Undercarriage fatigue test device

Abstract

The utility model discloses an undercarriage fatigue test device, and particularly relates to the technical field of undercarriage detection, which comprises a base, four corners of the top end of the base are respectively and fixedly provided with a support rod, the top ends of the four support rods are fixedly provided with a top plate, the bottom of the top plate is provided with a bearing plate, and the bearing plate is provided with a load bearing assembly; the device comprises a top plate and four connecting rods, four fixed guide pipes are fixedly arranged at the bottom end of the top plate, the top ends of the four connecting rods extend into the four fixed guide pipes respectively, a plurality of ball grooves are formed in the inner walls of the fixed guide pipes, and balls are arranged in the ball grooves. According to the utility model, the connecting rod is limited and guided through the fixed guide pipe and the balls, so that the bearing plate and the load-bearing assembly on the bearing plate can be limited and guided, the situation that the bearing plate is blocked during falling is avoided, the impact force in the test is more accurate, and the effect of the anti-impact bearing fatigue test is better.

Description

Technical Field

[0001] This utility model relates to the field of aircraft landing gear testing technology, specifically to a landing gear fatigue testing device. Background Technology

[0002] Landing gear is an accessory device located at the bottom of an aircraft, used to support the aircraft during takeoff, landing, or taxiing on land (or water) and for movement on the ground (or water). The landing gear is the only component that supports the entire aircraft; therefore, it is an indispensable part of the aircraft, without which the aircraft cannot move on the ground. After takeoff, the landing gear can be retracted depending on the aircraft's performance. To accommodate the needs of takeoff, landing rolls, and ground taxiing, the lowest part of the landing gear is equipped with wheels with inflatable tires. To shorten the landing roll distance, the wheels are equipped with brakes or automatic braking systems. Other components include load-bearing struts, shock absorbers (often using the load-bearing struts as the outer casing of the shock absorbers), retraction mechanisms, nose wheel sway dampers, and steering control mechanisms.

[0003] Currently, when conducting load-bearing fatigue tests on aircraft landing gear, most methods involve dropping a heavy object of a certain weight directly onto a fixed aircraft landing gear to simulate the impact load experienced by the aircraft during landing. The fatigue performance is then analyzed based on the impact force experienced by the landing gear. However, the guidance during the drop of the heavy object mostly relies on vertical guide rods passing through the four corners of the heavy object. If the four corners cannot move synchronously during the drop, jamming may occur, which will affect the impact force during the drop and make the test less accurate. Utility Model Content

[0004] The purpose of this invention is to provide a landing gear fatigue testing device to address the aforementioned shortcomings in the technology.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a landing gear fatigue testing device, comprising:

[0006] The base has a support rod fixed at each of the four corners of its top end, a top plate fixed at the top of the four support rods, a load-bearing plate at the bottom of the top plate, and a load-bearing component on the load-bearing plate.

[0007] Four connecting rods are fixedly installed at the four corners of the top of the load-bearing plate. Four fixed guide tubes are fixedly installed at the bottom of the top plate. The top ends of the four connecting rods extend into the four fixed guide tubes. Multiple ball grooves are opened on the inner wall of the fixed guide tubes. Balls are installed inside the ball grooves. The outer ends of the multiple balls are in contact with the outer ends of the connecting rods.

[0008] Preferably, a connecting ring is fixedly provided at the top center of the load-bearing plate to facilitate connection with the hanging assembly above.

[0009] Preferably, the weight-bearing assembly comprises two fixed screws fixed with the top end of the load-bearing plate, the two fixed screws are symmetrically distributed on the load-bearing plate, the outer end of the fixed screw is sleeved with a weight piece, the outer end of the fixed screw is threadedly connected with a limiting ring, and the limiting ring is arranged at the top end of the weight piece, so that the load-bearing plate is provided with the weight.

[0010] Preferably, the top plate is provided with a hydraulic cylinder fixed at the middle of the bottom end, a connecting plate is fixed at the bottom end of the hydraulic cylinder, a hanging assembly is arranged at the bottom end of the connecting plate, and the connecting plate is connected with the connecting hanging ring through the hanging assembly, so that the load-bearing plate can be driven to move upward.

