Aircraft landing light wind-borne vibration damping device and its application

Abstract

The present invention discloses a wind-borne vibration damping device for an aircraft landing light and its use. The aircraft landing light wind-borne vibration damping device is composed of a fixed base, a vertical guide sleeve, a fixed bracket and a support assembly. The support assembly comprises a vertical guide rod, an adjusting nut, a support spring, a ball holder and a rolling ball. The beneficial effect of the present invention is that the support spring in the support assembly can reduce or eliminate the wind-borne vibration of the aircraft landing light, thereby greatly improving the reliability and life of the aircraft landing light. The noise caused by the wind-borne vibration of the aircraft landing light can be reduced by using a rubber pad. If the aircraft landing light is not in a horizontal position, the rolling ball can be rotated during the force-bearing process to release forces other than the vertical force, and the specific position can be prevented from being continuously worn by rotating the rolling ball.

Description

Technical Field

[0001] The present invention relates to an aircraft landing light, in particular to a wind-borne vibration damping device for an aircraft landing light and a use thereof. Background Art

[0002] Aircraft landing lights vibrate due to wind loads and other factors during flight or ground surveys. This vibration not only creates noise but can also loosen fasteners in the mechanical components of the landing light actuator, reducing product reliability and lifespan. Furthermore, during ground surveys, the vibration of the landing light actuator can cause the emitted light spot to fluctuate, seriously compromising the safety of nighttime landings. The current solution to wind-induced vibration in landing lights is to strengthen the mechanical connections, but this is less than ideal. Summary of the Invention

[0003] The purpose of the present invention is to solve the problem of wind-borne vibration of aircraft landing lights in the prior art and to provide a novel wind-borne vibration damping device for aircraft landing lights and its use.

[0004] In order to achieve this purpose, the technical solution of the present invention is as follows: an aircraft landing light wind-borne vibration damping device comprises:

[0005] A fixed base, a top surface of which is formed with a base groove opening upward;

[0006] A vertical guide sleeve, comprising an upper guide sleeve section and a lower guide sleeve section having an outer diameter greater than that of the upper guide sleeve section, wherein the lower guide sleeve section is disposed inside the base groove;

[0007] a fixed bracket, comprising a bracket bottom wall, a bracket peripheral wall, and a bracket top wall, wherein the bracket bottom wall is positioned above the fixed base and the guide sleeve lower section and surrounds the outer periphery of the guide sleeve upper section, the bracket peripheral wall extends vertically upward from the inner edge of the bracket bottom wall, exceeds the top surface of the guide sleeve upper section, and surrounds the outer periphery of the guide sleeve upper section, and the bracket top wall extends horizontally inward from the top edge of the bracket peripheral wall and encloses a bracket opening; and

[0008] The supporting assembly comprises a vertical guide rod, an adjusting nut, a supporting spring, a ball holder and a rolling ball, wherein the vertical guide rod is placed inside the vertical guide sleeve, the vertical guide rod has a guide rod upper section and a guide rod lower section, the guide rod lower section is a screw section and is surrounded by the adjusting nut, the supporting spring is placed on the top surface of the adjusting nut and is surrounded between the vertical guide sleeve and the vertical guide rod, the top surface of the supporting spring supports the ball holder, the top surface of the ball holder supports the rolling ball, the supporting spring is in a compressed state and will press the top surface of the rolling ball against the bottom surface of the top wall of the bracket through the ball holder, the outer diameter of the rolling ball is larger than the inner diameter of the bracket orifice, so that the rolling ball has a portion that passes upward through the bracket orifice and the portion is used to press against the aircraft landing light actuator.

[0009] As a preferred solution for the wind-borne vibration damping device of the aircraft landing light, the bottom surface of the lower section of the guide sleeve is against the bottom surface of the base groove, the outer peripheral surface of the lower section of the guide sleeve is against the inner peripheral surface of the base groove, and the bottom surface of the bottom wall of the bracket is against the top surface of the fixed base and the top surface of the lower section of the guide sleeve respectively.

[0010] As a preferred solution for the wind-borne vibration damping device of the aircraft landing light, the inner peripheral surface of the bracket peripheral wall abuts against the outer peripheral surface of the upper section of the guide sleeve.

