Aircraft landing gear testing device

Abstract

The utility model discloses a testing device of an aircraft landing gear, which comprises a box body, an adjustable support is arranged below the box body, and the adjustable support is used for adjusting the height of the box body; a cross beam is arranged in the box body, a supporting plate is arranged below the cross beam, a fixing assembly is arranged between the supporting plate and the side face of the box body, the fixing assembly is connected with a shaft body of the undercarriage, the box body is provided with an opening face, the opening face of the box body is of an inclined structure, and the undercarriage enters the box body through the opening face of the box body. The internal structure of the undercarriage storage bin is simulated through the box body, and the undercarriage is fixed by arranging the cross beam, the supporting plate and the fixing assembly in the box body, so that the actual working conditions of installation and movement of the undercarriage on the undercarriage storage bin can be simulated, and the actual movement condition of the undercarriage on the undercarriage storage bin can be observed; the mechanical problem when the undercarriage is folded and unfolded on the aircraft undercarriage storage bin can be conveniently found in time, and the box body is simple in structure and low in manufacturing cost.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft landing gears, and in particular relates to a testing device for aircraft landing gears. Background Art

[0002] The landing gear of an aircraft is an essential and important component for fixed-wing aircraft. Usually, the landing gear is retracted into the aircraft compartment when the aircraft takes off. When the aircraft needs to descend and land, the landing gear is extended from the compartment and fixed so that the aircraft can taxi on the runway. Therefore, the retraction and extension test of the landing gear is very important. It is necessary to test the retraction and extension function of the landing gear on the ground, and at the same time, it is necessary to make structural adjustments to the aircraft's landing gear compartment. Traditional landing gear test experiments only adjust the structure of the landing gear itself, without fully considering whether the matching relationship between the landing gear and the landing gear compartment is appropriate. Therefore, there are great safety hazards in the actual operation process. Utility Model Content

[0003] The utility model aims to provide a testing device for an aircraft landing gear, which can set the landing gear in a test box, simulate the aircraft landing gear storage compartment through the box, and make the landing gear perform retractable and retractable movements on the box, so as to intuitively detect the coordination effect between the landing gear and the internal structure of the box.

[0004] The utility model is realized by the following technical solutions:

[0005] A testing device for an aircraft landing gear comprises a box body, wherein an adjustable bracket is arranged below the box body, and the adjustable bracket is used to adjust the height of the box body; at least one crossbeam is arranged inside the box body, and the crossbeam is connected to a hydraulic assembly of the landing gear; a support plate is arranged below the crossbeam, and the support plate is connected to an end of a connecting rod mechanism of the landing gear; a fixing assembly is arranged between the support plate and a side surface of the box body, and the fixing assembly is connected to an axle body of the landing gear; an opening surface is arranged on the box body, and the angle between the opening surface of the box body and the horizontal plane of the bottom of the box body is 120 degrees; the landing gear enters the box body through the opening surface of the box body, and the box body is used to store the landing gear.

[0006] Furthermore, the fixing assembly includes a fixing beam and a connecting plate, the fixing beam is arranged between the supporting plate and the side surface of the box body, the connecting plate is connected to the fixing beam, and the shaft body of the landing gear is connected to the fixing beam.

[0007] Furthermore, a baffle assembly is arranged on the opening surface of the box body, and the baffle assembly includes a first baffle, and the first baffle is hinged to the upper edge of the opening surface.

[0008] Furthermore, the baffle assembly includes a second baffle, which is arranged on one side of the first baffle, the second baffle is hinged to the side edge of the opening surface, and the first baffle and the second baffle cooperate to close the box.

[0009] Furthermore, the height of the second baffle is greater than the height of the first baffle.

[0010] Furthermore, a limit plate is provided below the support plate, and the limit plate is used to limit the landing gear.

[0011] Furthermore, reinforcing ribs are arranged inside the box.

[0012] Compared with the prior art, the utility model has the following advantages and beneficial effects:

[0013] In the utility model, the internal structure of the aircraft landing gear storage bin is simulated by a box body, and a crossbeam, a support plate and a fixing assembly are arranged in the box body to fix the landing gear, so that the actual working conditions of the installation and movement of the landing gear on the aircraft landing gear storage bin can be simulated. By observing the retraction and extension movement of the landing gear on the box body, the actual movement of the landing gear on the aircraft landing gear storage bin can be observed, which is convenient for timely discovering mechanical problems when the landing gear is retracted and extended on the aircraft landing gear storage bin, so as to avoid unexpected situations during the actual operation of the landing gear. The box body has a simple structure and low manufacturing cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0015] Figure 1 The figure is a schematic diagram of the internal structure of the test device for aircraft landing gear of the utility model.