[0011] Preferably, the hanging assembly comprises a movable plate arranged at the bottom end of the connecting plate, a hanging rod is fixed at one side of the movable plate, a limiting frame is fixed at the bottom end of the connecting plate, one end of the hanging rod penetrates through the inside of the connecting hanging ring and extends into the inside of the limiting frame, and an electric push rod is fixed at the bottom end of the connecting plate, and the other side of the movable plate is fixedly connected with the extension end of the electric push rod, so that the load-bearing plate can be hung.

[0012] Preferably, a T-shaped sliding groove is arranged at the bottom end of the connecting plate, and a T-shaped sliding block is arranged in the T-shaped sliding groove, and the bottom end of the T-shaped sliding block is fixedly connected with the top end of the movable plate, so that the movable plate and the hanging rod can be limited and guided.

[0013] Preferably, a placing plate is fixed at the top end of the base, and the central axis of the placing plate coincides with the central axis of the load-bearing plate, so that the aircraft landing gear can be placed.

[0014] In the above technical scheme, the technical effects and advantages of the present application are provided.

[0015] 1. The fixed guide pipe and the ball are used for limiting and guiding the connecting rod, thereby limiting and guiding the load-bearing plate and the weight-bearing assembly thereon, avoiding the jamming of the load-bearing plate during falling, making the impact force in the test more accurate, and improving the effect of the impact resistance bearing fatigue test.

[0016] 2. The number of weight pieces is increased or decreased to adjust the impact degree of the load-bearing plate during falling, so that the adjustment process of the impact degree is simple and convenient, and the impact resistance bearing fatigue test of different aircraft landing gears can be applied, and the applicability is high. DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments or the prior art, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0018] Figure 1It is the whole structure schematic diagram of the utility model;

[0019] Figure 2 It is the whole three-dimensional sectional structure schematic diagram of the utility model;

[0020] Figure 3 It is the fixed guide pipe three-dimensional sectional structure schematic diagram of the utility model Figure 1 ;

[0021] Figure 4 It is the fixed guide pipe three-dimensional sectional structure schematic diagram of the utility model Figure 2 ;

[0022] Figure 5 It is the connecting hanging ring, hydraulic cylinder and connecting plate connecting structure schematic diagram of the utility model;

[0023] Figure 6 It is the connecting plate three-dimensional sectional structure schematic diagram of the utility model;

[0024] Figure 7 It is the fixed screw rod, weight piece and limit ring three-dimensional structure schematic diagram of the utility model.

[0025] Mark explanation:

[0026] 1, base, 2, support rod, 3, top plate, 4, bearing plate, 5, connecting rod, 6, fixed guide pipe, 7, ball groove, 8, ball, 9, connecting hanging ring, 10, fixed screw rod, 11, weight piece, 12, limit ring, 13, hydraulic cylinder, 14, connecting plate, 15, movable plate, 16, hanging rod, 17, limit frame, 18, electric push rod, 19, T-shaped sliding groove, 20, T-shaped sliding block, 21, placing plate. Specific implementation

[0027] In order to make the technical personnel of the prior art better understand the technical scheme of the utility model, the utility model will be introduced further in detail below in conjunction with the drawings.

[0028] The utility model provides a kind of landing gear fatigue test device as Figures 1 to 6 It includes:

[0029] Base 1, base 1 top end four corners are fixedly provided with one support rod 2, four support rods 2 top end are fixedly provided with one top plate 3, and top plate 3 bottom is equipped with bearing plate 4, and bearing plate 4 is equipped with weight assembly;

[0030] Four connecting rods 5 are respectively fixed at the top corners of the bearing plate 4, four fixed guide pipes 6 are fixed at the bottom end of the top plate 3, the top ends of the four connecting rods 5 respectively extend into the interiors of the four fixed guide pipes 6, a plurality of ball grooves 7 are formed on the inner walls of the fixed guide pipes 6, a plurality of balls 8 are arranged in the ball grooves 7, the outer ends of the balls 8 are in contact with the outer ends of the connecting rods 5, and a connecting hanging ring 9 is fixed at the middle of the top end of the bearing plate 4.

