Aircraft landing light retraction adjustment drive and application

Abstract

The application discloses an aviation landing light retraction and deployment adjusting driving device and application, which is used for controlling aviation landing light retraction and deployment. The aviation landing light retraction and deployment adjusting driving device is composed of a device shell, a two-stage worm and gear pair, a driving motor, a gear assembly, a rack assembly and an angular displacement sensor and the like. The aviation landing light retraction and deployment adjusting driving device has the advantages that the structure is compact and reasonable, the space requirement is small, the work is reliable, and the aviation landing light retraction and deployment adjusting function can be realized in a small space volume.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aviation landing lights, in particular, an aviation landing light retraction adjustment driving device and application. BACKGROUND

[0002] In the field of aviation, the aviation landing light retraction adjustment driving device is used to drive the aviation landing light to retract and move, so as to adjust the distance of the light spot irradiation. The aviation landing light retraction adjustment driving device needs to stay and lock at the limit position of the aviation landing light retraction, the limit position of the aviation landing light retraction, and any position in between. Due to the limitation of space volume and weight, the aviation landing light retraction adjustment driving device is gradually reduced. At the same time, as the flight speed of the aircraft is gradually increased, the wind load resistance of the aviation landing light retraction adjustment driving device is gradually improved. Due to the difference in the consistency of different aircraft skins, the limit position of the aviation landing light retraction after installation, the limit position of the aviation landing light retraction, and the angle of the aviation landing light retraction adjustment driving device need to be adjusted. Due to the small space volume and the high load capacity required, there is currently no such aviation landing light retraction adjustment driving device. SUMMARY

[0003] The purpose of the present application is to solve the problem of the lack of aviation landing light retraction adjustment driving devices in the prior art, and to provide a new aviation landing light retraction adjustment driving device and application.

[0004] To achieve this purpose, the technical solution of the present application is as follows: an aviation landing light retraction adjustment driving device, comprising,

[0005] a device housing, the inside of which is arranged with a lower partition and an upper partition, and the inside of the device housing is separated into a lower cavity, a middle cavity and an upper cavity by the lower partition and the upper partition;

[0006] a two-stage worm and worm wheel pair arranged inside the lower cavity of the device housing, the two-stage worm and worm wheel pair having a first worm, a first worm wheel, a second worm and a second worm wheel, the first worm and the first worm wheel being meshed with each other, the second worm and the second worm wheel being meshed with each other, the first worm extending vertically, the second worm extending horizontally, the second worm and the first worm wheel having a common axis and being fixedly connected;

[0007] a driving motor below the device housing, the driving motor having a motor output shaft, the motor output shaft extending vertically, the motor output shaft entering the lower cavity of the device housing upwardly and being fixedly connected with the lower end of the first worm, the motor output shaft and the first worm having a common axis;

[0008] A gear assembly, disposed within the cavity of the housing, comprises a gear shaft and a full-tooth gear. The gear shaft is fixedly connected to the full-tooth gear. The lower end of the gear shaft passes through the lower partition and enters the lower cavity of the housing, where it is fixedly connected to the second worm gear. The gear shaft, the full-tooth gear, and the second worm gear share a common axis.

[0009] A rack assembly is arranged inside the cavity of the housing. The rack assembly has a rack vertical shaft and a sector rack. The rack vertical shaft is fixedly connected to the sector rack. The sector rack and the full gear are on the same horizontal plane and mesh with each other. The sector rack has a first end and a second end opposite to each other in the circumferential direction. A housing perforation is formed in the side wall of the cavity of the housing. The first end of the sector rack extends laterally out of the cavity of the housing from the housing perforation. The first end of the sector rack is used to be fixedly connected to the aviation landing light.

[0010] As a preferred embodiment of an aircraft landing light retraction and adjustment drive device, it also includes an angular displacement sensor arranged inside the upper cavity of the housing. The angular displacement sensor has a sensor output shaft that extends vertically. The lower end of the sensor output shaft passes downward through the upper partition and enters the middle cavity of the housing, where it is fixedly connected to the upper end of the gear vertical shaft. The sensor output shaft and the gear vertical shaft share a common axis.

[0011] As a preferred embodiment of an aviation landing light retraction and adjustment drive device, it further includes a sensor output shaft having an "I"-shaped protrusion, and the top surface of the gear vertical shaft having an "I"-shaped groove, with the protrusion inserted into the groove.

