An aircraft landing gear connecting bolt assembly

Abstract

The utility model relates to aviation bolt technical field discloses an aviation landing gear connecting bolt assembly, including bolt, arc rod and clamping seat, the top of bolt is provided with hexagonal hole, the inside insertion of hexagonal hole has hexagonal block, both ends of hexagonal block all are fixedly connected with fixed strip, the other end of fixed strip rotatably connects with the pivot, the surface of arc rod is provided with the clamping groove, the inner wall of clamping groove is fixedly connected with the pivot, the lower end outer wall of arc rod is fixedly connected with the clamping block, the utility model has the beneficial effect that: through bolt thread connection and arc rod clamping seat's mechanical clamping structure, makes bolt even wear, arc rod and clamping sleeve ring, clamping groove's cooperation still can fix bolt position, avoids its from screw hole and falls off, guarantees landing gear support function, the clamping block and clamping sleeve ring pasting surface design is cambered surface, can closely paste and scatter vibration stress, clamping seat and bolt coaxial arrangement, stress is even, reduces the component loss due to the alternating load, prolongs the life.

Description

Technical Field

[0001] This utility model relates to the field of aviation bolt technology, specifically to an aviation landing gear connecting bolt assembly. Background Technology

[0002] Aviation bolts are core fastening components for structural connections in aerospace vehicles. They are mainly used in critical parts such as fuselage frames, engine nacelles, wing-fuselage connections, and landing gear. They must withstand extreme working conditions (such as high temperature, high pressure, vibration, and alternating loads) while meeting the requirements of lightweight, high strength, high reliability, and long service life. Their performance directly affects the structural safety and flight stability of aviation equipment.

[0003] For example, a double-eared bracket bolt for aviation, disclosed in CN117231613A, uses a movable design between the bracket component and the nut component to balance thermal expansion and contraction caused by temperature changes, reducing deformation and loosening of the connection parts caused by thermal expansion and contraction. When an aircraft lands, the landing gear must keep the bolts fixed in the screw holes to prevent the landing gear from failing to support the aircraft's stable landing. When the threads of the aviation bolts are severely worn, the aviation bolts are still easily dislodged from the screw holes by vibration, which can lead to landing gear damage and make it impossible to guarantee the safe landing of the aircraft. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft landing gear connecting bolt assembly to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an aircraft landing gear connecting bolt assembly, comprising a bolt, an arc rod, and a locking seat. The bolt has a hexagonal hole at its top, into which a hexagonal block is inserted. Both ends of the hexagonal block are fixedly connected to fixing strips, and the other end of each fixing strip is rotatably connected to a rotating shaft. The arc rod has a clamping groove on its surface, and the rotating shaft is fixedly connected to the inner wall of the clamping groove. A locking block is fixedly connected to the outer wall of the lower end of the arc rod. The locking seat has two symmetrically arranged locking slots on its surface, and a threaded hole is formed at the center of the locking seat. A screw is threaded into the threaded hole, and a locking collar is fixedly fitted onto the surface of the screw.

[0006] Preferably, the lower end of the arc rod is engaged inside the slot, and the lower end of the arc rod matches the slot.

[0007] Preferably, the locking block is engaged with the inner wall of the locking collar, and the side of the locking block that is in contact with the locking collar has an arc surface.

[0008] Preferably, the snap-fit ​​seat is located directly below the bolt, and the threaded hole inside the snap-fit ​​seat is centrally located and extends through the bolt.

[0009] Preferably, the hexagonal block matches the hexagonal hole.

[0010] Compared with the prior art, the beneficial effects of this utility model are as follows: through the mechanical snap-fit ​​structure of the bolt thread connection and the arc rod snap-fit ​​seat, even if the bolt is worn, the cooperation between the arc rod and the snap-fit ​​collar and the snap-fit ​​groove can still fix the bolt position, prevent it from falling out of the bolt hole, and ensure the landing gear support function. The contact surface between the snap-fit ​​block and the snap-fit ​​collar is designed as an arc surface, which can fit tightly and disperse vibration stress. The snap-fit ​​seat and the bolt are set coaxially, and the force is evenly distributed, reducing component wear caused by alternating loads and extending service life. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 This is a schematic cross-sectional view of the present invention. Figure 1 ; Figure 3 This is a schematic cross-sectional view of the present invention. Figure 2 ; Figure 4 This is a schematic diagram of the arc rod structure of this utility model; Figure 5 This is a schematic diagram of the snap-fit ​​collar structure of this utility model; Figure 6 This is a schematic diagram of the card holder structure of this utility model.

