Aircraft landing gear down lock guiding and deviation rectifying device and down lock

Abstract

The invention discloses an aircraft landing gear down lock guiding and deviation rectifying device and a down lock, the aircraft landing gear down lock guiding and deviation rectifying device comprises a lock arm and a lock shell, a guiding block assembly is installed on the lock shell, the guiding block assembly is installed at the final limiting position when the lock arm is locked, and the guiding block assembly comprises a guiding face; the guide surface is formed by the circumferential surfaces of the first pin rollers which are rotationally mounted in parallel; a deviation rectifying assembly is installed on the side, deviating from the heading direction, in a lock arm inlet of the lock shell and comprises a rotationally-installed second roller, a deviation rectifying face is formed by the circumferential face of the second roller, and when locking is conducted, when the motion trail of the lock arm deviates towards the rear side of the heading direction, the deviation rectifying face of the second roller is deviated towards the rear side of the heading direction. When the lock arm enters the lock shell, the lock arm firstly makes contact with the second pin roller of the deviation rectifying assembly, under the action of the second pin roller and the landing gear folding and unfolding load, the track of the lock arm gradually returns to the normal track, and then the lock arm makes contact with the first pin roller of the guide block assembly till the final limiting position.

Description

Technical Field

[0001] The invention relates to an aircraft landing gear, in particular to a lower lock guide deviation correction device and a lower lock of the aircraft landing gear. Background Art

[0002] If the aircraft landing gear is subjected to a lateral load in the same direction as the lowering trajectory during the lowering process, the landing gear may deviate from the original locking position, resulting in the failure of the lower lock to lock. The lower locking of the landing gear is related to the safety of the aircraft landing and ground movement.

[0003] Chinese patent CN202368788U discloses a guiding and correcting device for the lower lock of a landing gear. When the lower lock arm is in operation, it is subject to static friction when in contact with the guide plate. Since the movement trajectory of the landing gear lock arm will be subject to over-deviation due to the lateral load in the same direction as the movement trajectory, the lock arm will contact the V-shaped guide surface when it enters the lock shell after the deviation and contacts the rigid guide mechanism that plays a correcting role, and corrects the deviation through forced friction. During this process, it will be affected by static friction, resulting in an increase in the load for retracting and extending the landing gear, and it is easy for the landing gear to not be lowered into place and the lower lock to be unable to lock, which reduces the safety of the product and causes abnormal wear of the lock arm and the guide plate, affecting the durability and life of the product. Summary of the invention

[0004] The technical problem to be solved by the present invention is that, in view of the deficiency that the existing landing gear lower lock guide correction device is affected by large resistance during the correction process, resulting in the safety and durability of the aircraft landing gear being affected, the present invention provides an aircraft landing gear lower lock guide correction device and a lower lock which can reduce the resistance and wear during the correction process.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0006] A guide and correction device for a lower lock of an aircraft landing gear comprises a locking arm and a lock shell, wherein a guide block assembly is installed in the lock shell, and the guide block assembly is installed in the final limit position when the locking arm is locked. The structural characteristics of the device are as follows: the guide block assembly comprises a guide surface, and the guide surface is formed by the circumferential surface of a first roller installed in parallel and rotationally; a correction assembly is installed on the side of the lock arm entrance in the lock shell away from the heading, and the correction assembly comprises a second roller installed in rotation, and the circumferential surface of the second roller forms the correction surface; when locking, when the movement trajectory of the locking arm deviates toward the rear side of the heading, the locking arm first contacts the second roller of the correction assembly during the process of entering the lock shell, and under the action of the second roller and the landing gear retraction and extension load, the trajectory of the locking arm gradually returns to the normal trajectory, and then the locking arm contacts the first roller of the guide block assembly until the final limit position.