[0012] As a preferred embodiment of an aviation landing light retraction and adjustment drive device, the side wall of the lower cavity of the housing is formed with a housing oil inlet, through which lubricating oil is injected into the lower cavity of the housing to lubricate the secondary worm gear pair.

[0013] Furthermore, the oil inlet of the housing is completely sealed with a screw plug.

[0014] As a preferred embodiment of an aviation landing light retraction and adjustment drive device, the first worm, the first worm wheel, the second worm, and the second worm wheel all adopt a small module.

[0015] As a preferred embodiment of an aviation landing light retraction and adjustment drive device, the lower partition has a partition annular groove formed on the outer periphery of the gear vertical shaft. The opening of the partition annular groove faces inward. The partition annular groove and the gear vertical shaft together define a sealing annular cavity, and a sealing ring is arranged inside the sealing annular cavity.

[0016] As a preferred embodiment of an aircraft landing light retraction and adjustment drive device, the drive motor is an adjustable speed brushless DC motor.

[0017] As a preferred embodiment of an aviation landing light retraction and adjustment drive device, the first end of the fan-shaped rack has a flange connection portion, the flange connection portion has a connection hole, the aviation landing light has a connected hole corresponding to the connection hole, and a fixed connector is provided between the connected hole and the connection hole.

[0018] The present invention also discloses the application of an aircraft landing light retraction and adjustment drive device on an aircraft.

[0019] Compared with existing technologies, the advantages of this invention are at least as follows: It features a compact and reasonable structure, minimal space requirements, and reliable operation, enabling the retraction and adjustment of aircraft landing lights within a small space. The self-locking characteristic of the two-stage worm gear pair allows for wind resistance and locking of the aircraft landing light position at high flight speeds. An angular displacement sensor and corresponding drive circuit enable adjustable driving angles for the retraction and adjustment of the aircraft landing lights, thereby fulfilling the retraction and adjustment requirements and ensuring reliable aircraft flight. Attached Figure Description

[0020] Fig. 1 This is a schematic diagram of the structure of the present invention.

[0021] Fig. 2 This is a schematic diagram of the structure of the two-stage worm gear pair in this invention.

[0022] Fig. 3 This is a schematic diagram of the gear assembly in this invention.

[0023] Fig. 4 This is a schematic diagram of the rack and pinion assembly in this invention. Detailed Implementation

[0024] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. It should be noted that these descriptions are for the purpose of aiding understanding the invention and do not constitute a limitation thereof. Furthermore, the technical features involved in the various embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.

[0025] Please see Figs. 1 to 4 The figure shows an aircraft landing light retraction and extension adjustment drive device, used to control the retraction and extension of the aircraft landing light 1.

[0026] The aircraft landing light retraction and adjustment drive device consists of a device housing 2, a secondary worm gear pair 3, a drive motor 4, a gear assembly 5, a rack assembly 6, and an angular displacement sensor 7.

[0027] The device housing 2 is provided with a lower partition 21 and an upper partition 22, which divide the interior of the device housing 2 into a lower cavity 23, a middle cavity 24 and an upper cavity 25.

[0028] The secondary worm gear pair 3 is arranged inside the lower cavity 23 of the housing. The secondary worm gear pair 3 serves as a speed reduction transmission. The secondary worm gear pair 3 includes a first worm 31, a first worm wheel 32, a second worm 33, and a second worm wheel 34. The first worm 31 meshes with the first worm wheel 32. The second worm 33 meshes with the second worm wheel 34. The first worm 31 extends vertically. The second worm 33 extends horizontally. The second worm 33 and the first worm wheel 32 share a common axis and are fixedly connected.

[0029] Preferably, a housing oil inlet 231 may be formed on the side wall of the lower cavity 23 of the housing. Lubricating oil can be injected into the lower cavity 23 of the housing through the housing oil inlet 231 to lubricate the secondary worm gear pair 3. After injection, the housing oil inlet 231 can be completely sealed with a screw plug 232 to prevent lubricating oil inside the lower cavity 23 from leaking out through the housing oil inlet 231.

[0030] Preferably, the first worm 31, the first worm wheel 32, the second worm 33, and the second worm wheel 34 all adopt a small module.

