Airplane cabin door sensor target adjusting mechanism and use method thereof

Abstract

The invention discloses an aircraft cabin door sensor target adjusting mechanism and a use method thereof, belongs to the technical field of cabin door mechanism design, and particularly relates to attitude control of a target monitored by a sensor in an aircraft cabin door mechanism, reliable alignment and reliable induction of the target and the sensor are achieved through axial adjustment and circumferential adjustment of the target, and the target can be accurately adjusted. The target is clamped on the front support arm through the double nuts, the distance requirement of the target and a sensor probe is reliably guaranteed, the angle of the front support arm relative to the rear support arm is driven through the adjusting rod screwed on the rear support arm, and the angle requirement of the target relative to the sensor is guaranteed. Accurate adjustment of the cabin door mechanism sensor is achieved, the problem that in the assembling and maintaining process of an existing cabin door, mechanism adjustment restricts a sensor detection mechanism is solved, the influence of the posture of the cabin door mechanism on sensor signal output is avoided, and the adjusting mechanism is easy to operate, accurate in position and low in cost.

Description

Technical Field

[0001] The present invention belongs to the field of civil aircraft door mechanisms, and relates to the design of adjustment measures for sensor targets installed on civil aircraft door mechanisms, and particularly relates to an aircraft door sensor target adjustment mechanism and its usage method. Background Art

[0002] At present, the key mechanism state of an aircraft door usually needs to be monitored for its motion posture by sensors, and attitude adjustment needs to be carried out according to various technical indicators during assembly or maintenance. After the function of the door mechanism is realized, the monitoring target of the sensor often has a certain position deviation along with the mechanism. In order to ensure that the sensor can correctly output the state signal of the monitored mechanism, reasonable target adjustment measures must be available to adapt to the attitude of the door mechanism and ensure that the target can be correctly aligned with the sensor after the door mechanism is adjusted. However, the traditional installation method of the sensor and the target lacks convenient and simple adjustment measures, which restrict each other between the adjustment of the door mechanism and the adjustment of the sensor monitoring signal, are difficult to coordinate, have complex operations, and are time-consuming and laborious.

[0003] The present invention realizes stepless and precise attitude adjustment of the target in the form of a regulating rod driving a front support arm, without repeatedly coordinating the door mechanism, which is efficient and convenient, and saves assembly costs, maintenance costs, etc. Summary of the Invention

[0004] The purpose of the present invention is to provide an aircraft door sensor target adjustment mechanism, which can effectively solve the problems in the background art.

[0005] In order to achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0006] An aircraft door sensor target adjustment mechanism, the aircraft door sensor target adjustment mechanism is installed on the door structure, and includes a support 2, a sensor 4, a target 5, a front support arm 7, a regulating rod 9, a regulating shaft 10, a rear support arm 13, and a mechanism shaft 14. Specifically:

[0007] The sensor 4 is clamped on the support 2 by a first nut 3, and the support 2 is fixedly connected to the door structure 1. The target 5 is clamped on the front support arm 7 by two second nuts 6. The front support arm 7 is hinged to the rear support arm 13, the rear support arm 13 is fixedly connected to the mechanism shaft 14, and the mechanism shaft 14 is hinged to the door structure 1. The front end of the regulating rod 9 is hinged to the front support arm 7, the rear end of the regulating rod 9 is screwed to the regulating shaft 10 through a regulating nut 11, and the regulating shaft 10 is hinged to the front end of the rear support arm 13; the end of the regulating rod 9 is screwed to a third nut 12, and the third nut 12 is outside the regulating nut 11.

[0008] Further, the rear end of the front support arm 7 is hinged to the front end of the rear support arm 13 through a second hinge shaft 15.

[0009] Further, the double-forked ear 22 at the front end of the adjusting rod 9 is hinged to the front support arm 7 through the first hinge shaft 8. The rear end of the adjusting rod 9 is screwed to the adjusting nut 11, and the adjusting nut 11 is screwed to the adjusting shaft 10. By rotating the adjusting nut 11, the adjusting nut 11 will drive the adjusting rod 9 to expand and contract, and the front support arm 7 will rotate around the second hinge shaft 15 on the rear support arm 13, and the front support arm 7 will drive the target 5 to achieve rotational adjustment.

