An aircraft door position adjustment device
By using a threaded shaft and adjusting bolts to form a threaded pair, the problem of time-consuming and laborious traditional hatch adjustment is solved, enabling precise stepless adjustment of the hatch position and simplifying operation.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
- Filing Date
- 2023-12-28
- Publication Date
- 2026-05-15
AI Technical Summary
Traditional cabin door heading position adjustment is limited by the minimum thickness of the gasket, resulting in a large minimum offset and a time-consuming and laborious adjustment process.
The system uses a threaded shaft and adjusting bolts to form a threaded pair, which achieves stepless adjustment and precise control of the hatch position through the helical characteristics, avoiding repeated disassembly.
It achieves precise adjustment of the hatch position, is simple to operate, has a compact structure, and does not increase the weight of the hatch mechanism.
Smart Images
Figure CN117657425B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft door mechanism design, and specifically relates to an aircraft door position adjustment device. Background Technology
[0002] Traditionally, the heading position of a hatch is adjusted by adding washers, using washers of different thicknesses to achieve heading offset. This method has two drawbacks: first, it is limited by the minimum thickness of the washers, resulting in a relatively large minimum offset and making precise adjustment of the hatch position impossible; second, the adjustment process requires repeated disassembly and removal of the hatch, which is labor-intensive and time-consuming.
[0003] Therefore, it is desirable to have a technical solution to overcome or at least mitigate one of the aforementioned defects of the prior art. Summary of the Invention
[0004] The purpose of this application is to provide an aircraft door position adjustment device to solve at least one problem existing in the prior art.
[0005] The technical solution of this application is:
[0006] An aircraft door position adjustment device, comprising:
[0007] A rocker arm, one end of which is hinged to the main hinge of the hatch, and the other end is provided with a first through hole;
[0008] The hatch bulkhead includes a left hatch bulkhead and a right hatch bulkhead. The left hatch bulkhead is provided with a second through hole, and the right hatch bulkhead is provided with a third through hole.
[0009] A threaded shaft with an internal thread passes through the second through hole, the first through hole, and the third through hole in sequence and is hinged to the rocker arm and the hatch bulkhead. Limiting bushings are installed on the threaded shaft on both sides of the rocker arm by connecting bolts.
[0010] The support includes a left support and a right support, wherein the left support is fixedly connected to the left hatch bulkhead and the right support is fixedly connected to the right hatch bulkhead;
[0011] The adjusting bolts include a left adjusting bolt and a right adjusting bolt. The left adjusting bolt is connected to the left bolt of the threaded shaft, and the right adjusting bolt is connected to the right bolt of the threaded shaft.
[0012] In at least one embodiment of this application, rocker arm bushings are provided at both ends of the rocker arm at the connection points where they mate with the threaded shaft.
[0013] In at least one embodiment of this application, the end face of the limiting bushing abuts against the end face of the corresponding rocker arm bushing.
[0014] In at least one embodiment of this application, the hatch bulkhead is connected to the threaded shaft in conjunction with the hatch bulkhead bushing.
[0015] In at least one embodiment of this application, the threaded shaft is stepped, and the radial dimensions at both ends of the threaded shaft are greater than the radial dimension at the middle.
[0016] In at least one embodiment of this application, the threaded shaft is provided with limiting planes at both ends, and the support is provided with limiting portions. The limiting portions cooperate with the limiting planes to restrict the rotation of the threaded shaft.
[0017] In at least one embodiment of this application, the adjusting bolt is connected to the threaded shaft via a washer.
[0018] The invention has at least the following beneficial technical effects:
[0019] The aircraft door position adjustment device of this application utilizes the helical characteristics of the threaded pair to achieve stepless adjustment and precise control of the door position, which is easy to operate, avoids repeated disassembly of the door, has a simple structure, occupies little space, and does not significantly increase the weight of the door mechanism. Attached Figure Description
[0020] Figure 1 This is a schematic diagram of an aircraft cabin door position adjustment device according to one embodiment of this application;
[0021] Figure 2 This is a cross-sectional view of an aircraft cabin door position adjustment device according to one embodiment of this application;
[0022] Figure 3 This is a schematic diagram of a threaded shaft according to one embodiment of this application;
[0023] Figure 4 This is a schematic diagram of a support according to one embodiment of this application.
[0024] in:
[0025] 1-Adjusting bolt; 2-Washer; 3-Support; 4-Threaded shaft; 5-Limiting bushing; 6-Connecting bolt; 7-Rocker arm; 8-Door bulkhead. Detailed Implementation
[0026] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0027] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.
[0028] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.
[0029] This application provides an aircraft door position adjustment device, including: a rocker arm 7, a door frame 8, a threaded shaft 4, a support 3, and an adjusting bolt 1.
[0030] Specifically, such as Figure 1 , 2 As shown, one end of the rocker arm 7 is hinged to the main hinge of the hatch, and the other end is provided with a first through hole; the hatch bulkhead 8 includes a left hatch bulkhead and a right hatch bulkhead, the left hatch bulkhead is provided with a second through hole, and the right hatch bulkhead is provided with a third through hole; the threaded shaft 4 is provided with an internal thread, and the threaded shaft 4 passes through the second through hole, the first through hole, and the third through hole in sequence to be hinged to the rocker arm 7 and the hatch bulkhead 8. Limiting bushings 5 are installed on the threaded shaft 4 on both sides of the rocker arm 7 by connecting bolts 6, and the rocker arm 7 and the threaded shaft 4 are axially limited by the two limiting bushings 5; the support 3 includes a left support and a right support, the left support is fixedly connected to the left hatch bulkhead, and the right support is fixedly connected to the right hatch bulkhead; the adjusting bolt 1 includes a left adjusting bolt and a right adjusting bolt, the left adjusting bolt is connected to the left bolt of the threaded shaft 4, and the right adjusting bolt is connected to the right bolt of the threaded shaft 4.