[0011] As a preferred solution for the wind-borne vibration damping device of an aircraft landing light, a connecting hole is formed on the bottom wall of the bracket, a connected hole corresponding to the connecting hole is formed on the fixed base, and a fixed connecting piece is provided between the connected hole and the connecting hole, so that the bottom wall of the bracket is fixedly connected to the fixed base.

[0012] As a preferred solution for the wind-borne vibration damping device of the aircraft landing light, the inner diameter of the upper section of the guide sleeve is smaller than the inner diameter of the lower section of the guide sleeve, and the adjusting nut is placed inside the lower section of the guide sleeve.

[0013] As a preferred solution for the wind-borne vibration damping device of the aircraft landing light, the inner circumference of the upper section of the guide sleeve and the inner circumference of the lower section of the guide sleeve are transitioned with a rounded corner.

[0014] As a preferred solution for the wind-borne vibration damping device of the aircraft landing light, the upper section of the guide rod is a polished rod section.

[0015] The present invention also provides a use of a wind-borne vibration damping device for an aircraft landing light, comprising: the wind-borne vibration damping device for the aircraft landing light; the portion passing upward through the bracket opening presses against the aircraft landing light to reduce or eliminate wind-borne vibration of the aircraft landing light.

[0016] As a preferred solution for the use of the wind-borne vibration damping device for an aircraft landing light, a rubber pad is arranged between the portion passing upward through the bracket opening and the aircraft landing light actuating device.

[0017] Compared to the prior art, the present invention offers at least the following advantages: the support spring in the support assembly can reduce or eliminate wind-induced vibrations in the aircraft landing light, thereby significantly improving the reliability and lifespan of the aircraft landing light. The rubber pad can also reduce noise caused by wind-induced vibrations in the aircraft landing light. If the aircraft landing light actuator is not in a horizontal position, the ball can be rotated during the force application process to release forces other than vertical forces. This rotation of the ball also prevents continued wear of specific locations. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural schematic diagram of the present invention. DETAILED DESCRIPTION

[0019] The present invention will be further described in detail below using specific embodiments in conjunction with the accompanying drawings. It should be noted that the description of these embodiments is intended to facilitate understanding of the present invention and does not constitute a limitation of the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0020] See Figure 1 , the figure shows a wind-borne vibration damping device for an aircraft landing light, which can be used to reduce or eliminate the wind-borne vibration of the aircraft landing light.

[0021] The damping device is composed of a fixed base 1, a vertical guide sleeve 2, a fixed bracket 3, screws 4 and a support assembly 5.

[0022] A base groove 11 opening upward is formed on the top surface of the fixed base 1 .

[0023] The vertical guide sleeve 2 is a cylindrical structure that extends from top to bottom. The vertical guide sleeve 2 comprises an upper guide sleeve section 21 and a lower guide sleeve section 22. The outer diameter of the upper guide sleeve section 21 is smaller than the outer diameter of the lower guide sleeve section 22. The lower guide sleeve section 22 is positioned within the base groove 11. Preferably, the bottom surface of the lower guide sleeve section 22 abuts against the bottom surface of the base groove 11, and the outer circumference of the lower guide sleeve section 22 abuts against the inner circumference of the base groove 11, so that the fixed base 1 achieves downward and horizontal positioning of the lower guide sleeve section 22.

