavity with an upward opening with the test box body; A plurality of second frame members are detachably connected to two adjacent first frame members, so that the two adjacent first frame members are connected and fixed.

4. The aircraft landing gear drop shock test device according to claim 1, characterized in that: The test component also includes: The test block is detachably connected to the connection seat, and the test block is a metal block. The test block and one of the test box bodies are connected to the same connection seat.

5. The aircraft landing gear drop shock test device according to claim 1, characterized in that: There are multiple mounting seats, which are respectively arranged at the front and rear sides of the stand; and there are multiple test assemblies, which are respectively arranged at the front and rear sides of the stand.

6. The aircraft landing gear drop shock test device according to claim 1, characterized in that: The support structure comprises at least two support columns, the two support columns are arranged opposite to each other, and the stand is arranged between the two support columns and is movably connected to the support columns.

7. The aircraft landing gear drop shock test device according to claim 6, characterized in that: The platform is detachably connected with a first counterweight block to adjust the levelness of both ends of the platform connected to the support column.

8. The aircraft landing gear drop shock test device according to claim 7, characterized in that: A first counterweight seat is arranged on the top or bottom of the platform, and the first counterweight block is detachably connected to the first counterweight seat.

9. The aircraft landing gear drop shock test device according to claim 6 or 7, characterized in that: The platform is connected with a second counterweight block to adjust the horizontality of the front and rear sides of the platform; the front and rear sides of the platform are both provided with a second counterweight seat, and the second counterweight block is detachably connected to the second counterweight seat.

10. The aircraft landing gear drop shock test device according to claim 1, characterized in that: The support structure is provided with a slide rail arranged along the length direction of the support structure, and the stand is connected with a pulley, and the pulley can slide on the slide rail; and, There are multiple slide rails, and the multiple slide rails are arranged in the circumference of the support structure; there are multiple pulleys, and each of the slide rails is slidably connected to at least one pulley.

11. A method for testing the drop shock of an aircraft landing gear, characterized in that: The aircraft landing gear drop shock test device according to any one of claims 1 to 10 is applied, comprising the following steps: Installing the landing gear on the mounting seat of the gantry; Lift the platform to make it suspended in the air; adjust the platform to make it in and maintain a horizontal state, and install a sensor on the platform that maintains a horizontal state, so that the sensor is connected to a signal acquisition device; The pavement material is placed in the first cavity to form a first pavement structure, and the test assembly having the first pavement structure is arranged below the stand; The platform is adjusted to a preset launch height, and the platform is released, so that the platform falls with the landing gear, so that the landing gear hits the first road surface structure; the sensor senses the signal and transmits the signal to the signal acquisition device for data acquisition.

12. The aircraft landing gear drop test method according to claim 11, characterized in that: The frame body is connected to the test box body, and the pavement material is placed in the second cavity to form a second pavement structure, and the test assembly with the second pavement structure is arranged below the stand.

13. The aircraft landing gear drop shock test method according to claim 11, characterized in that: A test block is connected to the test box body to form a metal pavement structure, and the test assembly with the metal pavement structure is arranged below the stand.

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