[0010] Further, the first hinge shaft 8, the adjusting shaft 10, and the second hinge shaft 15 are all stepped shafts. The other ends of the stepped shafts are respectively restricted from axial movement by the first circlip 16, the second circlip 17, and the third circlip 18, playing the role of hinge pairs for the adjustment movement of the mechanism.

[0011] Further, there are two parallel clamping planes 19 on the target 5 for clamping tools during installation or adjustment. A threaded rod 20 for sleeving the second nut 6 is provided at the tail of the target 5. The two second nuts 6 clamp the target 5 on the front support arm 7. Adjusting the two second nuts 6 will complete the position adjustment of the target 5 relative to the front support arm 7, realizing the axial position adjustment of the target 5 until the clearance requirement between the target 5 and the sensor 4 is met.

[0012] Further, the front end of the adjusting rod 9 is provided with a double-forked ear 22, and the tail of the adjusting rod 9 is provided with a right-handed thread 21.

[0013] Further, the adjusting nut 11 is integrally formed by a front end and a rear end, and has a through hole inside. The front end is a hexagonal head 24, and the hexagonal head 24 is a clamping surface for the adjustment operation of the mechanism. The rear end is a rod-shaped structure, which is provided with an external thread, specifically a left-handed thread 25. The inner hole of the adjusting nut 9 is provided with a thread structure, specifically a right-handed thread 23. The adjusting nut 11 and the adjusting rod 9 are matched through the right-handed thread 21. By rotating the adjusting nut 11, the adjusting nut 11 will move relative to the adjusting rod 9 in the front and rear positions.

[0014] Further, the adjusting shaft 10 is in the form of a stepped shaft. One end is characterized by a boss, and the other end is a groove. The third circlip 18 will be placed in the groove. The adjusting shaft 10 is hinged in the rear support arm 13, and the boss and the third circlip 18 jointly realize the axial limit of the adjusting shaft 10. The inner hole of the adjusting shaft 10 is matched with the left-handed thread 25 of the adjusting nut 11. By rotating the adjusting nut 11, the adjusting nut 11 will move relative to the adjusting shaft 10 in the front and rear positions.

[0015] Further, the rear end of the rear support arm 13 is fixedly connected to the mechanism shaft 14.

[0016] Further, the third nut 12 is arranged at the rear end of the adjusting nut 11 for fixing its relative position.

[0017] A method for using a target adjusting mechanism of an aircraft cabin door sensor, comprising the following steps:

[0018] First, the target 5 is clamped by two second nuts 6. By adjusting the axial position of the second nut 6 relative to the target 5, the target 5 is driven to move relative to the front support arm 7, thereby realizing the gap adjustment of the target 5 relative to the sensor 4. When the gap reaches the appropriate position, tighten the second nut 6 to achieve the axial locking of the target 5.

[0019] Second, rotate the adjusting nut 11 to drive the adjusting rod 9 to achieve telescopic movement. The adjusting rod 9 drives the front support arm 7 to rotate around the second hinge shaft 15 on the rear support arm 13, and the front support arm 7 drives the target 5 to achieve rotational adjustment.

[0020] Finally, the adjusting nut 11 is screwed onto the adjusting shaft 10. When the adjusting nut 11 pulls the adjusting rod 9 to expand and contract, the adjusting nut 11 drives the adjusting shaft 10 to rotate relative to the rear support arm 13. When the target 5 rotates to the correct position under the action of the adjusting rod 9, tighten the third nut 12 to complete the locking.

[0021] The present invention has the following advantages and beneficial effects:

[0022] (1) Convenient operation. The present invention uses a thread pair as the adjustment drive. During the assembly process of the mechanism, only a wrench needs to be used to rotate the nut to achieve the axial adjustment and circumferential adjustment of the target relative to the sensor, without repeatedly coordinating the states of the cabin door mechanism and the sensor mechanism, greatly reducing the adjustment difficulty and improving the work efficiency.

[0023] (2) Precise adjustment. The present invention adopts pure thread transmission, with a simple structure, precise adjustment, fully realizing stepless precise adjustment, high reliability, and convenient installation and debugging.

[0024] (3) Cost saving. The present invention only needs to use simple tools for adjustment operations, without repeated disassembly and assembly, greatly reducing the adjustment and maintenance man-hours of the cabin door, and significantly saving the manufacturing and maintenance costs of the cabin door.