[0016] Figure 2 The utility model is a schematic diagram of the box structure of the test device for aircraft landing gear.

[0017] Among them: 1-box, 11-opening surface, 111-first baffle, 112-second baffle, 2-adjustable bracket, 3-cross beam, 4-support plate, 5-fixed component, 51-fixed beam, 52-connecting plate, 6-landing gear, 61-axle body, 62-hydraulic component, 63-connecting rod mechanism, 64-wheel hub, 7-reinforcement rib. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solutions and advantages of the embodiments of the utility model clearer, the technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments.

[0019] Embodiment 1:

[0020] The main structure of this embodiment is a testing device for aircraft landing gear, such as Figure 1 As shown, it includes a box body 1, an adjustable bracket 2 is arranged below the box body 1, and the adjustable bracket 2 is used to adjust the height of the box body 1; at least one crossbeam 3 is arranged in the box body 1, and the crossbeam 3 is connected to the hydraulic assembly 62 of the landing gear 6, a support plate 4 is arranged below the crossbeam 3, and the support plate 4 is connected to the end of the connecting rod mechanism 63 of the landing gear 6, a fixing assembly 5 is arranged between the support plate 4 and the side of the box body 1, and the fixing assembly 5 is connected to the shaft 61 of the landing gear 6, an opening surface 11 is arranged on the box body 1, and the angle between the opening surface 11 of the box body 1 and the horizontal plane of the bottom of the box body 1 is 120°, and the landing gear 6 enters the box body 1 through the opening surface 11 of the box body 1, and the box body 1 is used to store the landing gear 6; a reinforcing rib 7 is arranged in the box body 1; a limiting plate is arranged below the support plate 4, and the limiting plate is used to limit the landing gear 6.

[0021] The aircraft landing gear test device includes a box body 1, the surface of the box body 1 is provided with a skin, the box body 1 is used to simulate the storage compartment of the aircraft landing gear 6, and to perform relevant tests on the retraction and extension of the aircraft landing gear 6; an adjustable bracket is provided under the box body 1, and the bracket can adjust the box body 1 up and down to adapt to the length of the landing gear 6; preferably, two cross beams 3 are provided in the box body 1, and the two cross beams 3 are arranged at intervals, the end of the hydraulic assembly 62 of the landing gear 6 is hinged to the cross beam 3, and a support plate 4 is provided under the cross beam 3, and the connecting rod mechanism on the landing gear 6 The end of 63 is hinged to the support plate 4, and a fixing assembly 5 is provided on the right side of the support plate 4. The fixing assembly 5 is relatively fixed in the box body 1. The shaft 61 of the landing gear 6 is hinged to the fixing assembly 5, and the other end of the connecting rod assembly is also hinged to the fixing assembly 5, so that the landing gear 6 can complete the opening and closing action in the box body 1, and the landing gear 6 can be retracted and extended; preferably, one side of the box body 1 is provided with an opening surface 11 of an opening structure, and the opening surface 11 is an inclined structure, and the inclination angle of the opening surface 11 relative to the horizontal plane is 120°. In order to improve the stability of the box body 1, a reinforcing rib 7 is provided on the inner surface of the box body 1, which can keep the box body 1 rigid and prevent it from deformation, and a limiting plate is provided under the support plate 4. When the landing gear 6 is retracted into the box body 1, the side of the limiting plate will limit the landing gear 6 to prevent it from being over-tightened in the box body 1 and causing damage to the landing gear 6.

[0022] Embodiment 2:

[0023] Based on the above embodiments, this embodiment further defines a fixing component 5, which includes a fixing beam 51 and a connecting plate 52. The fixing beam 51 is arranged between the support plate 4 and the side of the box body 1, the connecting plate 52 is connected to the fixing beam 51, and the shaft 61 of the landing gear 6 is connected to the fixing beam 51.