[0007] The guide surface of the guide block assembly and the correction surface of the correction assembly in the aircraft landing gear lower lock guide correction device of the present invention are both formed by the circumferential surface of a rotatably mounted roller, so that when the locking arm contacts the guide surface or the correction surface, the static friction originally borne can be converted into rolling friction, thereby not only reducing the wear of the locking arm, the guide block assembly and the correction assembly, but also reducing the impact on the landing gear retraction and extension load, so that the lower lock can be locked accurately, improving the safety of the aircraft, while reducing the wear of the locking arm, the guide block assembly and the correction assembly, ensuring the durability and life of the aircraft. In addition, the present invention installs a correction component at the lock arm entrance of the lock shell away from the heading side, so that one side of the lower lock arm will first contact the correction surface of the correction component during the correction process of entering the lock shell, thereby avoiding premature contact of the two sides of the lock arm with the guide block assembly, reducing the resistance encountered during the correction process and the influence of the resistance on the retraction and extension load of the landing gear, which not only ensures that the lower lock can be locked accurately to a certain extent, but also improves the safety of the aircraft, while reducing the wear of the lock arm, the guide block assembly and the correction assembly, thereby ensuring the durability and life of the aircraft.

[0008] Preferably, a lock pin hole is provided on the lock housing directly opposite to the lock pin of the lower position lock, and a baffle and a positioning pin are rotatably installed on one side of the lock pin hole, a torsion spring is installed between the lock housing and the baffle, and when unlocking, the baffle faces the lock pin of the lower position lock with the support of the torsion spring and the positioning pin. In this way, the baffle can be used to prevent the lower position lock actuator of the landing gear from being locked by mistake, and at the same time, the speed at which the lock arm enters the lock housing can be slowed down, thereby improving the safety and stability of the locking of the lower position lock of the landing gear.

[0009] Preferably, the guide block assembly further comprises a V-shaped frame, and the bottom surface of the V-shaped frame is arranged as the guide surface.

[0010] Preferably, the correction component further comprises a correction bracket, the correction bracket is fixedly connected to the lock housing, and the second roller is rotatably mounted on the correction bracket to form the correction surface.

[0011] Preferably, the guide block assembly further comprises a sensor mounting bracket, on which a proximity sensor is mounted. When the locking arm reaches the upper locking position, the proximity sensor gives a locking arm in place signal, and the lower lock lowers the locking pin to complete the locking.

[0012] Preferably, two lock pin holes are arranged in parallel on the lock housing, the baffles are symmetrically arranged on both sides of the lock arm entrance, and the guide block assembly forms a concave-convex matching structure with the lock head on the lock arm.

[0013] Based on the same inventive concept, the present invention also provides an aircraft landing gear down lock, which includes the guide deviation correction device.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] 1) During the locking process, one side of the locking arm of the lower lock of the present invention first contacts the correction surface of the correction assembly during the correction process of entering the lock housing, thereby avoiding premature contact of the two sides of the locking arm with the guide block assembly, which not only reduces the resistance encountered during the correction process, but also reduces the influence of the resistance on the retraction and extension load of the landing gear, so that the lower lock can be locked in place, thereby improving the safety of the aircraft, reducing the wear of the locking arm, the guide block assembly and the correction assembly, and ensuring the durability and life of the aircraft.

[0016] 2) The lower lock arm of the present invention is subjected to dynamic friction provided by the roller during the process of entering the lock housing. Compared with static friction, the present invention greatly reduces the resistance of the lock arm entering the lock housing.

[0017] 3) The baffle, torsion spring and positioning pin of the present invention work together to prevent the landing gear lower lock actuator from being locked by mistake, and at the same time can slow down the speed at which the lock arm enters the lock housing, thereby improving the safety and stability of the landing gear lower lock locking. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 It is a schematic diagram of the initial state of the lower lock arm entering the lock housing during the locking process of the lower lock of the landing gear of the present invention;

[0020] Figure 2 It is a schematic diagram of the state of the lower lock arm after the lower lock arm is corrected during the locking process of the lower lock of the landing gear;

[0021] Figure 3 This is a schematic diagram of the state in which the locking process of the lower lock of the landing gear is completed;

[0022] Figure 4 It is a schematic diagram of the matching relationship between the guide block assembly and the locking arm after locking;

[0023] Figure 5 It is a schematic diagram of the state before the baffle plate contacts the locking arm.

[0024] In the figure, 1-locking arm, 2-correction assembly, 3-guide block assembly, 4-lock housing, 5-baffle, 6-locating pin, 7-first roller, 8-sensor mounting seat, 9-torsion spring, 10-lower lock actuator, 11-second roller, 12-lock pin hole, 13-lock pin. DETAILED DESCRIPTION

[0025] The present invention is further described below in conjunction with specific preferred embodiments, but the protection scope of the present invention is not limited thereby.

