Automatic locking hook device for aircraft arresting cable

Abstract

The invention discloses an automatic locking hook device for an aircraft arresting cable in the technical field of aircraft arresting cables, which comprises an arresting cable, the arresting cable is provided with a locking hook unit, the locking hook unit comprises an elastic locking structure and a connecting structure, and the connecting structure is used for connecting the elastic locking structure with the arresting cable. The elastic locking structure is used for locking the aircraft tail hook and the arresting cable under the action of the force of the aircraft tail hook; by arranging the lock hook unit, the unhooking rate of the tail hook and the arresting cable of the aircraft can be reduced, and then the problems that the risk of landing failure is increased, and the flight safety and the operation efficiency are threatened due to unhooking of the tail hook and the arresting cable are solved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft arresting cables, and in particular to an automatic locking hook device for an aircraft arresting cable. Background Art

[0002] Aircraft arresting cables play a vital role in military airports and aircraft carriers. They can quickly and effectively slow down and stop the aircraft's taxiing during landing, ensuring that the aircraft can safely and accurately stay in the designated area. Especially in emergency landings or when rapid braking is required, they are key equipment to ensure the safety of pilots and aircraft.

[0003] During the landing process, the tail hook of the aircraft may hit the ground and bounce up, or hit the arresting cable and bounce up, which may easily cause problems such as poor contact angle between the arresting cable and the tail hook of the aircraft and lead to decoupling. Traditional arresting cables are prone to decoupling due to the huge impact force and complex posture of the aircraft when landing at high speed, increasing the risk of landing failure and posing a threat to flight safety. Summary of the invention

[0004] In order to overcome the deficiencies of the prior art, the technical problem to be solved by the present invention is: how to reduce the risk of decoupling between the tail hook and the arresting cable.

[0005] The technical solution adopted by the present invention to solve its technical problem is:

[0006] An automatic locking hook device for an aircraft arresting cable comprises an arresting cable, wherein the arresting cable is provided with a locking hook unit, wherein the locking hook unit comprises an elastic locking structure and a connecting structure, wherein the connecting structure is used to connect the elastic locking structure and the arresting cable, and wherein the elastic locking structure is used to lock the aircraft tail hook and the arresting cable when subjected to the force of the aircraft tail hook.

[0007] Furthermore, there are multiple locking hook units evenly arranged on the arresting cable.

[0008] Furthermore, the connecting mechanism includes a rolling bearing, the inner wall of the rolling bearing is fixedly sleeved on the outer wall of the barrier cable, and the outer wall of the rolling bearing is fixedly connected to the elastic locking structure.

[0009] Furthermore, the outer wall of the rolling bearing and the elastic locking structure are rigidly connected via a bolt structure.

[0010] Furthermore, the elastic locking structure includes an elastic metal sheet, which is in a strip-shaped state arranged along the extension direction of the arresting cable under natural conditions. When the tail hook of the aircraft contacts the elastic metal sheet, the elastic metal sheet undergoes elastic deformation and wraps around the arresting cable.

[0011] Furthermore, the elastic metal sheet is made of high-elastic steel material.

[0012] Furthermore, the cross-sectional profile of the elastic metal sheet is arched, and the direction of the arched protrusion is away from the barrier cable.

[0013] Furthermore, the cross-sectional profile of the elastic metal sheet is an arc shape adapted to the outer wall of the barrier cable.

[0014] The beneficial effects of the present invention are:

[0015] By setting up a locking hook unit, the decoupling rate of the aircraft's tail hook and the arresting cable can be reduced, thereby improving the risk of increased landing failure and threat to flight safety caused by the decoupling of the tail hook and the arresting cable. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a three-dimensional schematic diagram of the present invention in a natural state;

[0017] Figure 2 It is a schematic diagram of the elastic deformation state of the elastic metal sheet of the present invention;

[0018] Figure 3 It is a cross-sectional schematic diagram of the present invention;

[0019] Marked in the figure, 1-barrier cable, 2-elastic metal sheet, 3-connecting structure, 31-rolling bearing, 32-bolt structure. DETAILED DESCRIPTION

[0020] The present invention is further described below in conjunction with the accompanying drawings.

[0021] according to Figure 1 to Figure 3 As shown, an embodiment of the present application proposes an automatic locking hook device for an aircraft arresting cable, including an arresting cable 1, wherein the arresting cable 1 is provided with a locking hook unit, wherein the locking hook unit includes an elastic locking structure and a connecting structure 3, wherein the connecting structure 3 is used to connect the elastic locking structure and the arresting cable 1, and wherein the elastic locking structure is used to lock the aircraft tail hook and the arresting cable 1 when subjected to the aircraft tail hook force; the locking hook unit is arranged at a preset collision hook position of the arresting cable 1 to ensure that the locking hook unit can stably form a locking hook effect.

