Timing double-hinged cabin door linkage mechanism and airplane cabin door thereof

Abstract

The application belongs to the field of aircraft doors, and particularly relates to a time sequence double-leaf door linkage mechanism and an aircraft door thereof. The time sequence double-leaf door linkage mechanism of the application is characterized in that when the door is opened, the piston rod of the actuator is extended, the rocker arm is driven to rotate through the connecting rod, and the first mounting shaft, the second mounting shaft and the differential rocker arm rotate synchronously. Due to the length difference between the two rocker arms of the differential rocker arm, the movement speed of the second adjusting pull rod connected with the long arm of the differential rocker arm is greater than that of the first adjusting pull rod connected with the short arm of the differential rocker arm, so that the angular speed of the second door around the rotating shaft is greater than the rotating speed of the first door, effectively avoiding the movement interference and impact problem of the two door overlap areas.

Description

Technical Field

[0001] This application belongs to the field of aircraft cabin doors, and specifically relates to a timing-sequential opening cabin door linkage mechanism and its aircraft cabin door. Background Technology

[0002] Supine doors are a common type of cabin door arrangement in modern aircraft. Their use and maintenance require the doors to be able to open and close both in the air and on the ground—that is, to retract and extend. The retraction and extension mechanism, as a crucial unit for enabling the doors to open and close, plays an extremely important role.

[0003] Generally, opposing hatches are controlled by two independent drive elements to extend and retract. While this mechanism is simple and mature, the drive elements require space above the hatch, which is inconvenient for the release and retraction of equipment (such as landing gear and gear) in aircraft with compact layouts. Currently, hydraulic actuators are the most widely used actuators. However, in high-temperature areas (such as the lower engine compartment), the internal seals of hydraulic actuators are at risk of failure, making direct installation of such actuators impossible. Specifically, for example... Figure 1 , 2 As shown, to improve low-observable performance, aircraft require adjoining areas for their doors. This results in the radius R1 of the far point of the adjoining door around the axis of rotation being larger than the radius R2 of the far point of the other door. When the doors move synchronously, interference or even impact damage will inevitably occur. While it's possible to force the doors to move in a specific sequence by separately acquiring position signals and using delay control and other electrical logic techniques on the two actuators, this method has relatively low reliability. If a component in any of these stages fails, the doors may malfunction, affecting their normal operation.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide a timing-based split-opening cabin door linkage mechanism and its aircraft cabin door to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] The first aspect of this application provides a timing-locked hatch linkage mechanism, comprising:

[0008] The mounting shaft includes a first mounting shaft and a second mounting shaft, which are respectively hinged to the body structure.

[0009] A differential rocker arm, the two ends of which are respectively connected to the first mounting shaft and the second mounting shaft by fasteners, and the differential rocker arm is provided with a differential rocker arm short arm and a differential rocker arm long arm.

[0010] A rocker arm, wherein the rocker arm is fixedly connected to the end of the first mounting shaft away from the differential rocker arm;

[0011] An actuator, which is fixedly mounted on the machine body structure;

[0012] A connecting rod, one end of which is hinged to the piston rod of the actuator, and the other end of which is hinged to the rocker arm;

[0013] The adjusting rod includes a first adjusting rod and a second adjusting rod, the first adjusting rod and the second adjusting rod having different lengths, one end of the first adjusting rod being hinged to the short arm of the differential rocker arm, and one end of the second adjusting rod being hinged to the long arm of the differential rocker arm;

[0014] The hatch includes a first hatch and a second hatch, which are respectively hinged to the hatch pivot of the fuselage structure. The first hatch is hinged to the end of the first adjusting rod away from the short arm of the differential rocker arm, and the second hatch is hinged to the end of the second adjusting rod away from the long arm of the differential rocker arm.

[0015] In a preferred embodiment of this application, the rotational speeds of the first hatch and the second hatch are adjusted by changing the lengths of the differential rocker arm short arm and the differential rocker arm long arm.