[0031] A hydraulic cylinder 13 is fixed at the middle of the bottom end of the top plate 3, a connecting plate 14 is fixed at the bottom end of the hydraulic cylinder 13, a hanging assembly is arranged at the bottom end of the connecting plate 14, and the connecting plate 14 is connected with the connecting hanging ring 9 through the hanging assembly.

[0032] The hanging assembly comprises a movable plate 15 arranged at the bottom end of the connecting plate 14, a hanging rod 16 fixed at one side of the movable plate 15, a limiting frame 17 fixed at the bottom end of the connecting plate 14, one end of the hanging rod 16 penetrating through the interior of the connecting hanging ring 9 and extending into the interior of the limiting frame 17, an electric push rod 18 fixed at the bottom end of the connecting plate 14, the other side of the movable plate 15 being fixedly connected with the extension end of the electric push rod 18, a T-shaped sliding groove 19 formed at the bottom end of the connecting plate 14, and a T-shaped sliding block 20 arranged in the T-shaped sliding groove 19, the bottom end of the T-shaped sliding block 20 being fixedly connected with the top end of the movable plate 15.

[0033] A placing plate 21 is fixed at the top end of the base 1, and the central axis of the placing plate 21 coincides with the central axis of the bearing plate 4.

[0034] The aircraft landing gear is placed at the middle of the top end of the placing plate 21, the electric push rod 18 is started, the movable plate 15 is driven by the electric push rod 18 to move forward, the hanging rod 16 is driven by the movable plate 15 to move forward and drive the T-shaped sliding block 20 to move in the T-shaped sliding groove 19, one end of the hanging rod 16 is separated from the limiting frame 17 and the interior of the connecting hanging ring 9, the bearing plate 4 is driven by the gravity of the weight bearing assembly to move downward, the four connecting rods 5 at the top end of the bearing plate 4 are drawn out of the interiors of the fixed guide pipes 6, the connecting rods 5 and the fixed guide pipes 6 position and guide the bearing plate 4, the bearing plate 4 can thus fall above the aircraft landing gear to impact and bear the test of the aircraft landing gear, after one impact, the connecting plate 14 is driven by the hydraulic cylinder 13 to move downward, one end of the hanging rod 16 is driven by the electric push rod 18 to penetrate through the interior of the connecting hanging ring 9, the bearing plate 4 can thus be pulled up by the hydraulic cylinder 13 to perform the next impact test.

[0035] The utility model discloses a fixed guide pipe 6 and ball 8 are used to carry out the positioner of connecting rod 5, and then can carry out the positioner of bearing plate 4 and the heavy load component on it, avoid the bearing plate 4 when falling and appear the situation of jam, make the impact force in the test is more accurate, and the effect of impact bearing fatigue test is better, the embodiment specifically solves the aircraft landing gear in the prior art when carrying out bearing capacity fatigue test, it is mostly using certain weight weight directly falls to the fixed aircraft landing gear to imitate the impact bearing capacity that the aircraft landing is received, then according to the impact force that landing gear is received to analyze its fatigue performance, but the guidance when the weight falls mostly is through the weight four corners by vertical guide rod, and if four corners can not move synchronously when the weight falls, possibly will appear the situation of jam, this will influence the impact force when the weight falls, make the test not accurate enough.

[0036] The utility model provides a landing gear fatigue test device as Figure 5 And Figure 7 The utility model discloses a landing gear fatigue test device, heavy load component includes two fixed screw rod 10 of fixedly equipped with bearing plate 4 top, two fixed screw rod 10 is distributed on bearing plate 4 symmetry, and fixed screw rod 10 outer end is equipped with heavy load piece 11, and fixed screw rod 10 outer end is connected with a limit ring 12 with screw thread, and limit ring 12 is equipped at heavy load piece 11 top.

