A landing gear door locking mechanism

Abstract

This invention provides a landing gear door locking mechanism, belonging to the field of aircraft landing gear technology. The mechanism includes a bracket mounted on the aircraft fuselage, a latch mounted on the door, and a locking mechanism mounted on the bracket and cooperating with the latch. The locking mechanism includes an expansion bolt, one end of which is threaded, and the other end of which is a sealing end. The threaded end passes through a first through hole in the bracket and is mounted on the bracket via a nut and a washer. The sealing end is disposed within a second through hole in the latch and is used to seal the second through hole. This invention ensures a tight seal between the door and the fuselage when the door is locked by adjusting the height of the expansion bolt. It also provides a double-redundant locking mechanism for the door.

Description

Technical Field

[0001] This invention belongs to the field of aircraft landing gear technology, and particularly relates to a landing gear door locking mechanism. Background Technology

[0002] Traditional aircraft landing gear bay doors rely on a locking hook on the upper door to engage the door locking pin. However, in actual use, to ensure locking, an adjustment gap is designed in the design. Because the height of the locking pin cannot be adjusted, this can lead to a gap between the door and the fuselage after locking. Rubber sealing strips are typically used to eliminate this gap, but if the gap exceeds the compression capacity of the rubber sealing strip, it will affect aircraft operation. During normal flight, the atmospheric temperature is low, and airflow does not affect critical components inside the landing gear bay, such as brake pads, retraction / extension actuators, pressure transmission cylinders, and locking actuators. However, during ultra-high-speed flight, extremely high-temperature airflow is generated, which can seep through gaps and damage equipment inside the landing gear bay, causing serious consequences such as landing gear failure. Simultaneously, severe turbulence causes high-frequency vibrations in the door, affecting the fatigue life of the door mechanism. Summary of the Invention

[0003] The purpose of this invention is to provide a landing gear bay door locking mechanism to solve the technical problem of ultra-high temperature airflow affecting the equipment inside the landing gear bay through the door gap.

[0004] To solve the above-mentioned technical problems, the specific technical solution of the present invention is as follows:

[0005] A landing gear door locking mechanism includes a bracket mounted on the aircraft fuselage, a latch mounted on the door, and a locking mechanism mounted on the bracket and cooperating with the latch. The locking mechanism includes an explosive bolt, one end of which is threaded and the other end of which is sealed. The explosive bolt is a cylinder filled with explosive.

[0006] The threaded end passes through the first through hole of the bracket and is mounted on the bracket by a nut and a washer;

[0007] The sealing end is disposed in the second through hole of the buckle, and the sealing end is used to seal the second through hole;

[0008] The explosive bolt has a locking block on one side of the sealing end. The diameter of the locking block on the side near the sealing end is smaller than the diameter of the second through hole, and the diameter of the locking block on the side away from the sealing end is larger than the diameter of the second through hole.

[0009] A spring is also fitted onto the explosive bolt. One end of the spring abuts against the bracket, and the other end of the spring abuts against the side of the locking block away from the sealing end.

[0010] Therefore, when the hatch is manually closed, the locking block is locked in the second through hole on the side near the sealing end, ensuring that the hatch is tightly sealed to the fuselage when it is closed and locked. If the gap is too large, the position of the explosive bolt can be adjusted by shims to ensure the installation height of the locking block, so that the hatch is sealed after the locking block and the buckle are locked together.

[0011] Furthermore, a bushing is provided between the wall of the first through hole and the explosive bolt, and the bushing is fitted onto the explosive bolt. The bushing is interference-fitted with the first through hole.

[0012] Furthermore, the bushing has a flange at one end near the spring, and the spring abuts against the flange.

[0013] Furthermore, the sealing end is clearance-fitted with the second through hole, and the outer periphery of the sealing end is provided with a groove that extends along the circumferential direction of the sealing end, and a sealing ring is provided in the groove.

[0014] Furthermore, the card block is a frustum, and the upper part of the second through hole is a conical inner wall that matches the shape of the card block.

[0015] Furthermore, the first through hole and the second through hole are coaxially arranged.