[0012] In the diagram: 1. Bolt; 2. Hexagonal hole; 3. Hexagonal block; 4. Fixing strip; 5. Shaft; 6. Arc rod; 7. Gutter; 8. Clip; 9. Clip seat; 10. Slot; 11. Threaded hole; 12. Screw; 13. Clip collar. Detailed Implementation

[0013] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0014] Please see Figure 1-6 The present invention provides the following technical solution: Example 1: An aircraft landing gear connecting bolt assembly includes a bolt 1, an arc rod 6, and a locking seat 9. The top of the bolt 1 has a hexagonal hole 2, and a hexagonal block 3 is inserted into the hexagonal hole 2. Both ends of the hexagonal block 3 are fixedly connected to fixing strips 4, and the other end of the fixing strips 4 is rotatably connected to a rotating shaft 5. The surface of the arc rod 6 has a clamping groove 7, and the rotating shaft 5 is fixedly connected to the inner wall of the clamping groove 7. A locking block 8 is fixedly connected to the outer wall of the lower end of the arc rod 6. Two locking grooves 10 are symmetrically opened on the surface of the locking seat 9. A threaded hole 11 is opened at the center of the locking seat 9. A screw 12 is threadedly connected inside the threaded hole 11, and a locking collar 13 is fixedly sleeved on the surface of the screw 12.

[0015] The lower end of the arc rod 6 is engaged inside the slot 10. The lower end of the arc rod 6 matches the slot 10. The slot 10 positions the arc rod 6 to prevent it from sliding on the mounting base 9 and reduce friction damage.

[0016] The locking block 8 is engaged with the inner wall of the locking collar 13. The side of the locking block 8 that is in contact with the locking collar 13 has an arc surface. The arc surface of the contact surface between the locking block 8 and the locking collar 13 can fit tightly and disperse vibration stress.

[0017] The snap-fit ​​seat 9 is located directly below the bolt 1. The threaded hole 11 inside the snap-fit ​​seat 9 is centrally located and runs through the bolt 1, so that the snap-fit ​​seat 9 and the bolt 1 are on the same straight line. When the bolt 1 is subjected to force, the force is evenly distributed from both ends to the snap-fit ​​seat 9, preventing the snap-fit ​​seat 9 from deforming rapidly due to uneven force.

[0018] The hexagonal block 3 matches the hexagonal hole 2, so that the hexagonal block 3 is stably snapped onto the upper end of the bolt 1, so that the external components of the bolt 1 are stably stressed.

[0019] In use, first fix the snap-fit ​​seat 9 to the landing gear preset mounting position through the threaded hole 11, ensuring that the snap-fit ​​seat 9 is directly below the bolt 1 to be installed, and that the two slots 10 face the direction that facilitates the insertion of the arc rod 6. Tighten the bolt 1 into the corresponding screw hole of the landing gear until the hexagonal hole 2 at the top of the bolt 1 protrudes from the mounting surface. Then, insert the hexagonal block 3 into the hexagonal hole 2. At this time, the fixing strips 4 at both ends of the hexagonal block 3 are in a movable state. Rotate the shaft 5 at the end of the fixing strips 4 on both sides respectively to drive the arc rod 6 to flip downward, so that the lower end of the arc rod 6 is aligned with the slot 10 of the snap-fit ​​seat 9 and snapped in. Tighten the screw 12 into the threaded hole 11 of the snap-fit ​​seat 9. During the tightening process, the snap-fit ​​collar 13 on the surface of the screw 12 moves down synchronously until the inner wall of the snap-fit ​​collar 13 is completely in contact with the snap block 8 on the arc rod 6. Utilizing the arc surface design of the snap block 8, the snap-fit ​​collar 13 will form a radial constraint on the snap block 8, and finally complete the double fixation of the entire component.

[0020] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft landing gear connecting bolt assembly, comprising a bolt (1), an arc rod (6), and a retaining seat (9), characterized in that: The bolt (1) has a hexagonal hole (2) at its top end. A hexagonal block (3) is inserted into the hexagonal hole (2). Both ends of the hexagonal block (3) are fixedly connected to a fixing strip (4). The other end of the fixing strip (4) is rotatably connected to a rotating shaft (5). A clamping groove (7) is opened on the surface of the arc rod (6). The rotating shaft (5) is fixedly connected to the inner wall of the clamping groove (7). A locking block (8) is fixedly connected to the outer wall of the lower end of the arc rod (6). Two locking grooves (10) are symmetrically opened on the surface of the locking seat (9). A threaded hole (11) is opened at the center of the locking seat (9). A screw (12) is threaded into the threaded hole (11). A locking collar (13) is fixedly sleeved on the surface of the screw (12).

2. The aircraft landing gear connecting bolt assembly according to claim 1, characterized in that: The lower end of the arc rod (6) is engaged inside the slot (10), and the lower end of the arc rod (6) matches the slot (10).

3. The aircraft landing gear connecting bolt assembly according to claim 1, characterized in that: The locking block (8) is engaged with the inner wall of the locking collar (13), and the side of the locking block (8) that is in contact with the locking collar (13) has an arc surface.

4. The aircraft landing gear connecting bolt assembly according to claim 1, characterized in that: The snap-fit ​​seat (9) is located directly below the bolt (1), and the threaded hole (11) inside the snap-fit ​​seat (9) is located at the center and passes through.

5. The aircraft landing gear connecting bolt assembly according to claim 1, characterized in that: The hexagonal block (3) matches the hexagonal hole (2).

Images