[0037] When needing to adjust the impact degree, the limit ring 12 is unscrewed from the top end of the fixed screw rod 10, and then the number of the heavy load pieces 11 is increased or decreased to change the weight of the bearing plate 4 and the heavy load component, so that the impact degree when the bearing plate 4 falls can be changed, and the impact degree when the bearing plate 4 falls is adjusted by increasing or decreasing the number of the heavy load pieces 11, so that the adjustment process of the impact degree is relatively simple and convenient, and then the impact bearing fatigue test of different aircraft landing gears can be applied, and the applicability is relatively high.

[0038] The above only describes some exemplary embodiments of the utility model in a descriptive manner, without doubt, for ordinary skilled in the art, under the condition that deviating from the spirit and scope of the utility model, the described embodiments can be modified in various different ways. Therefore, the above drawings and description are illustrative in nature and should not be understood as limiting the scope of protection of the utility model claims.

Claims

1. A landing gear fatigue test apparatus characterized by comprising: Include: Base (1), the base (1) top four corners are respectively provided with a support rod (2), four support rods (2) top fixedly provided with a top plate (3), the bottom of the top plate (3) is provided with a bearing plate (4), the bearing plate (4) is provided with a weight bearing assembly; Four connecting rods (5), four connecting rods (5) are respectively fixedly provided at the top of the bearing plate (4), the bottom of the top plate (3) is fixedly provided with four fixed guide tubes (6), the top of the four connecting rods (5) extends into the inside of the four fixed guide tubes (6) respectively, a plurality of ball grooves (7) are formed in the inner wall of the fixed guide tube (6), the ball grooves (7) are provided with a plurality of balls (8), and the outer ends of the plurality of balls (8) are in contact with the outer ends of the connecting rods (5).

2. The landing gear fatigue test apparatus according to claim 1, characterized by: The top of the bearing plate (4) is fixedly provided with a connecting hanging ring (9).

3. A landing gear fatigue test apparatus according to claim 2, characterised in that: The weight bearing assembly comprises two fixed screw rods (10) fixedly provided at the top of the bearing plate (4), the two fixed screw rods (10) are symmetrically distributed on the bearing plate (4), the outer end of the fixed screw rod (10) is provided with a weight bearing sheet (11), the outer end of the fixed screw rod (10) is threadedly connected with a limiting ring (12), and the limiting ring (12) is arranged at the top of the weight bearing sheet (11).

4. The landing gear fatigue test apparatus of claim 2, wherein: The bottom of the top plate (3) is fixedly provided with a hydraulic cylinder (13), the bottom of the hydraulic cylinder (13) is fixedly provided with a connecting plate (14), the bottom of the connecting plate (14) is provided with a hanging assembly, and the connecting plate (14) is connected with the connecting hanging ring (9) through the hanging assembly.

5. A landing gear fatigue test apparatus according to claim 4, characterised in that: The hanging assembly comprises a movable plate (15) arranged at the bottom of the connecting plate (14), a hanging rod (16) is fixedly arranged on one side of the movable plate (15), a limiting frame (17) is fixedly arranged at the bottom of the connecting plate (14), one end of the hanging rod (16) penetrates through the inside of the connecting hanging ring (9) and extends into the inside of the limiting frame (17), and an electric push rod (18) is fixedly arranged at the bottom of the connecting plate (14). The other side of the movable plate (15) is fixedly connected with the telescopic end of the electric push rod (18).

6. A landing gear fatigue test apparatus according to claim 5, wherein: A T-shaped sliding groove (19) is formed in the bottom of the connecting plate (14), a T-shaped sliding block (20) is arranged in the T-shaped sliding groove (19), and the bottom of the T-shaped sliding block (20) is fixedly connected with the top of the movable plate (15).

7. The landing gear fatigue test apparatus of claim 1, wherein: The top of the base (1) is fixedly provided with a placing plate (21), and the central axis of the placing plate (21) coincides with the central axis of the bearing plate (4).

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