[0031] In a preferred embodiment of this application, rocker arm 7 is provided with rocker arm bushings at both ends of the rocker arm 7 at the connection points with the threaded shaft 4, and the end face of the limiting bushing 5 abuts against the end face of the corresponding rocker arm bushing.
[0032] In a preferred embodiment of this application, the hatch bulkhead 8 is connected to the threaded shaft 4 in conjunction with the hatch bulkhead bushing.
[0033] In the preferred embodiment of this application, such as Figure 3 As shown, the threaded shaft 4 is stepped, with the radial dimensions at both ends being larger than those at the middle. Mounting holes for connecting bolts 6 are provided on it. In this embodiment, limiting planes are provided at both ends of the threaded shaft 4, and a limiting part is provided on the support 3. The limiting part cooperates with the limiting planes to restrict the rotation of the threaded shaft 4.
[0034] In a preferred embodiment of this application, the adjusting bolt 1 is connected to the threaded shaft 4 in conjunction with the washer 2.
[0035] The aircraft door position adjustment device of this application has a threaded shaft 4 that sequentially passes through bushing holes on the left door bulkhead, rocker arm 7, and right door bulkhead. The end face of the limiting bushing 5 contacts the bushing end faces at both ends of the rocker arm 7 and is fixed to the threaded shaft 4 by connecting bolts 6, thus limiting the axial movement of the rocker arm 7, with only one rotational degree of freedom between them. The adjusting bolt 1 and the threaded shaft 4 form a threaded pair; turning the adjusting bolt 1 drives the threaded shaft 4, which in turn drives the rocker arm 7 to slide axially. The support 3 is fixed to the door bulkhead 8. The cylindrical surfaces at both ends of the threaded shaft 4 are partially flattened and fit against the limiting surface of the support 3 to form a linear pair, preventing rotation of the threaded shaft 4 during adjustment and ensuring that the threaded shaft 4 and rocker arm 7 only undergo axial translation during adjustment. Since the door bulkhead 8 remains stationary relative to the ground, the door will undergo axial translation during adjustment, thus adjusting the door position. The specific adjustment amount can be determined by leaving a gap between the limiting bushing 5 and the bushing end faces of the door bulkhead 8.
[0036] During installation of the aircraft cabin door position adjustment device of this application, after inserting the threaded shaft 4 into the holes on the cabin door frame 8, rocker arm 7 and limiting bushing 5, and confirming that the limiting bushing 5 and rocker arm bushing are in contact, the limiting bushing 5 and the threaded shaft 4 are fixedly connected with the connecting bolt 6. Then, the corresponding support 3 and washer 2 are installed. Finally, the adjusting bolt 1 is screwed in to clamp the washer 2 and the support 3.
[0037] The aircraft door position adjustment device of this application utilizes the helical characteristics of a threaded pair to achieve stepless adjustment and precise control of the door position. The specific adjustment amount can be determined by leaving a gap between the limit bushing 5 and the bushing end face of the door frame 8. This application designs a stepless adjustment device using the helical characteristics of a threaded pair, achieving precise control of the door position. Adjustment only requires turning the adjusting nut 1, which is simple to operate, avoids repeated disassembly of the door, and has a simple structure, occupies little space, and does not significantly increase the weight of the door mechanism.
[0038] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. An aircraft cabin door position adjustment device, characterized in that, include: Rocker arm (7), one end of which is hinged to the main hinge of the hatch, and the other end is provided with a first through hole; The hatch bulkhead (8) includes a left hatch bulkhead and a right hatch bulkhead. The left hatch bulkhead is provided with a second through hole, and the right hatch bulkhead is provided with a third through hole. The threaded shaft (4) is provided with an internal thread. The threaded shaft (4) passes through the second through hole, the first through hole, and the third through hole in sequence and is hinged to the rocker arm (7) and the cabin door frame (8). Limiting bushings (5) are installed on the threaded shaft (4) on both sides of the rocker arm (7) by connecting bolts (6). Support (3), including a left support and a right support, wherein the left support is fixedly connected to the left hatch frame and the right support is fixedly connected to the right hatch frame; Adjusting bolt (1) includes a left adjusting bolt and a right adjusting bolt. The left adjusting bolt is connected to the left bolt of the threaded shaft (4), and the right adjusting bolt is connected to the right bolt of the threaded shaft (4). The threaded shaft (4) has limiting planes at both ends, and the support (3) has limiting parts. The limiting parts cooperate with the limiting planes to restrict the rotation of the threaded shaft (4).
2. The aircraft door position adjustment device according to claim 1, characterized in that, At both ends of the rocker arm (7), rocker arm bushings are respectively provided at the connection points where it mates with the threaded shaft (4).
3. The aircraft door position adjustment device according to claim 2, characterized in that, The end face of the limiting bushing (5) abuts against the end face of the corresponding rocker arm bushing.
4. The aircraft door position adjustment device according to claim 1, characterized in that, The hatch bulkhead (8) is connected to the threaded shaft (4) in conjunction with the hatch bulkhead bushing.
5. The aircraft door position adjustment device according to claim 1, characterized in that, The threaded shaft (4) is stepped, and the radial dimensions at both ends of the threaded shaft (4) are greater than the radial dimensions at the middle.
6. The aircraft door position adjustment device according to claim 1, characterized in that, The adjusting bolt (1) is connected to the threaded shaft (4) in conjunction with the washer (2).