An aircraft door inboard and outboard handle mechanism
By designing components such as rocker arm pivot, fixed shaft, and outer handle pivot, the problems of complex assembly and poor maintainability of aircraft cabin door handle mechanisms in the existing technology have been solved, achieving the effect of the handle being flush with the skin in the closed state and the differential use of the inner and outer handles.
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
- 2023-12-31
- Publication Date
- 2026-05-19
AI Technical Summary
The existing aircraft cabin door handle mechanism is difficult to achieve a differential effect, and its assembly is complex and maintainability is poor.
It adopts components such as rocker arm pivot, fixed shaft, outer handle pivot, tension spring and limit bolt. Through the cooperation of arc groove and L-shaped groove, the differential use of inner and outer handle is realized, and the limit bolt and stop plate are used for limiting.
The design allows the hatch handle to be flush with the skin when closed, and enables differential use of the inner and outer handles, simplifying the assembly process and improving maintainability and stability.
Smart Images
Figure CN117905341B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft cabin door handle mechanisms, and specifically relates to an aircraft cabin door handle mechanism for both inside and outside. Background Technology
[0002] Aircraft emergency exits, maintenance doors, and boarding doors need to be able to open from both inside and outside, and when closed, the door handles need to be flush with the skin. Doors are typically equipped with retractable inner and outer handles. Generally, coaxial inner and outer handle mechanisms are fixedly connected, making it difficult to achieve a differential effect. In contrast, inner and outer handles that achieve a differential effect often use multi-layered nesting of irregularly shaped slots, resulting in complex assembly and poor maintainability.
[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 cabin door handle mechanism to solve at least one problem existing in the prior art.
[0005] The technical solution of this application is:
[0006] An aircraft cabin door handle mechanism, comprising:
[0007] A rocker arm pivot, one end of which is fixedly fitted with an inner handle, and the interior of the rocker arm pivot has a first receiving space, and the side wall of the rocker arm pivot has a first limiting hole.
[0008] A fixed shaft is nested in the first accommodating space. One end of the fixed shaft is provided with a spring pull tab, and the other end is fixedly installed with a handle box. The interior of the fixed shaft is provided with a second accommodating space, and an arc-shaped groove is provided on the side wall of the fixed shaft.
[0009] An outer handle pivot is nested in the second receiving space. One end of the outer handle pivot is connected to the outer handle via a pin. An L-shaped groove is provided on the side wall of the outer handle pivot.
[0010] A tension spring, one end of which is connected to the spring tab, and the other end of which is connected to the pin.
[0011] The limiting bolt is inserted into the first limiting hole, the arc-shaped groove, and the L-shaped groove, and works with the stop piece to limit the rocker arm shaft, the fixed shaft, and the outer handle shaft.
[0012] In at least one embodiment of this application, a connecting lug is provided on the rocker arm shaft.
[0013] In at least one embodiment of this application, the connecting ear piece includes connecting one ear and connecting both ears.
[0014] In at least one embodiment of this application, a second limiting hole is provided on the handle box, and a limiting pin is installed on the outer handle, the limiting pin being used to cooperate with the second limiting hole on the handle box.
[0015] In at least one embodiment of this application, the inner handle, the rocker arm pivot, the fixed shaft, the handle box, the outer handle pivot, the outer handle, the spring pull plate, and the stop plate are all machined parts made of 7050 aluminum alloy.
[0016] In at least one embodiment of this application, the limiting pin, the pin shaft, and the limiting bolt are all machined parts made of 0Cr13Ni8Mo2Al stainless steel.
[0017] The invention has at least the following beneficial technical effects:
[0018] The aircraft cabin door inner and outer handle mechanism of this application has an arc-shaped groove on the fixed shaft and an L-shaped groove at the outer handle pivot to cooperate with the movement of the cabin door handle mechanism, according to the opening angle and extension height of the cabin door handle. It can not only allow the outer handle to be inserted and removed so that it is flush with the cabin door skin when closed, but also realize the differential use of the inner and outer handles, and limit the movement of the cabin door mechanism. Attached Figure Description
[0019] Figure 1 This is an isometric drawing of an embodiment of the aircraft cabin door handle mechanism according to this application;
[0020] Figure 2 This is a front view of an aircraft cabin door handle mechanism according to one embodiment of this application;
[0021] Figure 3 This is a top view of an aircraft cabin door handle mechanism according to one embodiment of this application;
[0022] Figure 4 This is an exploded view of an aircraft cabin door handle mechanism according to one embodiment of this application;
[0023] Figure 5 This is a schematic diagram of a fixed shaft according to one embodiment of this application;
[0024] Figure 6 This is a schematic diagram of the outer handle shaft according to one embodiment of this application.