[0016] In a preferred embodiment of this application, both the first adjusting rod and the second adjusting rod include:

[0017] A rotating drum, with threaded holes at both ends;

[0018] A left-hand threaded earring, wherein the left-hand threaded earring is provided with a threaded section, and the left-hand threaded earring is connected to one end of the rotating cylinder in conjunction with a left-hand threaded nut;

[0019] A right-hand threaded lug, wherein the right-hand threaded lug is provided with a threaded section, and the right-hand threaded lug is connected to the other end of the rotating drum in conjunction with a right-hand threaded nut.

[0020] In a preferred embodiment of this application, a stop washer is provided between the left-hand threaded nut and the rotating cylinder, and between the right-hand threaded nut and the rotating cylinder.

[0021] In a preferred embodiment of this application, both the first hatch and the second hatch are wedge-shaped.

[0022] In a preferred embodiment of this application, the first hatch is hinged to the hatch pivot via a first pivot seat; the second hatch is hinged to the hatch pivot via a second pivot seat.

[0023] In a preferred embodiment of this application, the first hatch is hinged to the first adjusting rod via a first pull rod seat; the second hatch is hinged to the second adjusting rod via a second pull rod seat.

[0024] A second aspect of this application provides an aircraft door having a timing-based door linkage mechanism as described above.

[0025] The invention has at least the following beneficial technical effects:

[0026] The timing-based hatch linkage mechanism of this application, on the one hand, allows the actuator to be arranged in an area far away from the upper part of the hatch, solving the adverse problems of limited movement space and high cabin temperature; on the other hand, it realizes the timing control of the hatch opening through the mechanism, solving the problem of low reliability of electrical control. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overlapping area of ​​the split hatches;

[0028] Figure 2 This is a schematic diagram illustrating the interference of the opening hatch movement;

[0029] Figure 3 This is a schematic diagram of a timing-based split-opening hatch linkage mechanism according to one embodiment of this application;

[0030] Figure 4 This is a schematic diagram of the movement of the split hatch according to one embodiment of this application;

[0031] Figure 5 This is a schematic diagram of a differential rocker arm according to one embodiment of this application;

[0032] Figure 6 This is a schematic diagram of an adjusting rod according to one embodiment of this application.

[0033] in:

[0034] 1-Actuator; 2-Connecting rod; 3-Rocker arm; 4-First mounting shaft; 5-Differential rocker arm; 6-Second mounting shaft; 7-First adjusting rod; 8-Second adjusting rod; 9-First hatch; 10-Second hatch; 11-Left-hand threaded lug; 12-Right-hand threaded lug; 13-Left-hand threaded nut; 14-Right-hand threaded nut; 15-Rotating drum. Detailed Implementation

[0035] 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.

[0036] 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.

[0037] The following is in conjunction with the appendix Figures 3 to 6 This application will be described in further detail.

[0038] The first aspect of this application provides a timing-dependent hatch linkage mechanism, including: an actuator 1, a connecting rod 2, a rocker arm 3, a mounting shaft, a differential rocker arm 5, an adjusting rod, and a hatch.

[0039] like Figure 3 As shown, the mounting shaft includes a first mounting shaft 4 and a second mounting shaft 6, which are hinged to the machine body structure. The two ends of the differential rocker arm 5 are connected to the first mounting shaft 4 and the second mounting shaft 6 respectively via fasteners. The differential rocker arm 5 is provided with a differential rocker arm short arm and a differential rocker arm long arm. In this embodiment, the ends of both the first mounting shaft 4 and the second mounting shaft 6 are provided with connecting lugs, and the two ends of the differential rocker arm 5 are provided with corresponding lugs. The differential rocker arm 5 is fixedly connected to the first mounting shaft 4 and the second mounting shaft 6 respectively by bolts. The differential rocker arm short arm and the differential rocker arm long arm are located at the two ends of the differential rocker arm 5 respectively.

[0040] The rocker arm 3 is fixedly connected to the end of the first mounting shaft 4 away from the differential rocker arm 5. After the connection, the rocker arm 3, the first mounting shaft 4, the second mounting shaft 6, and the differential rocker arm 5 form a whole.