[0031] The drive motor 4 is located below the housing 2 of the device. The drive motor 4 has a motor output shaft 41. The motor output shaft 41 extends vertically. The motor output shaft 41 enters the lower cavity 23 of the housing upward and is fixedly connected to the lower end of the first worm gear 31. The motor output shaft 41 and the first worm gear 31 share a common axis. The motor output shaft 41 moves synchronously with the first screw. Preferably, the motor output shaft 41 and the first worm gear 31 can be fixedly connected by fastening screws. In this embodiment, the drive motor 4 can be an adjustable speed brushless DC motor.

[0032] The gear assembly 5 and the rack assembly 6 are arranged inside the cavity 24 of the housing.

[0033] The gear assembly 5 has a gear vertical shaft 51 and a full-tooth gear 52. The gear vertical shaft 51 is fixedly connected to the full-tooth gear 52. The lower end of the gear vertical shaft 51 passes through the lower partition 21 and enters the lower cavity 23 of the housing, where it is fixedly connected to the second worm gear 34. The gear vertical shaft 51, the full-tooth gear 52, and the second worm gear 34 share a common axis.

[0034] Preferably, the lower partition 21 has a partition annular groove formed on the outer periphery of the gear vertical shaft 51. The opening of the partition annular groove faces inward. The partition annular groove and the gear vertical shaft 51 together define a sealing ring cavity. A sealing ring 211 is arranged inside the sealing ring cavity to prevent lubricating oil inside the lower cavity 23 of the housing from entering the middle cavity 24 of the housing upward.

[0035] The rack assembly 6 has a rack vertical shaft 61 and a sector rack 62. The rack vertical shaft 61 is fixedly connected to the sector rack 62. The sector rack 62 and the full-tooth gear 52 are on the same horizontal plane and mesh with each other. The sector rack 62 has a first end and a second end opposite each other in the circumferential direction. A housing through hole 241 is formed on the side wall of the housing cavity 24. The first end of the sector rack 62 extends laterally out of the housing cavity 24 through the housing through hole 241. The first end of the sector rack 62 is used for fixed connection with the aviation landing light 1.

[0036] Preferably, the first end of the fan-shaped rack 62 has a flange connection portion 621. The flange connection portion 621 has a connection hole. The aircraft landing light 1 has a connection hole corresponding to the connection hole. A connecting bolt, serving as a fixing member, is provided between the connection hole and the connection hole. Thus, the aircraft landing light 1 can be fixed to the first end of the fan-shaped rack 62.

[0037] The angular displacement sensor 7 is arranged inside the upper cavity 25 of the housing. The angular displacement sensor 7 has a sensor output shaft 71. The sensor output shaft 71 extends vertically. The lower end of the sensor output shaft 71 passes downward through the upper partition 22 into the middle cavity 24 of the housing and is fixedly connected to the upper end of the gear vertical shaft 51. The sensor output shaft 71 and the gear vertical shaft 51 have a common axis. The angular displacement sensor 7 is used to detect the rotation of the full-tooth gear 52 to indirectly know the rotation of the sector rack 62. Preferably, the sensor output shaft 71 has a "I"-shaped protrusion, and the top surface of the gear vertical shaft 51 has a "I"-shaped groove. The protrusion is inserted into the groove to achieve a fixed connection between the two. The angular displacement sensor 7 is connected to the drive control circuit. Using the angular displacement sensor 7 and the drive control circuit, the adjustable driving angle of the aircraft landing light 1 can be realized, thereby meeting the retraction and adjustment requirements of the aircraft landing light 1.

[0038] Preferably, the ends of the first worm 31, the second worm 33, the gear vertical shaft 51, and the rack vertical shaft 61 are all provided with support bearings.

[0039] Working process: The drive motor 4 is activated, and the motor output shaft 41 drives the first worm gear 31 to rotate. The first worm gear 31 drives the sector rack 62 to rotate sequentially through the first worm wheel 32, the second worm gear 33, the second worm wheel 34, the gear vertical shaft 51, and the full gear 52. The rotation of the sector rack 62 is the retraction and extension process of the aircraft landing light 1. The sector rack 62 can drive the aircraft landing light 1 to retract inward or extend outward, realizing the retraction and extension adjustment of the aircraft landing light 1 and the adjustable drive angle, thereby meeting the retraction and extension adjustment requirements of the aircraft landing light 1 and ensuring reliable flight of the aircraft.