[0025] (4) Wide application range. The present invention has a compact structure and good applicability, and can be widely applied to the attitude monitoring of the rotating mechanisms of various cabin doors, and can also be used for the stepless precise adjustment of other mechanical products. Description of the Drawings

[0026] Figure 1 It is an axonometric view of a target adjusting mechanism of an aircraft cabin door sensor;

[0027] Figure 2 It is a connection diagram of a target adjusting mechanism of an aircraft cabin door sensor;

[0028] Figure 3Schematic diagram of shaft connection for a target adjusting mechanism of an aircraft cabin door sensor;

[0029] Figure 4 Schematic diagram of target connection for a target adjusting mechanism of an aircraft cabin door sensor;

[0030] Figure 5 Schematic diagram of adjusting rod for a target adjusting mechanism of an aircraft cabin door sensor;

[0031] Figure 6 Schematic diagram of adjusting nut for a target adjusting mechanism of an aircraft cabin door sensor;

[0032] Figure 7 Schematic diagram of adjusting shaft for a target adjusting mechanism of an aircraft cabin door sensor;

[0033] Figure 8 Schematic diagram of adjusting shaft fitting for a target adjusting mechanism of an aircraft cabin door sensor;

[0034] Figure 9 Schematic diagram of adjusting rod fitting for a target adjusting mechanism of an aircraft cabin door sensor;

[0035] Figure 10 Schematic diagram of adjusting assembly for a target adjusting mechanism of an aircraft cabin door sensor.

[0036] In the figure: 1 cabin door structure; 2 support; 3 first nut; 4 sensor; 5 target; 6 second nut; 7 front support arm; 8 first hinge shaft; 9 adjusting rod; 10 adjusting shaft; 11 adjusting nut; 12 third nut; 13 rear support arm; 14 mechanism shaft; 15 second hinge shaft; 16 first circlip; 17 second circlip; 18 third circlip; 19 clamping plane; 20 threaded rod; 21 right - hand thread; 22 double - fork ear; 23 right - hand thread; 24 hexagon head; 25 left - hand thread; 26 inner hole. Detailed implementation mode

[0037] To make the technical solutions and their advantages of this application clearer, the technical solutions of this application will be further described clearly and completely below in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of this application, which are only used to explain the mechanism principle of this application and not to limit this application. The accompanying drawings are not drawn to scale, but are only appropriately simplified drawings for illustrating the basic principles and various features of the present invention. The specific design features disclosed in this application, such as specific dimensions, directions, positions, and shapes, will be partially determined by the specific application and usage environment.

[0038] It should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments and technical features in the embodiments of the present application can be combined with each other to obtain new embodiments.

[0039] In addition, it should be noted that, unless otherwise clearly specified and defined, the terms such as "installation" and "fixed connection" used in the description of the present application should be understood in a broad sense. For example, the fixed connection can be achieved by riveting, or by bolting, or by the connection inside two components. Those skilled in the art can understand their specific meanings in the present application according to the specific situation.

[0040] The mechanism of the present invention will be described in detail below with reference to the drawings:

[0041] See Figure 1 , which is an axonometric view of the target adjustment mechanism for the aircraft cabin door sensor. The support 2 is fixedly connected to the cabin door structure 1. The sensor 4 is clamped on the support 2 by two first nuts 3. The target 5 is clamped on the front support arm 7 by two second nuts 6. The front support arm 7 is hinged to the rear support arm 13 by a hinge shaft 15. The rear support arm 13 is fixedly connected to the mechanism shaft 14. The mechanism shaft 14 is hinged to the cabin door structure 1. The front end of the adjusting rod 9 is hinged to the front support arm 7 by a hinge shaft 8. The rear end of the adjusting rod 9 is screwed to an adjusting nut 11. The adjusting nut 11 is screwed to an adjusting shaft 10. The adjusting shaft 10 is hinged to the rear support arm 13. A third nut 12 is screwed to the adjusting rod 9.

[0042] See Figure 2 , which is a connection schematic diagram of the target adjustment mechanism for the aircraft cabin door sensor. With the target 5 clamped by two second nuts 6, by adjusting the axial position of the second nuts 6 relative to the target 5, the target 5 is driven to move relative to the front support arm 7, realizing the gap adjustment of the target 5 relative to the sensor 4. When the gap reaches the appropriate position, tighten the second nuts 6 to achieve the axial locking of the target 5. The front support arm 7 is hinged to the rear support arm 13 by a second hinge shaft 15. The double fork ears 22 at the front end of the adjusting rod 9 are hinged to the front support arm 7 by a first hinge shaft 8. The rear end of the adjusting rod 9 is screwed to the adjusting shaft 10 through the adjusting nut 11. The adjusting shaft 10 is hinged to the rear support arm 13. Rotate the adjusting nut 11, and the adjusting nut will drive the adjusting rod 9 to expand and contract. The front support arm 7 will rotate around the second hinge shaft 15 on the rear support arm 13, and the front support arm 7 drives the target 5 to achieve rotational adjustment.