[0041] Actuator 1 is fixedly mounted on the machine body structure; one end of connecting rod 2 is hinged to the piston rod of actuator 1, and the other end is hinged to rocker arm 3.

[0042] The adjusting rod includes a first adjusting rod 7 and a second adjusting rod 8. The first adjusting rod 7 and the second adjusting rod 8 have different lengths. One end of the first adjusting rod 7 is hinged to the short arm of the differential rocker arm, and one end of the second adjusting rod 8 is hinged to the long arm of the differential rocker arm.

[0043] The hatch includes a first hatch 9 and a second hatch 10, which are respectively hinged to hatch pivots on the fuselage structure. The first hatch 9 is hinged to the end of the first adjusting rod 7 away from the short arm of the differential rocker arm, and the second hatch 10 is hinged to the end of the second adjusting rod 8 away from the long arm of the differential rocker arm. In a preferred embodiment of this application, both the first hatch 9 and the second hatch 10 are wedge-shaped. The first hatch 9 is hinged to the hatch pivot via a first pivot seat; the second hatch 10 is hinged to the hatch pivot via a second pivot seat. The first hatch 9 is hinged to the first adjusting rod 7 via a first rod seat; the second hatch 10 is hinged to the second adjusting rod 8 via a second rod seat.

[0044] The timing-sequenced hatch linkage mechanism of this application, such as... Figure 4 As shown, when the hatch is opened, the piston rod of actuator 1 extends and drives the rocker arm 3 to rotate via connecting rod 2. At this time, the first mounting shaft 4, the second mounting shaft 6, and the differential rocker arm 5 rotate synchronously. Due to the length difference between the two rocker arms of the differential rocker arm 5, the movement speed of the second adjusting rod 8 connected to the long arm of the differential rocker arm is greater than the movement speed of the first adjusting rod 7 connected to the short arm of the differential rocker arm. This results in the angular velocity of the second hatch 10 around the axis of rotation being greater than the rotational speed of the first hatch 9, effectively avoiding motion interference and impact problems in the overlapping area of ​​the two hatches.

[0045] In the preferred embodiment of this application, such as Figure 5 As shown, the rotational speeds of the first hatch 9 and the second hatch 10 are adjusted by changing the lengths of the short arm a and the long arm b of the differential rocker arm 5. This achieves a coordinated relationship between the opening angles of the two hatches. When the lengths a and b of the two rocker arms 5 are equal, the first hatch 9 and the second hatch 10 move synchronously.

[0046] In the preferred embodiment of this application, such as Figure 6As shown, both the first adjusting rod 7 and the second adjusting rod 8 include: a rotating cylinder 15, a left-hand threaded lip 11, and a right-hand threaded lip 12. The rotating cylinder 15 has threaded holes at both ends. The left-hand threaded lip 11 has a threaded section and is connected to one end of the rotating cylinder 15 in conjunction with a left-hand threaded nut 13. The right-hand threaded lip 12 has a threaded section and is connected to the other end of the rotating cylinder 15 in conjunction with a right-hand threaded nut 14. In this embodiment, preferably, a stop washer 16 is provided between the left-hand threaded nut 13 and the rotating cylinder 15, and between the right-hand threaded nut 14 and the rotating cylinder 15.

[0047] When the first adjusting rod 7 and the second adjusting rod 8 are in the installed state, that is, when their two ends are respectively hinged to the differential rocker arm 5 and the first hatch 9 and the second hatch 10, after loosening the left-hand threaded nut 13, the right-hand threaded nut 14 and the stop washer 16 respectively, the left-hand threaded lug 11 and the right-hand threaded lug 12 can be screwed in (or screwed out) by rotating the rotating cylinder 15, thereby changing the total length of the first adjusting rod 7 and the second adjusting rod 8, and thus adjusting the closing state of the first hatch 9 and the second hatch 10, so as to realize the step control between the hatch and the surrounding structure, and between the first hatch 9 and the second hatch 10.

[0048] The second aspect of this application provides an aircraft door having the aforementioned timing-locked door linkage mechanism.