[0016] Furthermore, the bracket includes a mounting plate with a first through hole, through which the threaded end passes and is mounted on the mounting plate by a nut and a washer.

[0017] Furthermore, the flange is in contact with the lower end face of the mounting plate.

[0018] The landing gear door locking mechanism of the present invention has the following advantages: the landing gear door locking mechanism of the present invention is simple and easy to adjust and operate, has high reliability, and provides a dual-redundant locking device for locking the door, thus ensuring the flight safety of the aircraft. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the landing gear bay door locking mechanism of the present invention;

[0020] Figure 2 This is a schematic diagram of the explosive bolt structure of the present invention;

[0021] Figure 3 This is a schematic diagram of the support structure of the present invention, wherein (a) is a front view and (b) is a top view;

[0022] Figure 4 This is a schematic diagram of the bushing structure of the present invention;

[0023] Figure 5This is a schematic diagram of the card block structure of the present invention;

[0024] Figure 6 This is a schematic diagram of the buckle structure of the present invention, wherein (a) is a top view and (b) is a cross-sectional view along line A-A of (a);

[0025] Figure 7 This is a diagram showing the hatch locked and closed.

[0026] The markings in the diagram are as follows: 1. Explosion bolt; 2. Nut; 3. Washer; 4. Bracket; 41. First through hole; 42. Mounting plate; 5. Bushing; 51. Flange; 6. Spring; 7. Locking block; 8. Clip; 81. Second through hole; 9. Aircraft fuselage; 10. Door; 11. Locking mechanism; 12. Threaded end; 13. Sealing end; 14. Groove; 15. Door sealing strip. Detailed Implementation

[0027] To better understand the purpose, structure, and function of this invention, the invention will be described in further detail below with reference to the accompanying drawings.

[0028] like Figure 1 and Figure 2 As shown, a landing gear door locking mechanism in this embodiment includes a bracket 4 mounted on the aircraft fuselage 9, a latch 8 mounted on the door 10, and a locking mechanism 11 mounted on the bracket 4 and cooperating with the latch 8. The locking mechanism 11 includes an explosive bolt 1, one end of which is a threaded end 12, and the other end is a sealing end 13. The explosive bolt 1 is a cylinder filled with explosives. The bracket 4 is mounted on the aircraft fuselage 9 by bolts. Figure 3 As shown, the bracket 4 includes a mounting plate 42, on which a first through hole 41 is formed. Figure 1 and Figure 6 The buckle 8 shown is installed on the hatch 10 by bolts, and the buckle 8 has a second through hole 81.

[0029] like Figure 1 and Figure 3 As shown, the threaded end 12 passes through the first through hole 41 and is mounted on the mounting plate 42 via a nut 2 and a washer 3. The nut 2 is an aviation self-locking nut, and the washer 3 is a metal washer. A bushing 5 is provided between the hole wall of the first through hole 41 and the explosion bolt 1. The bushing 5 is fitted onto the explosion bolt 1, and the bushing 5 has an interference fit with the first through hole 41. Figure 1 , Figure 3 and Figure 4 As shown, the bushing 5 has a flange 51 at the end away from the threaded end 12, and the flange 51 is in contact with the lower end face of the mounting plate 42.

[0030] like Figure 1 and Figure 2 As shown, the sealing end 13 is disposed within the second through hole 81 of the buckle 8, and the sealing end 13 is used to seal the second through hole 81. The sealing end 13 is clearance-fitted with the second through hole 81, and the outer periphery of the sealing end 13 is provided with a groove 14, which extends along the circumferential direction of the sealing end 13, and a sealing ring is provided in the groove 14.

[0031] like Figure 1 , Figure 5 and Figure 6 As shown, the explosive bolt 1 has a locking block 7 fitted on one side of the sealing end 13. The locking block 7 is a frustum with a cone angle of M. The diameter of the locking block 7 on the side near the sealing end 13 is smaller than the diameter of the second through hole 81, and the diameter of the locking block 7 on the side away from the sealing end 13 is larger than the diameter of the second through hole 81. The buckle 8 is an inner conical buckle with an inner conical angle of N, where N≤M.

