Strength testing device for fixed-wing aircraft landing gear

Abstract

The utility model discloses a strength testing device for an undercarriage of a fixed-wing aircraft, and relates to the technical field of aircraft production testing equipment. According to the technical scheme, the automatic feeding device is characterized by comprising a base, a material containing base is arranged on the surface of the base, vertical guide columns are arranged on the portions, located on the two sides of the material containing base, of the surface of the base, the automatic feeding device further comprises a heavy block, the heavy block is provided with guide grooves allowing the guide columns to penetrate through and be in sliding connection, and the automatic feeding device further comprises a control mechanism used for controlling the heavy block to ascend and fall off. The utility model aims to provide a strength testing device for a fixed-wing aircraft landing gear.

Description

Technical Field

[0001] This utility model relates to aircraft production testing equipment, and more specifically, it relates to a strength testing device for the landing gear of a fixed-wing aircraft. Background Technology

[0002] Fixed-wing aircraft, also known as fixed-wing unmanned aerial vehicles (UAVs), are a type of fixed-wing micro-UAVs. They are widely used due to their low noise and good stealth capabilities. The main landing gear is the landing gear component that bears the main load when the aircraft is parked, taxiing, taking off, or landing on the ground.

[0003] Since the main landing gear is the main supporting component of an aircraft during flight or landing, it needs to bear the weight of the aircraft itself and even greater weight during landing. Therefore, the design requirements for the impact resistance of the main landing gear are particularly strict. After each aircraft's main landing gear is manufactured, it needs to undergo rigorous impact resistance testing. The design of the impact resistance testing equipment is related to whether each landing gear can be put into flight use.

[0004] Chinese patent CN211108070U discloses an impact resistance testing device for aircraft main landing gear, including a testing platform and main landing gear. Four sets of support columns are set at the upper part of the testing platform. Threaded rods are longitudinally inserted into the support columns. A partition is set near the bottom of the inner cavity of the support column. A first motor is set at the lower end of the partition. A ring is threaded onto the outer side of the threaded rod at the upper end of the support column. A top plate is fixedly connected between the rings. An electromagnet is fixedly set at the lower end of the top plate. A weight is set at the lower end of the electromagnet. A second motor is set at the upper part of the top plate. A motor shaft is set at the power end of the second motor. A rope is fixedly connected to the outer end of the motor shaft. A connecting block is fixedly connected to the inner side of the support column. A sliding groove is opened longitudinally in the connecting block, and a protective door is slidably inserted into the groove.

[0005] When the above technical solution is tested, the gravity block detaches from the equipment after being released, and its position after falling is uncertain. When testing is required again, it needs to be manually reset to the designated position, which results in high labor costs and reduced testing efficiency.

[0006] Therefore, a new technical solution is urgently needed to solve the above-mentioned technical problems. Utility Model Content

[0007] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide a strength testing device for the landing gear of fixed-wing aircraft.

[0008] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a strength testing device for the landing gear of a fixed-wing aircraft, comprising a base, a material placement seat on the surface of the base, vertical guide columns on both sides of the material placement seat on the surface of the base, a weight, a guide groove for the guide columns to pass through and slide through, and a control mechanism for controlling the weight to rise and fall.

[0009] The present invention is further configured such that: the control mechanism includes a guide sleeve sleeved and slidably connected to the guide post, the two guide sleeves are located above the weight, a connecting rod is fixedly connected between the two guide sleeves, the connecting rod is provided with a gripping component for gripping the weight, and a driving component for controlling the lifting and lowering of the connecting rod.

[0010] The present invention is further configured such that: the gripping assembly includes a rotating sleeve sleeved and rotatably connected to the connecting rod, the rotating sleeve is provided with an arc-shaped gripping plate, and also includes a driving component for driving the rotating sleeve; fixed blocks are provided at both ends of the upper surface of the weight, and a fixed rod that cooperates with the gripping plate is provided between the two fixed blocks; the driving component drives the gripping plate so that its inner surface is placed below the fixed rod.

[0011] The present invention is further configured such that: the driving component includes a first motor disposed at one end of the surface of the connecting rod, the output shaft of the first motor is provided with a gear, and the circumferential surface of one end of the rotating sleeve is provided with a toothed ring meshing with the gear.