[0049] Compared with conventional double-opening door movement mechanisms, the timing-based double-opening door linkage mechanism and its aircraft door of this application have the following advantages:

[0050] a) A single drive actuator simultaneously controls the opening and closing of the two opposing hatches, reducing the need for piping layout;

[0051] b) The actuator arrangement is more flexible, allowing for actuators to be positioned away from the hatch via a mechanism. This eliminates the limitations imposed by cabin space and conditions, resulting in a wider design scope.

[0052] c) By using a motion mechanism with differential characteristics, the timing motion control of the hatch opening is achieved, avoiding interference and impact from synchronous motion;

[0053] d) The mechanism timing control of the single-drive actuator replaces the electrical logic timing control of the dual-actuator actuator, thus improving reliability.

[0054] 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 time-sequential hatch linkage mechanism, characterized in that, include: The mounting shaft includes a first mounting shaft (4) and a second mounting shaft (6), which are respectively hinged to the body structure; Differential rocker arm (5), the two ends of the differential rocker arm (5) are respectively connected to the first mounting shaft (4) and the second mounting shaft (6) by fasteners, and the differential rocker arm (5) is provided with a differential rocker arm short arm and a differential rocker arm long arm; A rocker arm (3) is fixedly connected to one end of the first mounting shaft (4) away from the differential rocker arm (5); Actuator (1), wherein the actuator (1) is fixedly installed on the machine body structure; Linkage (2), one end of which is hinged to the piston rod of the actuator (1), and the other end is hinged to the rocker arm (3); The adjusting rod includes a first adjusting rod (7) and a second adjusting rod (8). The first adjusting rod (7) and the second adjusting rod (8) have different lengths. One end of the first adjusting rod (7) is hinged to the short arm of the differential rocker arm, and one end of the second adjusting rod (8) is hinged to the long arm of the differential rocker arm. The hatch includes a first hatch (9) and a second hatch (10). The first hatch (9) and the second hatch (10) are respectively hinged to the hatch pivot of the fuselage structure. The first hatch (9) is hinged to the end of the first adjusting rod (7) away from the short arm of the differential rocker arm, and the second hatch (10) is hinged to the end of the second adjusting rod (8) away from the long arm of the differential rocker arm.

2. The timing-sequential hatch linkage mechanism according to claim 1, characterized in that, The rotational speeds of the first hatch (9) and the second hatch (10) are adjusted by changing the lengths of the differential rocker arm short arm and the differential rocker arm long arm.

3. The timing-sequential hatch linkage mechanism according to claim 2, characterized in that, Both the first adjusting rod (7) and the second adjusting rod (8) include: Rotary drum (15), with threaded holes at both ends; A left-hand threaded earring (11) is provided with a threaded section. The left-hand threaded earring (11) is connected to one end of the rotating drum (15) in conjunction with a left-hand threaded nut (13). A right-hand threaded earring (12) is provided with a threaded section. The right-hand threaded earring (12) is connected to the other end of the rotating drum (15) in conjunction with a right-hand threaded nut (14).

4. The timing-sequential hatch linkage mechanism according to claim 3, characterized in that, A stop washer (16) is provided between the left-hand threaded nut (13) and the rotating drum (15), and between the right-hand threaded nut (14) and the rotating drum (15).

5. The timing-sequential hatch linkage mechanism according to claim 1, characterized in that, Both the first hatch (9) and the second hatch (10) are wedge-shaped.

6. The timing-sequential hatch linkage mechanism according to claim 5, characterized in that, The first hatch (9) is hinged to the hatch pivot via a first pivot seat; the second hatch (10) is hinged to the hatch pivot via a second pivot seat.

7. The timing-sequential hatch linkage mechanism according to claim 6, characterized in that, The first hatch (9) is hinged to the first adjusting rod (7) via the first pull rod seat; the second hatch (10) is hinged to the second adjusting rod (8) via the second pull rod seat.

8. An aircraft cabin door, characterized in that, The aircraft cabin door has a time-sequential opening cabin door linkage mechanism as described in any one of claims 1 to 7.

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