[0022] Specifically, when the aircraft lands in different postures, the tail hook of the aircraft may contact different positions of the arresting cable 1. In order to ensure that the tail hook of the aircraft can trigger the locking hook unit, the locking hook units on the arresting cable 1 are evenly arranged. The distribution of specific positions can be designed in a range by the contact positions of the tail hook of the aircraft and the arresting cable 1 in multiple flight landing experiments to ensure that the points on the arresting cable 1 that may be hit by the tail hook of the aircraft are all arranged with locking hook units, so as to ensure that when the aircraft lands, the tail hook of the aircraft can accurately contact the locking hook unit to achieve a locking effect.

[0023] Generally, it is difficult to ensure that the tail hook is exactly in the middle of the arresting cable 1 when the aircraft lands. In the process of dragging the arresting cable 1, sliding friction will be generated with the arresting cable 1, causing great loss to the arresting cable 1 and reducing the service life of the arresting cable 1. In order to improve the above problems, the connecting mechanism includes a rolling bearing 31, the inner wall of the rolling bearing 31 is fixedly sleeved on the outer wall of the arresting cable 1, and the outer wall of the rolling bearing 31 is fixedly connected to the elastic locking structure; relative displacement is achieved by rolling friction between the rolling bearing 31 and the arresting cable 1, which greatly reduces the friction loss of the arresting cable 1, reduces the raw material cost of the arresting cable 1 and the equipment maintenance time cost, and avoids the breakage of the arresting cable 1, thereby further ensuring safety; and the outer wall of the outer sleeve of the rolling bearing 31 and the elastic locking structure are rigidly connected by a bolt structure 32, and the bolt structure 32 is an existing rigid strength bolt structure 32, which ensures that the elastic locking structure will not fall off under the high-intensity impact of the aircraft tail hook.

[0024] With respect to the above-mentioned elastic locking structure, one implementation method in this embodiment may be a clamping structure with a spring structure, wherein the clamping structure is in an open state under natural conditions, and a spring is arranged between the two clamping parts of the clamping structure, and the clamping structure is in an expanded state through the clamping effect of the clamping structure, and the spring is in a compressed state at this time, and a corresponding triggering structure is arranged at the position where the arresting cable 1 hits the tail hook of the aircraft, and the triggering structure is connected to the clamping structure, and when the tail hook of the aircraft touches the triggering structure of the arresting cable 1, the two clamping parts of the clamping structure quickly approach under the action of the spring to achieve the locking effect on the tail hook of the aircraft.

[0025] In order to reduce costs and simplify the structure, the elastic locking structure in the present embodiment may be an elastic metal sheet 2 in another implementation manner. The elastic metal sheet 2 is naturally in a strip-shaped state arranged along the extension direction of the arresting cable 1, and the size can cover a certain length, thereby ensuring that the tail hook of the aircraft is stably locked to a certain extent. When the tail hook of the aircraft contacts the elastic metal sheet 2, the elastic metal sheet 2 undergoes elastic deformation and wraps around the arresting cable 1. When the aircraft lands and acts on the arresting cable 1, the main resistance and hooking effect rely on the interaction force between the tail hook of the aircraft and the arresting cable 1. The elastic metal sheet 2 in the present embodiment plays an auxiliary role in the force by being wrapped around the outer wall of the tail hook of the aircraft, thereby improving the connection stability between the tail hook of the aircraft and the arresting cable 1 and reducing the unhooking rate to a certain extent.

[0026] Specifically, the elastic metal sheet 2 is made of high-elastic steel material, which has excellent corrosion resistance and impact resistance. In the highly corrosive aircraft carrier environment, high-elastic steel can not only maintain stable performance for a long time, but also show high strength and toughness when subjected to extreme impacts such as aircraft tail hook impact. At the same time, its long service life and good fatigue resistance also meet the requirements of repeated use of the aircraft arresting cable 1; and in the material parameter simulation experiment, the elastic modulus of high-elastic steel is about 200GPa, and the yield strength is about 350MPa. In the process of the aircraft landing and sliding to stop, the main kinetic energy of the aircraft tail hook is transmitted by the arresting cable 1, and the elastic steel sheet mainly plays an auxiliary role in the force, that is, it undergoes elastic deformation, thereby playing a fixing role. It only needs to ensure that its own shape does not change significantly during the deformation process. The required elastic modulus is about 50GPa, and the yield strength is about 120MPa. Therefore, the material parameters can meet the requirements and have a large load margin; the elastic metal sheet 2 can also be an existing elastic memory alloy material.