[0012] The present invention is further configured such that: vertical support plates are provided at both ends of the surface of the base, a top plate is fixedly connected between the tops of the two support plates, and side plates are fixedly connected at both ends of the surface of the top plate; the driving assembly includes a take-up roller rotatably connected between the two side plates; a second motor for driving the take-up roller is provided on one side of the side plate; two sets of pull ropes are wound on the take-up roller, and one end of each pull rope passes through the top plate and is fixedly connected to both ends of a connecting rod.

[0013] This invention has the following advantages: Before testing the landing gear, the control mechanism drives the weight to rise to a specified height along the guide column. Then, the landing gear is placed on the placement seat. The control structure separates the weight from the control mechanism, and the weight falls freely along the guide column under its own action, thus testing the strength of the landing gear. After the test is completed, the horizontal position of the weight does not change. It can be raised to a specified height again by the control mechanism for subsequent testing, saving labor costs and improving testing efficiency. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of this embodiment;

[0015] Figure 2 This is a schematic diagram of the structure of the heavy block in this embodiment;

[0016] Figure 3 This is a schematic diagram of the rotating sleeve mechanism in this embodiment;

[0017] Figure 4 This is a schematic diagram of the guide sleeve and connecting rod in this embodiment.

[0018] Attached diagram descriptions: 1. Base; 2. Material placement seat; 3. Guide column; 4. Weight; 5. Guide sleeve; 6. Connecting rod; 7. Rotating sleeve; 8. Gripping plate; 9. Fixing block; 10. Fixing rod; 11. First motor; 12. Gear; 13. Gear ring; 14. Support plate; 15. Top plate; 16. Side plate; 17. Take-up roller; 18. Second motor; 19. Pull rope. Detailed Implementation

[0019] The present invention will be further described in detail below with reference to the accompanying drawings.

[0020] Identical parts are indicated by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "up," and "down" used in the following description refer to directions in the accompanying drawings, while the terms "bottom surface," "top surface," "inner," and "outer" refer to directions toward or away from the geometric center of a specific part, respectively.

[0021] As shown in the figure, a strength testing device for landing gear of fixed-wing aircraft includes a base 1, a material placement seat 2 is provided on the surface of the base 1, vertical guide columns 3 are provided on both sides of the material placement seat 2 on the surface of the base 1, a weight 4 is provided, the weight 4 has a guide groove for the guide columns 3 to pass through and slide, and a control mechanism for controlling the weight 4 to rise and fall.

[0022] Before testing the landing gear, the control mechanism raises the weight 4 along the guide post 3 to a specified height. Then, the landing gear is placed on the support seat 2. The control structure separates the weight 4 from the control mechanism, and it falls freely along the guide post 3 under its own action to test the strength of the landing gear. After the test, the horizontal position of the weight 4 does not change. It can be raised to the specified height again by the control mechanism for subsequent testing, saving manpower costs and improving testing efficiency.

[0023] The control mechanism includes a guide sleeve 5 that is sleeved and slidably connected to the guide post 3. The two guide sleeves 5 are located above the weight 4. A connecting rod 6 is fixedly connected between the two guide sleeves 5. A gripping component for gripping the weight 4 is provided on the connecting rod 6. The mechanism also includes a drive component for controlling the lifting and lowering of the connecting rod 6.

[0024] The gripping assembly includes a rotating sleeve 7 that is sleeved and rotatably connected to the connecting rod 6. The rotating sleeve 7 is provided with an arc-shaped gripping plate 8. It also includes a driving component for driving the rotating sleeve 7. Fixed blocks 9 are provided at both ends of the upper surface of the weight 4. A fixed rod 10 that cooperates with the gripping plate 8 is provided between the two fixed blocks 9. The driving component drives the gripping plate 8 so that its inner surface is placed below the fixed rod 10.