[0025] in:
[0026] 1-Inner handle; 2-Rock arm pivot; 3-Fixed shaft; 4-Handle box; 5-Tension spring; 6-Outer handle pivot; 7-Outer handle; 8-Limit pin; 9-Pin; 10-Spring pull plate; 11-Stop plate; 12-Limit bolt. Detailed Implementation
[0027] 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.
[0028] 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.
[0029] The following is in conjunction with the appendix Figures 1 to 6 This application will be described in further detail.
[0030] This application provides an aircraft cabin door inner and outer handle mechanism, including: inner handle 1, rocker arm pivot 2, fixed shaft 3, handle box 4, tension spring 5, outer handle pivot 6, outer handle 7, limit pin 8, pin shaft 9, spring pull plate 10, stop plate 11, and limit bolt 12.
[0031] Specifically, an inner handle 1 is fixedly installed at one end of the rocker arm shaft 2 via a connector. In this embodiment, the inner handle 1 and the rocker arm shaft 2 are connected by a through bolt. The rocker arm shaft 2 has a first accommodating space inside, and a first limiting hole is provided on the side wall of the rocker arm shaft 2. The fixed shaft 3 is nested in the first accommodating space. One end of the fixed shaft 3 is provided with a spring pull tab 10, and the other end is fixedly installed with a handle box 4 via a connector. The fixed shaft 3 has a second accommodating space inside, and an arc-shaped groove that mates with the limiting bolt 12 is provided on the side wall of the fixed shaft 3. The outer handle shaft 6 is nested in the second accommodating space. One end of the outer handle shaft 6 is connected to the outer handle 7 via a pin 9, and an L-shaped groove that mates with the limiting bolt 12 is provided on the side wall of the outer handle shaft 6.
[0032] One end of the tension spring 5 is connected to the spring pull plate 10, and the other end is connected to the pin 9. It always provides an inward pulling force to the outer handle 7 to prevent the outer handle 7 from accidentally coming off and causing the hatch to unlock.
[0033] The limiting bolt 12 is inserted into the first limiting hole, the arc-shaped groove, and the L-shaped groove, and works with the stop plate 11 to limit the rocker arm shaft 2, the fixed shaft 3, and the outer handle shaft 6. The opening and closing of the handle mechanism is controlled by the positional relationship between the limiting bolt 12 and the two grooves. The limiting bolt 12 rubs frequently with the fixed shaft 3 and the outer handle shaft 6 during the opening and closing process. The stop plate 11 and the bolt connection provide reliable stopping and prevent the threads from stripping.
[0034] In a preferred embodiment of this application, the rocker arm shaft 2 is provided with connecting ear pieces, which include connecting single ear pieces and connecting double ear pieces.
[0035] In a preferred embodiment of this application, a second limiting hole is provided on the handle box 4, and a limiting pin 8 is installed on the outer handle 7. The limiting pin 8 is used to cooperate with the second limiting hole on the handle box 4 to ensure that the handle mechanism is in place.
[0036] In the preferred embodiment of this application, the inner handle 1, rocker arm pivot 2, fixed shaft 3, handle box 4, outer handle pivot 6, outer handle 7, spring pull plate 10, and stop plate 11 are preferably all machined parts of 7050 aluminum alloy. The limiting pin 8, pin shaft 9, and limiting bolt 12 are all machined parts of 0Cr13Ni8Mo2Al stainless steel. The processing technology is mature, the processing reliability is high, and the dimensions and tolerances of the parts are easily guaranteed.