[0027] In addition, in order to ensure that the elastic metal sheet 2 can quickly react and elastically deform after receiving the impact of the aircraft tail hook in the naturally stretched state, in one embodiment, the cross-sectional profile of the elastic metal sheet 2 is arched, and the direction of the arch protrusion is away from the arresting cable 1. This arched design can play a stable supporting role in the naturally stretched state, and a large amount of elastic stress is released during impact deformation, and the supporting effect of the arch quickly fails, so that the elastic metal sheet 2 can be quickly deformed and tightly wrapped around the outside of the aircraft tail hook; in another embodiment, the cross-sectional profile of the elastic metal sheet 2 is an arc shape that is adapted to the outer wall of the arresting cable 1. The principle is similar to that of the arch, but it adapts to the characteristics of the outer wall of the arresting cable 1, so that the structure of the elastic metal sheet 2 in the natural state is more stable.

[0028] The actual working principle of the automatic locking hook device of the aircraft arresting cable is: when the aircraft lands, the inner wall of the aircraft tail hook impacts the position of the elastic metal sheet 2, and the elastic metal sheet 2 quickly undergoes elastic deformation and is wrapped around the outer wall of the aircraft tail hook. At this time, the aircraft tail hook is locked by the elastic metal sheet 2, reducing the unhooking rate, but the actual arresting force is borne by the arresting cable 1 itself. In the process of pulling the arresting cable 1 to move, the aircraft tail hook rotates relative to the arresting cable 1. At this time, under the action of the rolling bearing 31, the sliding friction force is converted into the rolling friction force of the roller, reducing wear.

[0029] In summary, the embodiment of the present application proposes an automatic locking hook device for an aircraft arresting cable. When the elastic metal sheet 2 collides with the tail hook of the aircraft, it can trigger its elastic deformation to tightly wrap the tail hook of the aircraft, thereby effectively preventing unhooking; the elastic metal sheet 2 is connected to the arresting cable 1 through a bearing, thereby converting the original sliding friction between the tail hook of the aircraft and the arresting cable 1 into rolling friction, thereby effectively reducing friction loss and greatly increasing the service life of the arresting cable 1.

Claims

1. An automatic hook locking device for an aircraft arresting cable, comprising an arresting cable (1), characterized in that: The arresting cable (1) is provided with a locking hook unit, and the locking hook unit comprises an elastic locking structure and a connecting structure (3), wherein the connecting structure (3) is used to connect the elastic locking structure and the arresting cable (1), and the elastic locking structure is used to lock the aircraft tail hook and the arresting cable (1) when subjected to the force of the aircraft tail hook.

2. The automatic hook locking device for aircraft arresting cable according to claim 1, characterized in that: The locking hook units on the arresting cable (1) are multiple and evenly arranged.

3. The automatic hook locking device for aircraft arresting cable according to claim 1, characterized in that: The connection mechanism comprises a rolling bearing (31), the inner wall of the rolling bearing (31) is fixedly sleeved on the outer wall of the blocking cable (1), and the outer wall of the rolling bearing (31) is fixedly connected to the elastic locking structure.

4. The automatic hook locking device for aircraft arresting cables according to claim 3, characterized in that: The outer wall of the rolling bearing (31) and the elastic locking structure are rigidly connected via a bolt structure (32).

5. The automatic hook locking device for aircraft arresting cables according to claim 3, characterized in that: The elastic locking structure comprises an elastic metal sheet (2), wherein the elastic metal sheet (2) is in a strip-shaped state arranged along the extension direction of the arresting cable (1) under a natural condition, and when the tail hook of the aircraft contacts the elastic metal sheet (2), the elastic metal sheet (2) undergoes elastic deformation and wraps the arresting cable (1).

6. The automatic hook locking device for aircraft arresting cables according to claim 5, characterized in that: The elastic metal sheet (2) is made of high-elastic steel material.

7. The automatic hook locking device for aircraft arresting cables according to claim 6, characterized in that: The cross-sectional profile of the elastic metal sheet (2) is arched, and the direction of the arched protrusion is away from the barrier cable (1).

8. The automatic hook locking device for aircraft arresting cables according to claim 6, characterized in that: The cross-sectional profile of the elastic metal sheet (2) is an arc shape adapted to the outer wall of the barrier cable (1).

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