[0043] See Figure 3 , which is a shaft connection schematic diagram of the target adjustment mechanism for the aircraft cabin door sensor. The hinge shaft 8, the adjusting shaft 10, and the hinge shaft 15 are all stepped shafts. The other ends of the stepped shafts are respectively restricted from axial movement by circlips 16, 17, and 18, playing the role of hinge pairs for the mechanism adjustment movement.

[0044] SeeFigure 4 , which is a target connection schematic diagram of the target adjustment mechanism of the aircraft door sensor. There are two parallel clamping planes 19 on the target 5, which are used for tool clamping during installation or adjustment. The tail feature of the target 5 is a threaded rod 20. Two second nuts 6 clamp the target 5 on the front support arm 7. Adjusting the two second nuts 6 will complete the position adjustment of the target 5 relative to the front support arm 7, and realize the axial position adjustment of the target 5 until the gap requirement from the target 5 to the sensor 4 is met.

[0045] See also Figure 5 , which is a schematic diagram of an adjustment rod of a target adjustment mechanism of an aircraft door sensor, the front end of the adjustment rod 9 is characterized by a double fork ear 22, and the rear end of the adjustment rod 9 is characterized by a right-hand thread 21.

[0046] See also Figure 6 , schematic diagram of the adjustment nut of the target adjustment mechanism of the aircraft door sensor, the end feature of the adjustment nut 11 is a hexagonal head 24, the hexagonal head 24 is used as a clamping surface for the mechanism adjustment operation, the outer surface feature of the adjustment nut 9 is a left-handed thread 25, and the inner hole feature of the adjustment nut 9 is a right-handed thread 23.

[0047] See also Figure 7 , which is a schematic diagram of the adjustment shaft of the target adjustment mechanism of the aircraft door sensor. The adjustment shaft 10 is in the form of a stepped shaft, one end of which is characterized by a boss and the other end is a slot. The third retaining spring 18 is placed in the slot. The adjustment shaft 10 is hinged in the rear support arm 13. The boss and the retaining spring 18 jointly realize the axial limit of the adjustment shaft 10.

[0048] See also Figure 8 , which is a schematic diagram of the adjustment shaft coordination of the aircraft door sensor target adjustment mechanism. The adjustment shaft 10 and the adjustment nut 11 are coordinated through the left-handed thread 25. Rotating the adjustment nut 11 will enable the adjustment nut 11 to move forward and backward relative to the adjustment shaft 10.

[0049] See also Figure 9 , which is a schematic diagram of the adjustment rod coordination of the aircraft door sensor target adjustment mechanism, the adjustment nut 11 and the adjustment rod 9 are coordinated through the right-hand thread 21, and rotating the adjustment nut 11 will enable the adjustment nut 11 to move forward and backward relative to the adjustment rod 9.

[0050] See also Figure 10, which is a schematic diagram of the adjustment component of the target adjustment mechanism for the aircraft cabin door sensor. When the adjustment nut 11 is rotated, the nut moves axially relative to the adjustment shaft 10, and at the same time, the adjustment rod 9 moves axially along the adjustment nut. Since the outer surface of the adjustment nut 11 has a left-handed thread 25 and the inner hole of the adjustment nut 11 has a right-handed thread 23, when the adjustment nut 11 is rotated clockwise, the adjustment nut 11 moves left relative to the adjustment shaft 10, and the adjustment rod 9 also moves left relative to the adjustment nut 11. The adjustment shaft 10 rotates and follows the rear support arm 13. At this time, the adjustment rod drives the front support arm 7 to rotate counterclockwise, and the front support arm 7 drives the target 5 to rotate counterclockwise. Conversely, the target 5 rotates clockwise, thereby realizing the angle adjustment of the target 5 relative to the sensor 4. After the adjustment is completed, tighten the nut 12 to lock the nut 12 and the adjustment nut 11 on the adjustment shaft 9.