[0024] Preferably, the fixing assembly 5 includes a fixing beam 51 and a connecting plate 52, the connecting plate 52 is arranged below the fixing beam 51, the fixing beam 51 is preferably a cross structure, one end of the fixing beam 51 is connected to the side of the box body 1, and the other end is connected to the support plate 4, and the other end of the connecting rod assembly and the shaft 61 of the landing gear 6 are both hinged to the connecting plate 52, so that the landing gear 6 can rotate on the connecting plate 52. The other parts of this embodiment are the same as the above embodiment, and will not be repeated here.

[0025] Embodiment 3:

[0026] Based on the above embodiment, this embodiment further adds a baffle assembly, such as Figure 2 As shown, a baffle assembly is provided on the opening surface 11 of the box body 1, and the baffle assembly includes a first baffle 111, and the first baffle 111 is hinged to the upper edge of the opening surface 11; the baffle assembly includes a second baffle 112, and the second baffle 112 is provided on one side of the first baffle 111, and the second baffle 112 is hinged to the side edge of the opening surface 11, and the first baffle 111 and the second baffle 112 cooperate to close the box body 1; the height of the second baffle 112 is greater than the height of the first baffle 111.

[0027] Preferably, a baffle assembly is provided on the opening surface 11 of the box body 1, and the baffle assembly includes a first baffle 111 and a second baffle 112, both of which are used to close the opening surface 11 of the box body 1, and the landing gear 6 is preferably provided at a position corresponding to the inner side of the first baffle 111, and the first baffle 111 is hinged to the upper side of the opening surface 11 of the box body 1 to form a flip opening structure; the second baffle 112 is provided on the left side of the first baffle 111, and the second baffle 112 is hinged to the side edge of the opening surface 11 of the box body 1, and the height of the second baffle 112 is higher than the height of the first baffle 111, and when the landing gear 6 enters the box body 1, its wheel hub 64 enters the box body 1 from the position of the second baffle 112, so it is necessary to enlarge the second baffle 112 and the opening size corresponding to the second baffle 112, so as to facilitate the wheel hub 64 of the landing gear 6 to enter the box body 1. The other parts of this embodiment are the same as the above embodiment, and will not be repeated here.

[0028] In the description of the present utility model, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. used to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the utility model product is usually placed when used. They are only for the convenience of describing the present utility model and simplifying the description, and do not indicate or imply 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 utility model.

[0029] In addition, if the terms "horizontal" or "vertical" appear in the description of the present invention, it does not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0030] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it 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 a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A testing device for aircraft landing gear, characterized in that: It comprises a box body, an adjustable bracket is arranged below the box body, and the adjustable bracket is used to adjust the height of the box body; at least one crossbeam is arranged inside the box body, and the crossbeam is connected to the hydraulic assembly of the landing gear; a support plate is arranged below the crossbeam, and the support plate is connected to the end of the connecting rod mechanism of the landing gear; a fixing assembly is arranged between the support plate and the side of the box body, and the fixing assembly is connected to the shaft body of the landing gear; an opening surface is arranged on the box body, and the angle between the opening surface of the box body and the horizontal plane of the bottom of the box body is between 120° and 130°, and the landing gear enters the box body through the opening surface of the box body, and the box body is used to store the landing gear.

2. The aircraft landing gear testing device according to claim 1, characterized in that: The fixing assembly comprises a fixing beam and a connecting plate, wherein the fixing beam is arranged between the supporting plate and the side surface of the box body, the connecting plate is connected to the fixing beam, and the shaft body of the landing gear is connected to the fixing beam.

3. The aircraft landing gear testing device according to claim 1, characterized in that: A baffle assembly is arranged on the opening surface of the box body, and the baffle assembly includes a first baffle, and the first baffle is hinged to the upper edge of the opening surface.

4. The aircraft landing gear testing device according to claim 3, characterized in that: The baffle assembly comprises a second baffle, which is arranged on one side of the first baffle and is hinged to the side edge of the opening surface. The first baffle cooperates with the second baffle to close the box.

5. The aircraft landing gear testing device according to claim 4, characterized in that: The height of the second baffle is greater than that of the first baffle.

6. The aircraft landing gear testing device according to claim 1, characterized in that: A limiting plate is arranged below the supporting plate, and the limiting plate is used for limiting the position of the landing gear.

7. The aircraft landing gear testing device according to claim 1, characterized in that: Reinforcing ribs are arranged in the box body.

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