[0025] After the drive assembly lowers the guide sleeve 5 and connecting rod 6 to a certain height, the drive unit drives the rotating sleeve 7 to rotate, causing the gripping plate 8 to rotate below the fixed rod 10. The drive assembly then drives the connecting rod 6 to rise, and the inner surface of the gripping plate 8 abuts against the bottom of the connecting rod 6, thereby causing the weight 4 to rise synchronously. After rising to a certain height and placing the landing gear to be tested, the drive unit drives the rotating sleeve 7 to rotate, causing the gripping plate 8 to separate from the connecting rod 6, and the weight 4 to fall.

[0026] The driving component includes a first motor 11 disposed at one end of the surface of the connecting rod 6. The output shaft of the first motor 11 is provided with a gear 12. The circumferential surface of one end of the rotating sleeve 7 is provided with a toothed ring 13 that meshes with the gear 12. The first motor 11 drives the rotating sleeve 7 to rotate through the gear 12 and the toothed ring 13, and controls the angle position of the gripping plate 8, thereby driving the weight 4 to rise and fall.

[0027] Vertical support plates 14 are provided at both ends of the surface of the base 1. A top plate 15 is fixedly connected between the tops of the two support plates 14. Side plates 16 are fixedly connected to both ends of the surface of the top plate 15. The driving assembly includes a take-up roller 17 rotatably connected between the two side plates 16. A second motor 18 for driving the take-up roller 17 is provided on one side of the side plate 16. Two sets of pull ropes 19 are wound on the take-up roller 17. One end of each pull rope 19 passes through the top plate 15 and is fixedly connected to both ends of the connecting rod 6. The second motor 18 controls the winding and unwinding of the pull ropes 19 by driving the rotation of the take-up roller 17, thereby controlling the rising and falling of the connecting rod 6.

[0028] The specific embodiments are merely explanations of this utility model and are not intended to limit it. After reading this specification, those skilled in the art can make modifications to these embodiments without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this utility model.

Claims

1. A strength testing apparatus for a fixed wing aircraft landing gear, characterized by: The device includes a base (1), a material placement seat (2) on the surface of the base (1), vertical guide columns (3) on both sides of the material placement seat (2) on the surface of the base (1), a weight (4) with a guide groove for the guide column (3) to pass through and slide, and a control mechanism for controlling the weight (4) to rise and fall.

2. The strength testing device for landing gear of a fixed-wing aircraft according to claim 1, characterized in that: The control mechanism includes a guide sleeve (5) sleeved and slidably connected to the guide post (3), two guide sleeves (5) located above the weight (4), a connecting rod (6) fixedly connected between the two guide sleeves (5), a gripping component for gripping the weight (4) provided on the connecting rod (6), and a drive component for controlling the lifting and lowering of the connecting rod (6).

3. A strength testing device for a fixed-wing aircraft landing gear as defined in claim 2, wherein: The gripping assembly includes a rotating sleeve (7) sleeved and rotatably connected to the connecting rod (6), an arc-shaped gripping plate (8) is provided on the rotating sleeve (7), and a driving component for driving the rotating sleeve (7). Fixed blocks (9) are provided at both ends of the upper surface of the weight (4), and a fixed rod (10) that cooperates with the gripping plate (8) is provided between the two fixed blocks (9). The driving component drives the gripping plate (8) so that its inner surface is placed below the fixed rod (10).

4. A strength testing device for a fixed wing aircraft landing gear as defined in claim 3, wherein: The driving component includes a first motor (11) disposed at one end of the surface of the connecting rod (6), the output shaft of the first motor (11) is provided with a gear (12), and the circumferential surface of one end of the rotating sleeve (7) is provided with a toothed ring (13) meshing with the gear (12).

5. A strength testing device for a fixed wing aircraft landing gear as defined in claim 4, wherein: Vertical support plates (14) are provided at both ends of the surface of the base (1). A top plate (15) is fixedly connected between the tops of the two support plates (14). Side plates (16) are fixedly connected at both ends of the surface of the top plate (15). The driving assembly includes a take-up roller (17) rotatably connected between the two side plates (16). A second motor for driving the take-up roller (17) is provided on one side of the side plate (16). Two sets of pull ropes (19) are wound on the take-up roller (17). One end of each pull rope (19) passes through the top plate (15) and is fixedly connected to both ends of the connecting rod (6).

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