[0032] like Figure 1 As shown, a spring 6 is also fitted on the explosive bolt 1. The spring 6 is a compression spring and is located between the bushing 5 and the locking block 7. One end of the spring 6 abuts against the flange 51, and the other end of the spring 6 abuts against the side of the locking block 7 away from the sealing end 13.

[0033] like Figure 1 and Figure 7 As shown, in this embodiment, the landing gear door locking mechanism has an expansion bolt 1 positioned lower than its theoretical height during initial installation. Figure 1 As shown, the upward position is high, and the downward position is low. When the hatch is manually closed, an upward external clamping force is applied to the hatch. After the latch 7 and the buckle 8 are fastened, because the initial installation position of the explosive bolt 1 is lower than the theoretical design position, the hatch compresses the spring 6 upward until the hatch sealing strip 15 can no longer compress the hatch and closes tightly. The external clamping force for closing the hatch is removed, and the hatch falls back to the stop position of the explosive bolt 1 under the action of the spring force and the hatch's own weight. The fall gap is measured. Assuming the gap value is Y, the thickness of the shim 3 is adjusted to X+Y to adjust the height position of the explosive bolt 1, ensuring that after the hatch is closed upward, the hatch sealing strip 15 can no longer compress the hatch and close tightly.

[0034] This invention ensures tight clamping between the hatch and the fuselage by adjusting the position of the explosive bolts when the hatch is retracted and locked. It also simplifies the mechanism, reduces weight, improves reliability, and saves installation space.

[0035] It is understood that the present invention has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the invention. Furthermore, under the teachings of the present invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of the present invention.

Claims

1. A landing gear bay door locking mechanism, characterized in that, It includes a bracket (4) installed on the aircraft fuselage (9), a buckle (8) installed on the cabin door (10), and a locking mechanism (11) installed on the bracket (4) and cooperating with the buckle (8). The locking mechanism (11) includes an explosive bolt (1), one end of which is a threaded end (12), and the other end of which is a sealing end (13). The threaded end (12) passes through the first through hole (41) of the bracket (4) and is mounted on the bracket (4) by a nut (2) and a washer (3); The sealing end (13) is disposed in the second through hole (81) of the buckle (8), and the sealing end (13) is used to seal the second through hole (81); The explosive bolt (1) has a locking block (7) on one side of the sealing end (13). The diameter of the locking block (7) on the side near the sealing end (13) is smaller than the diameter of the second through hole (81), and the diameter of the locking block (7) on the side away from the sealing end (13) is larger than the diameter of the second through hole (81). A spring (6) is also fitted on the explosive bolt (1). One end of the spring (6) abuts against the bracket (4), and the other end of the spring (6) abuts against the side of the locking block (7) away from the sealing end (13).

2. The landing gear bay door locking mechanism according to claim 1, characterized in that, A bushing (5) is provided between the hole wall of the first through hole (41) and the explosive bolt (1), and the bushing (5) is fitted on the explosive bolt (1).

3. The landing gear bay door locking mechanism according to claim 2, characterized in that, The bushing (5) has a flange (51) at one end near the spring (6), and the spring (6) abuts against the flange (51).

4. The landing gear bay door locking mechanism according to claim 1, characterized in that, The sealing end (13) is fitted with the second through hole (81) with a clearance, and the outer periphery of the sealing end (13) is provided with a groove (14), and a sealing ring is provided in the groove (14).

5. The landing gear bay door locking mechanism according to claim 1, characterized in that, The card block (7) is a frustum, and the upper part of the second through hole (81) is a conical inner wall that matches the shape of the card block (7).

6. The landing gear bay door locking mechanism according to claim 1, characterized in that, The first through hole (41) and the second through hole (81) are coaxially arranged.

7. The landing gear bay door locking mechanism according to claim 3, characterized in that, The bracket (4) includes a mounting plate (42) with a first through hole (41) on the mounting plate (42). The threaded end (12) passes through the first through hole (41) and is mounted on the mounting plate (42) by a nut (2) and a washer (3).

8. The landing gear bay door locking mechanism according to claim 7, characterized in that, The flange (51) is in contact with the lower end face of the mounting plate (42).

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