[0051] The above-described embodiments only represent the implementation modes of the present invention, but should not be construed as limiting the scope of the present invention patent. It should be noted that for those skilled in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention.

Claims

1. An aircraft door sensor target adjustment mechanism, characterized in that: The aircraft door sensor target adjustment mechanism is installed on the door structure, and comprises a support (2), a sensor (4), a target (5), a front support arm (7), an adjustment rod (9), an adjustment shaft (10), a rear support arm (13), and a mechanism shaft (14). Specifically: The sensor (4) is clamped on the support (2) through a first nut (3), and the support (2) is fixedly connected to the door structure (1); the target (5) is clamped on the front support arm (7) through two second nuts (6); the front support arm (7) is hinged to the rear support arm (13), the rear support arm (13) is fixedly connected to the mechanism shaft (14), and the mechanism shaft (14) is hinged to the door structure (1); the front end of the adjustment rod (9) is hinged to the front support arm (7), the rear end of the adjustment rod (9) is screwed to the adjustment shaft (10) through an adjustment nut (11), and the adjustment shaft (10) is hinged to the front end of the rear support arm (13); the end of the adjustment rod (9) is screwed to the third nut (12), wherein the third nut (12) is outside the adjustment nut (11).

2. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The rear end of the front support arm (7) is hinged to the front end of the rear support arm (13) via a second hinge shaft (15).

3. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The double fork ears (22) at the front end of the adjusting rod (9) are hinged to the front support arm (7) through the first hinge shaft (8), the rear end of the adjusting rod (9) is screwed to the adjusting nut (11), and the adjusting nut (11) is screwed to the adjusting shaft (10).

4. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The first hinge shaft (8), the adjustment shaft (10) and the second hinge shaft (15) are all stepped shafts, and the other ends of the stepped shafts are respectively restricted from axial movement by the first retaining spring (16), the second retaining spring (17) and the third retaining spring (18), thereby playing the role of a hinge pair.

5. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The target (5) is provided with two parallel clamping planes (19) for clamping tools during installation or adjustment. The tail of the target (5) is provided with a threaded rod (20) for sleeve-connecting a second nut (6). The two second nuts (6) clamp the target (5) on the front support arm (7). The position of the target (5) relative to the front support arm (7) can be adjusted by adjusting the two second nuts (6).

6. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: Furthermore, the front end of the adjusting rod (9) is provided with a double fork ear (22), and the rear end of the adjusting rod (9) is provided with a right-hand thread 21.

7. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The adjusting nut (11) is formed by integrating the front end and the rear end, and a through hole is provided inside the adjusting nut; the front end is a hexagonal head (24), and the hexagonal head (24) is used as a clamping surface for mechanism adjustment operation; the rear end is a rod-shaped structure, which is provided with a left-handed thread (25); the inner hole of the adjusting nut 9 is provided with a right-handed thread (23).

8. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The adjusting shaft (10) is in the form of a stepped shaft, one end of which is characterized by a boss and the other end is a slot. The third retaining spring (18) is placed in the slot. The adjusting shaft 10 is hinged in the rear support arm (13). The boss and the third retaining spring (18) jointly realize the axial limit of the adjusting shaft (10).

9. The aircraft door sensor target adjustment mechanism according to claim 1, characterized in that: The third nut (12) is arranged at the rear end of the adjusting nut (11).

10. A method for using the target adjustment mechanism of an aircraft door sensor according to any one of claims 1 to 9, characterized in that: The following steps are involved: First, the target (5) is clamped by two second nuts (6), and the axial position of the second nuts (6) relative to the target (5) is adjusted to drive the target (5) to move relative to the front support arm (7), thereby adjusting the gap between the target (5) and the sensor (4). When the gap reaches a suitable position, the second nuts (6) are tightened to achieve axial locking of the target (5); Secondly, the adjusting nut (11) is rotated to drive the adjusting rod (9) to realize telescopic movement, the adjusting rod (9) drives the front support arm (7) to rotate around the second hinge shaft (15) on the rear support arm (13), and the front support arm (7) drives the target (5) to realize rotation adjustment; Finally, the adjusting nut (11) is threadedly connected to the adjusting shaft (10). When the adjusting rod (9) is pulled to extend and retract by the adjusting nut (11), the adjusting nut (11) drives the adjusting shaft (10) to rotate relative to the rear support arm (13). When the target (5) is rotated to a correct position under the action of the adjusting rod (9), the third nut (12) is tightened to complete the locking.

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