[0040] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.

Claims

1. A retraction and adjustment drive device for an aircraft landing light, characterized in that, Includes, The device housing has a lower partition and an upper partition arranged inside, and the lower partition and the upper partition divide the interior of the device housing into a lower cavity, a middle cavity and an upper cavity. A two-stage worm gear pair is arranged inside the lower cavity of the housing. The two-stage worm gear pair has a first worm, a first worm wheel, a second worm, and a second worm wheel. The first worm and the first worm wheel mesh with each other, and the second worm and the second worm wheel mesh with each other. The first worm extends vertically, and the second worm extends horizontally. The second worm and the first worm wheel have a common axis and are fixedly connected to each other. A drive motor is located below the housing of the device. The drive motor has a motor output shaft that extends vertically and enters the lower cavity of the housing upwards, where it is fixedly connected to the lower end of the first worm gear. The motor output shaft and the first worm gear share a common axis. A gear assembly, disposed within the cavity of the housing, comprises a gear shaft and a full-tooth gear. The gear shaft is fixedly connected to the full-tooth gear. The lower end of the gear shaft passes through the lower partition and enters the lower cavity of the housing, where it is fixedly connected to the second worm gear. The gear shaft, the full-tooth gear, and the second worm gear share a common axis. A rack assembly is arranged inside the cavity of the housing. The rack assembly has a rack vertical shaft and a sector rack. The rack vertical shaft is fixedly connected to the sector rack. The sector rack and the full gear are on the same horizontal plane and mesh with each other. The sector rack has a first end and a second end opposite to each other in the circumferential direction. A housing perforation is formed in the side wall of the cavity of the housing. The first end of the sector rack extends laterally out of the cavity of the housing from the housing perforation. The first end of the sector rack is used to be fixedly connected to the aviation landing light.

2. The aircraft landing light retraction and adjustment drive device according to claim 1, characterized in that, It also includes an angular displacement sensor, which is arranged inside the upper cavity of the housing. The angular displacement sensor has a sensor output shaft that extends vertically. The lower end of the sensor output shaft passes downward through the upper partition and enters the middle cavity of the housing, and is fixedly connected to the upper end of the gear vertical shaft. The sensor output shaft and the gear vertical shaft have a common axis.

3. The aircraft landing light retraction and adjustment drive device according to claim 2, characterized in that, It also includes a sensor output shaft having an "I"-shaped protrusion, and the top surface of the gear vertical shaft having an "I"-shaped groove, with the protrusion inserted into the groove.

4. A flight landing light retraction and adjustment drive device according to any one of claims 1 to 3, characterized in that, The lower cavity of the housing has a housing oil inlet formed on its side wall. Lubricating oil is injected into the lower cavity of the housing through the housing oil inlet to lubricate the two-stage worm gear pair.

5. The aircraft landing light retraction and adjustment drive device according to claim 4, characterized in that, The oil inlet of the housing is completely sealed with a screw plug.

6. A flight landing light retraction and adjustment drive device according to any one of claims 1 to 3, characterized in that, The first worm, the first worm wheel, the second worm, and the second worm wheel all use a small module.

7. A flight landing light retraction and adjustment drive device according to any one of claims 1 to 3, characterized in that, The lower partition plate has a partition annular groove formed on the outer periphery of the gear vertical shaft. The opening of the partition annular groove faces inward. The partition annular groove and the gear vertical shaft together define a sealing ring cavity. A sealing ring is arranged inside the sealing ring cavity.

8. A flight landing light retraction and adjustment drive device according to any one of claims 1 to 3, characterized in that, The drive motor is an adjustable speed brushless DC motor.

9. A flight landing light retraction and adjustment drive device according to any one of claims 1 to 3, characterized in that, The first end of the fan-shaped rack has a flange connection portion, the flange connection portion has a connection hole, the aviation landing light has a connected hole corresponding to the connection hole, and a fixed connector is provided between the connected hole and the connection hole.

10. The application of an aircraft landing light retraction and adjustment drive device according to any one of claims 1 to 9 on an aircraft.

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