[0024] The fixed bracket 3 comprises a bracket bottom wall 31, a bracket peripheral wall 32, and a bracket top wall 33. The bracket bottom wall 31 is arranged above the fixed base 1 and the guide sleeve lower section 22 and surrounds the outer periphery of the guide sleeve upper section 21. The bracket bottom wall 31 is formed with a connecting hole. The fixed base 1 is formed with a connected hole corresponding to the connecting hole. The screw 4, serving as a fixing member, is located between the connected hole and the connecting hole, thereby securely connecting the bracket bottom wall 31 to the fixed base 1. Preferably, the bottom surface of the bracket bottom wall 31 abuts against the top surface of the fixed base 1 and the top surface of the guide sleeve lower section 22, respectively, so that the bracket bottom wall 31 achieves upper positioning of the guide sleeve lower section 22. Furthermore, the top surface of the fixed base 1 is flush with the top surface of the guide sleeve lower section 22, i.e., the bottom surface of the bracket bottom wall 31 is flat, facilitating machining. The bracket peripheral wall 32 extends vertically upward from the inner edge of the bracket bottom wall 31 and rises above the top surface of the guide sleeve upper section 21. Preferably, the bracket peripheral wall 32 surrounds the outer periphery of the guide sleeve upper section 21, and the inner circumference of the bracket peripheral wall 32 abuts against the outer circumference of the guide sleeve upper section 21, so that the bracket peripheral wall 32 and the guide sleeve upper section 21 are horizontally positioned. The bracket top wall 33 extends horizontally inward from the top edge of the bracket peripheral wall 32 and encloses a bracket opening 330. The bracket opening 330 can be a circular hole.

[0025] The support assembly 5 has a vertical guide rod 51, an adjusting nut 52, a supporting spring 53, a ball holder 54 and a rolling ball 55. The vertical guide rod 51 is arranged inside the vertical guide sleeve 2. The vertical guide rod 51 has an upper guide rod section and a lower guide rod section. The bottom surface of the lower guide rod section is against the bottom surface of the base groove 11. The upper guide rod section is a smooth rod section, and the lower guide rod section is a threaded section. The lower guide rod section is surrounded by the adjusting nut 52. The supporting spring 53 is arranged above the adjusting nut 52 and the supporting spring 53 is surrounded between the vertical guide rod 51 and the upper guide sleeve section 21 to ensure that the supporting spring 53 will not be deflected or stuck during the compression process. Preferably, the inner diameter of the upper guide sleeve section 21 is smaller than the inner diameter of the lower guide sleeve section 22. The adjusting nut 52 is arranged inside the lower guide sleeve section 22. The inner circumference of the guide sleeve upper section 21 and the inner circumference of the guide sleeve lower section 22 are transitioned by an arc-shaped chamfer, further ensuring that the support spring 53 will not get stuck. The upper end of the support spring 53 supports the ball holder 54. The ball holder 54 supports the rolling ball 55. The ball holder 54 is formed with a concave surface that cooperates with the rolling ball 55. The support spring 53 is in a compressed state and the top surface of the rolling ball 55 is pressed against the bottom surface of the bracket top wall 33 through the ball holder 54. The outer diameter of the rolling ball 55 is larger than the inner diameter of the bracket opening 330, so that the rolling ball has a portion that passes upward through the bracket opening 330 and a portion that does not pass through the bracket opening 330. The portion that passes upward through the bracket opening 330 is used to press against the aircraft landing light actuator 7 to eliminate the vibration impact of the aircraft landing light actuator 7. By rotating the adjusting nut 52 , the adjusting nut 52 moves upward or downward along the vertical guide rod 51 to change the compression amount of the supporting spring 53 , thereby changing the magnitude of the upward elastic force to meet different damping requirements.

[0026] Preferably, a rubber pad 6 is arranged between the rolling ball 55 and the aircraft landing light actuator 7. The rubber pad 6 plays a role in shock absorption and noise reduction.

[0027] The damping device is used as follows: Based on the height position of the aircraft landing light actuator 7 and the force required to overcome the vibration of the aircraft landing light actuator 7, the adjusting nut 52 is rotated to change the supporting force of the support spring 53 to adapt the aircraft landing light actuator 7. The support spring 53 supports the aircraft landing light actuator 7 through the ball holder 54, the ball 55, and the rubber pad 6 (if provided), causing it to reach a static state, reducing or even completely eliminating the vibration of the aircraft landing light actuator 7. This reduces the vibration impact on the transmission components of the aircraft landing light actuator 7, prolongs its service life, and prevents the light spot of the aircraft landing light from shifting during ground surveys, thereby ensuring flight safety.

[0028] If the aircraft landing light actuator 7 is in a non-horizontal position, the ball 55 can rotate when subjected to force to release forces other than the vertical direction, and the specific position can be prevented from being continuously worn by rotating the ball.