[0026] In the description of the present invention, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0027] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0028] See also Figure 1 - Figure 5 An embodiment of the aircraft landing gear lower lock guide correction device of the present invention comprises a lock arm 1 and a lock housing 4, wherein a guide block assembly 3 and a correction assembly 2 are installed in the lock housing 4.

[0029] The guide block assembly 3 is installed at the final limit position when the locking arm 1 is locked, and the guide block assembly 3 includes a V-shaped frame 13, and the two side surfaces of the V-shaped frame 13 are set as guide surfaces, and the guide surfaces are formed by the circumferential surfaces of a plurality of first rollers 7 installed in parallel rotation. The first rollers 7 on the two guide surfaces are symmetrically distributed in pairs and are installed on the V-shaped frame 13 via bearings. The overall shape of the guide block assembly 3 is V-shaped, the middle part of the lock head of the locking arm 1 is concave, and the guide block assembly 3 and the middle part of the lock head of the locking arm 1 form an adaptive concave-convex matching structure.

[0030] The deflection correction component 2 is installed on the side away from the course of the lock arm entrance of the lock housing 4, and the deflection correction component 2 includes a deflection correction bracket 14, the deflection correction bracket 14 is fixedly connected to the lock housing 4, and a second roller 11 is rotatably installed on the deflection correction bracket 14 through a bearing, and the circumferential surface of the second roller 11 forms a deflection correction surface. The lock housing 4 is provided with lock pin holes 12 facing the two lower lock pins, and the baffle 5 and the positioning pin 6 are rotatably installed inside the lock housing 4 on both sides of the two lock pin holes 12. The baffle plate 5 is rotatably mounted on the lock housing 4 via a rotating shaft, and a torsion spring 9 is mounted on the rotating shaft, one end of the torsion spring 9 abuts against the lock housing 4, and the other end abuts against the inner surface of the baffle plate 5, and the outer surface of the baffle plate 5 is supported by the positioning pin 6, so that when locking, when the baffle plate 5 is abutted by the lock arm 1, it can overcome the elastic force of the torsion spring 9 and rotate inward, and when unlocking, it can be reset by the restoring force of the torsion spring 9, and at the same time, the positioning pin 6 can be used to prevent the baffle plate 5 from being separated from the lock pin hole 12 when unlocking. That is, when unlocking, the baffle plate 5 is supported by the torsion spring 9 and the positioning pin 6 to face the lower lock pin, so as to prevent the lower lock actuator 10 of the landing gear from being locked by mistake, and at the same time, the speed of the lock arm 1 entering the lock housing 4 can be slowed down, thereby improving the safety and stability of the lower lock of the landing gear.

[0031] Preferably, the bottom of the guide block assembly 3 is set as a sensor mounting bracket 8, and a proximity sensor is installed on the sensor mounting bracket 8. When the locking arm 1 reaches the upper locking position, the proximity sensor gives a locking arm 1 in place signal, and the lower lock actuator 10 lowers the locking pin to complete the locking.

[0032] The specific working principle of the present invention is:

[0033] 1) In the unlocked state (the lock arm 1 has not yet entered the lock housing 4), the baffle 5 is fixed directly below the lower lock actuator 10 by the torsion spring 9 and the positioning pin 6 to prevent the lock pin of the lower lock actuator 10 from being accidentally lowered (such as Figure 5 As shown in the figure). Under the normal retraction and extension trajectory, the lock arm 1 enters the lock housing 4 and pushes the baffle 5 to move inside the lock housing 4. When the lock arm 1 moves to the point where the two inclined surfaces on the lock head are in contact with the V-shaped guide surface of the guide block assembly 3 (as shown in the figure), the lock arm 1 moves to the point where the two inclined surfaces on the lock head are in contact with the V-shaped guide surface of the guide block assembly 3 (as shown in the Figure 3 , Figure 4 As shown in the figure, the guide block assembly 3 prevents the lock arm 1 from moving further inward, and positions the lock arm 1 directly below the lower lock actuator 10, ensuring that the lower lock pin can smoothly enter the two lock pin holes 12 of the lock arm 1. The proximity sensor on the sensor mounting bracket 8 on the guide block assembly 3 gives a signal that the lower lock is in place, and the lower lock puts down the lock pin to complete the locking.