[0037] In the aircraft cabin door handle mechanism of this application, when the cabin door is closed (as illustrated by the outer handle 7), the limiting bolt 12 is located at the leftmost end of the L-shaped groove of the outer handle shaft 6 and the arc-shaped groove of the fixed shaft 3, restricting the outer handle 7 from being pulled outward. When it is necessary to open the cabin door, the outer handle 7 is pulled outward, and the vertical section of the L-shaped groove of the outer handle shaft 6, which is fixedly connected to the outer handle 7 by the pin 9, is pulled outward along the limiting bolt 12. Rotating the outer handle 7 to the left by 35° can drive the rocker arm shaft 2 to rotate through the limiting bolt 12. When closing the cabin door, rotating the outer handle 7 to the right by 35° can drive the rocker arm shaft 2 to rotate through the limiting bolt 12. Then, the outer handle 7 is pressed back into the handle box 4 until the limiting pin 8 coincides with the opening on the handle box 4, indicating that the handle mechanism is in place and the cabin door is fully closed.
[0038] The aircraft cabin door inner and outer handle mechanism of this application has an arc-shaped groove on the fixed shaft and an L-shaped groove at the outer handle pivot to cooperate with the movement of the cabin door handle mechanism, according to the opening angle and extension height of the cabin door handle. It can not only insert and remove the outer handle so that it is flush with the cabin door skin when closed, but also realize the differential use of the inner and outer handles, and limit the movement of the cabin door mechanism. The differential limit of the handle is reliable and stable, reducing the number of parts and assembly difficulty. The outer handle is equipped with limit pins 8 at 7, which conveniently and directly prevents the cabin door handle from being closed accidentally.
[0039] The aircraft door handle mechanism described in this application has been successfully applied to the design of an aircraft maintenance door. Assembly and use have demonstrated that its functions meet the requirements, and it is economical while also exhibiting excellent assembly and usability.
[0040] 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. A mechanism for handling both inside and outside an aircraft cabin door, characterized in that, include: A rocker arm pivot (2) is provided with an inner handle (1) fixedly installed at one end of the rocker arm pivot (2), and a first accommodating space is provided inside the rocker arm pivot (2). A first limiting hole is provided on the side wall of the rocker arm pivot (2). A fixed shaft (3) is nested in the first accommodating space. One end of the fixed shaft (3) is provided with a spring pull tab (10), and the other end is fixedly installed with a handle box (4). The interior of the fixed shaft (3) is provided with a second accommodating space, and an arc-shaped groove is provided on the side wall of the fixed shaft (3). An outer handle shaft (6) is nested in the second accommodating space. One end of the outer handle shaft (6) is connected to the outer handle (7) via a pin (9). An L-shaped groove is provided on the side wall of the outer handle shaft (6). A tension spring (5), one end of which is connected to the spring tab (10) and the other end of which is connected to the pin (9); The limiting bolt (12) is inserted into the first limiting hole, the arc groove and the L-shaped groove, and works with the stop piece (11) to limit the rocker arm shaft (2), the fixed shaft (3) and the outer handle shaft (6).
2. The aircraft cabin door inner and outer handle mechanism according to claim 1, characterized in that, The rocker arm shaft (2) is provided with connecting lugs.
3. The aircraft cabin door inner and outer handle mechanism according to claim 2, characterized in that, The connecting ear pieces include those for connecting a single ear and those for connecting both ears.
4. The aircraft cabin door inner and outer handle mechanism according to claim 1, characterized in that, The handle box (4) is provided with a second limiting hole, and the outer handle (7) is equipped with a limiting pin (8), which is used to cooperate with the second limiting hole on the handle box (4).
5. The aircraft cabin door inner and outer handle mechanism according to claim 4, characterized in that, The inner handle (1), the rocker arm pivot (2), the fixed shaft (3), the handle box (4), the outer handle pivot (6), the outer handle (7), the spring pull plate (10), and the stop plate (11) are all machined parts made of 7050 aluminum alloy.
6. The aircraft cabin door inner and outer handle mechanism according to claim 5, characterized in that, The limiting pin (8), the pin shaft (9), and the limiting bolt (12) are all machined parts made of 0Cr13Ni8Mo2Al stainless steel.