[0029] The above merely describes the embodiments of the present invention, and the description is relatively specific and detailed, but it should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art can make a number of variations and improvements without departing from the concept of the present invention, and these are all within the scope of protection of the present invention. Therefore, the scope of protection of the patent of the present invention shall be based on the appended claims.

Claims

1. Aircraft landing light wind-borne vibration damping device, characterized in that: Contains, A fixed base, a top surface of which is formed with a base groove opening upward; A vertical guide sleeve, comprising an upper guide sleeve section and a lower guide sleeve section having an outer diameter greater than that of the upper guide sleeve section, wherein the lower guide sleeve section is disposed inside the base groove; a fixed bracket, comprising a bracket bottom wall, a bracket peripheral wall, and a bracket top wall, wherein the bracket bottom wall is positioned above the fixed base and the guide sleeve lower section and surrounds the outer periphery of the guide sleeve upper section, the bracket peripheral wall extends vertically upward from the inner edge of the bracket bottom wall, exceeds the top surface of the guide sleeve upper section, and surrounds the outer periphery of the guide sleeve upper section, and the bracket top wall extends horizontally inward from the top edge of the bracket peripheral wall and encloses a bracket opening; and The supporting assembly comprises a vertical guide rod, an adjusting nut, a supporting spring, a ball holder and a rolling ball, wherein the vertical guide rod is placed inside the vertical guide sleeve, the vertical guide rod has a guide rod upper section and a guide rod lower section, the guide rod lower section is a screw section and is surrounded by the adjusting nut, the supporting spring is placed on the top surface of the adjusting nut and is surrounded between the vertical guide sleeve and the vertical guide rod, the top surface of the supporting spring supports the ball holder, the top surface of the ball holder supports the rolling ball, the supporting spring is in a compressed state and will press the top surface of the rolling ball against the bottom surface of the top wall of the bracket through the ball holder, the outer diameter of the rolling ball is larger than the inner diameter of the bracket orifice, so that the rolling ball has a portion that passes upward through the bracket orifice and the portion is used to press against the aircraft landing light actuator.

2. The wind-borne vibration damping device for an aircraft landing light according to claim 1, characterized in that: The bottom surface of the guide sleeve lower section abuts against the bottom surface of the base groove, the outer circumference of the guide sleeve lower section abuts against the inner circumference of the base groove, and the bottom surface of the bracket bottom wall abuts against the top surface of the fixed base and the top surface of the guide sleeve lower section respectively.

3. The wind-borne vibration damping device for an aircraft landing light according to claim 1 or 2, characterized in that: The inner peripheral surface of the bracket peripheral wall abuts against the outer peripheral surface of the upper section of the guide sleeve.

4. The wind-borne vibration damping device for an aircraft landing light according to claim 1, characterized in that: The bottom wall of the bracket is formed with a connecting hole, and the fixed base is formed with a connected hole corresponding to the connecting hole. A fixed connector is provided between the connected hole and the connecting hole, so that the bottom wall of the bracket is fixedly connected to the fixed base.

5. The wind-borne vibration damping device for an aircraft landing light according to claim 1, characterized in that: The inner diameter of the upper section of the guide sleeve is smaller than the inner diameter of the lower section of the guide sleeve, and the adjusting nut is placed inside the lower section of the guide sleeve.

6. The wind-borne vibration damping device for an aircraft landing light according to claim 5, characterized in that: The inner circumference of the upper section of the guide sleeve and the inner circumference of the lower section of the guide sleeve are transitioned with a rounded corner.

7. The wind-borne vibration damping device for an aircraft landing light according to claim 1, characterized in that: The upper section of the guide rod is a polished rod section.

8. Application of the wind-borne vibration damping device for aircraft landing lights, characterized in that: It comprises the aircraft landing light wind-borne vibration damping device according to any one of claims 1 to 7; the portion passing upward through the bracket opening presses against the aircraft landing light actuating device to reduce or eliminate the wind-borne vibration of the aircraft landing light.

9. The use of the wind-borne vibration damping device for aircraft landing lights according to claim 8, characterized in that: A rubber pad is arranged between the portion passing upward through the bracket opening and the aircraft landing light actuating device.

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