[0034] 2) The correction component 2 is located at the side of the lock arm entrance of the lock housing 4 that is away from the heading. It uses the second roller 11 to correct the locking arm 1. When the landing gear is lowered in the air / water, the movement trajectory of the locking arm 1 will move in the heading direction (such as Figure 1 The lock arm 1 with its trajectory shifted will first contact the second roller 11 on the deviation correction component 2 (as shown in FIG. Figure 1 ), avoiding the premature contact of both sides of the locking arm 1 with the guide block assembly 3 during the locking process, thereby reducing the resistance encountered during the correction process. Under the action of the second roller 11 and the retracting and releasing load, the trajectory of the locking arm 1 will gradually correct and return to the normal trajectory until the surface of the locking arm 1 close to the heading side contacts the first roller 7 on the V-shaped guide surface of the guide block assembly 3, and avoids the locking arm 1 from contacting the surface of the guide block assembly 3 other than the first roller 7. In this way, during the locking process, the locking arm 1 only contacts the correction surface formed by the second roller 11 and the guide surface formed by the first roller 7, that is, during the locking process, there is only rolling friction between the locking arm 1 and the correction assembly 2 and the guide block assembly 3, which further reduces the resistance during the locking process, enables the lower lock to be locked accurately, improves the safety of the aircraft, and reduces the wear of the locking arm, the guide block assembly and the correction assembly, ensuring the durability and life of the aircraft.

[0035] The above is only a specific implementation scheme of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the art can make many possible changes and modifications to the technical scheme of the present invention by using the technical content disclosed above without departing from the scope of the technical scheme of the present invention, or modify it into an equivalent embodiment of equivalent changes. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical scheme of the present invention should fall within the protection scope of the technical scheme of the present invention.

Claims

1. A guide deviation correction device for the lower lock of an aircraft landing gear, comprising a lock arm and a lock housing, wherein a guide block assembly is installed on the lock housing, and the guide block assembly is installed at the final limit position when the lock arm is locked, characterized in that: The guide block assembly includes a guide surface, which is formed by the circumferential surface of a first roller installed in parallel and rotationally. A correction assembly is installed on the side away from the heading in the lock arm entrance of the lock shell, and the correction assembly includes a second roller installed in rotation, and the circumferential surface of the second roller forms the correction surface. When locking, when the movement trajectory of the lock arm deviates toward the rear side of the heading, the lock arm first contacts the second roller of the correction assembly during the process of entering the lock shell. Under the action of the second roller and the landing gear retraction and extension load, the trajectory of the lock arm gradually returns to the normal trajectory. Subsequently, the lock arm contacts the first roller of the guide block assembly until it reaches the final limit position.

2. The aircraft landing gear lower lock guide correction device according to claim 1, characterized in that: A lock pin hole is arranged on the lock shell facing the lower lock pin, and a baffle and a positioning pin are rotatably installed on one side of the lock pin hole, a torsion spring is installed between the lock shell and the baffle, and when unlocking, the baffle faces the lower lock pin with the support of the torsion spring and the positioning pin.

3. The aircraft landing gear lower lock guide correction device according to claim 1, characterized in that: The guide block assembly further comprises a V-shaped frame, and a bottom surface of the V-shaped frame is configured as the guide surface.

4. The aircraft landing gear lower lock guide correction device according to claim 1, characterized in that: The correction component also includes a correction bracket, which is fixedly connected to the lock housing, and the second roller is rotatably mounted on the correction bracket to form the correction surface.

5. The aircraft landing gear lower lock guide correction device according to claim 1, characterized in that: The guide block assembly also includes a sensor mounting bracket, on which a proximity sensor is mounted. When the locking arm reaches the upper locking position, the proximity sensor gives a locking arm in place signal, and the lower lock lowers the locking pin to complete the locking.

6. The aircraft landing gear lower lock guide correction device according to claim 2, characterized in that: The lock housing is provided with two lock pin holes in parallel, the baffle is symmetrically arranged on both sides of the lock arm entrance, and the guide block assembly forms a concave-convex matching structure with the lock head on the lock arm.

7. An aircraft landing gear down position lock, characterized in that: It comprises the guiding and correcting device as described in any one of claims 1 to 6.

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