Handle mechanism of airplane cabin door

Abstract

An aircraft hatch handle mechanism is provided that can avoid accidental operation of an inner handle. The aircraft cabin door handle mechanism comprises: an inner handle assembly having an inner handle sleeve and an inner handle; an outer handle assembly having an outer handle sleeve and an outer handle, the outer handle sleeve and the inner handle sleeve are coaxially arranged, and a part of the outer handle sleeve is located on the inner peripheral side of the inner handle sleeve; the inner handle lock is provided with a clamping part; the inner handle sleeve is provided with a first groove, the outer handle sleeve can move in the axial direction relative to the inner handle sleeve and is provided with a second groove, the outer handle assembly comprises a locking mechanism, and when the outer handle sleeve moves to the specified position in the axial direction relative to the inner handle sleeve, the outer handle can be locked through the locking mechanism. By operating the operating portion, the engaging portion can be brought into a first state in which the engaging portion engages with the first groove and the second groove which overlap in the radial direction and a second state in which the engaging portion is disengaged toward the inner circumferential side with respect to the first groove and the second groove, and in the second state, the inner handle sleeve can rotate in the circumferential direction with respect to the outer handle sleeve.

Description

TECHNICAL FIELD

[0001] The present application relates to an aircraft cabin door handle mechanism. BACKGROUND

[0002] The equipment cabin door of an aircraft or the like needs to be opened and closed by a handle mechanism. The current handle mechanisms adopt the following two schemes.

[0003] In the first scheme, the outer handle and the inner handle are completely linked, that is, when the outer handle is operated, the inner handle moves synchronously with the outer handle, and when the inner handle is operated, the outer handle moves synchronously with the inner handle.

[0004] In the second scheme, the outer handle and the inner handle are semi-linked, that is, when the outer handle is operated, the inner handle moves synchronously with the outer handle, and when the inner handle is operated, the outer handle remains stationary.

[0005] In both of the above aircraft cabin door handle mechanisms, there is a concern that the cabin door is opened by the accidental operation of the inner handle by the cabin personnel, which affects the flight safety. SUMMARY

[0006] The present application is completed in view of the above problems, and aims to provide an aircraft cabin door handle mechanism capable of avoiding the opening of the cabin door by the accidental operation of the inner handle, which affects the flight safety.

[0007] To achieve the above object, the present application provides an aircraft cabin door handle mechanism, comprising: an inner handle assembly having an inner handle sleeve and an inner handle, the inner handle being installed at an end of the inner handle sleeve on one axial side; an outer handle assembly having an outer handle sleeve and an outer handle, the outer handle sleeve being coaxially arranged with the inner handle sleeve and being located at a part of the inner periphery of the inner handle sleeve, the outer handle being arranged at an end of the outer handle sleeve on the other axial side; an inner handle lock having an engaging portion; and an operation portion, the inner handle sleeve having a first groove recessed from the inner peripheral surface of the inner handle sleeve to the outer peripheral side, the outer handle sleeve being movable in the axial direction with respect to the inner handle sleeve and having a second groove penetrating the outer handle sleeve in the radial direction, the outer handle assembly including a locking mechanism, the outer handle being lockable by the locking mechanism when the outer handle sleeve is moved to a prescribed position in the axial direction with respect to the inner handle sleeve, the engaging portion being switchable between a first state of being engaged in the first groove and the second groove which overlap in the radial direction and a second state of being withdrawn to the inner peripheral side with respect to the first groove and the second groove by operating the operation portion, and the inner handle sleeve being rotatable in the circumferential direction with respect to the outer handle sleeve in the second state.

[0008] The aircraft cabin door handle mechanism according to the present application can prevent the cabin door from being opened by the cabin personnel due to the misoperation or accidental contact of the inner handle, thereby ensuring flight safety, and can realize the synchronous movement of the inner handle with the outer handle when the outer handle is operated, and the inaction of the outer handle when the inner handle is operated.

[0009] In addition, in the aircraft cabin door handle mechanism according to the present application, the inner handle lock can further include a first pin supported by the inner handle sleeve, the inner handle lock can have a rod portion extending into the inner handle sleeve and having a first through hole at the middle of the axial direction, an operated portion provided at the axial one end of the rod portion for contacting the operation portion, and the engaging portion protruding outward from the axial other end of the rod portion, and the first pin can support the rod portion to be rotatable by passing through the first through hole. According to the above structure, the cabin door can be prevented from being opened due to the accidental operation of the inner handle with a simple structure.

[0010] In addition, in the aircraft cabin door handle mechanism according to the present application, the rod portion can have a first rod portion on the axial one side of the first through hole and a second rod portion on the axial other side of the first through hole, the operated portion can be provided at the axial one end of the first rod portion, and the rod portion can be configured such that, when the engaging portion is in the first state, the first rod portion is inclined toward the first slot along the axial direction and the second rod portion is inclined toward the first slot as it moves toward the axial other side. According to the above structure, the rod portion can be easily rotated by the operation portion.

[0011] In addition, in the aircraft cabin door handle mechanism according to the present application, the inner handle sleeve can include a ring-shaped main body portion and a pair of support portions provided at the axial one end of the main body portion and protruding toward the axial one side, the aircraft cabin door handle mechanism can further include a second pin supported by the pair of support portions, the operation portion can have a second through hole, the second pin can support the operation portion to be rotatable by passing through the second through hole, the inner handle can have a first opening portion from which a first pressing surface of the axial one side of the operation portion, i.e., a first pressing surface, is exposed, and the operation portion can be rotated by pressing the first pressing surface to make the engaging portion into the first state and the second state. According to the above structure, the cabin door can be prevented from being opened due to the accidental operation of the inner handle with a simple structure.

[0012] Furthermore, in the aircraft door handle mechanism of the present invention, the operating part may have a pressing part at the other end in the axial direction. By rotating the operating part, the pressing part contacts and presses the operated part, thereby causing the lever to rotate. When viewed axially, the connection portion between the operated part and the lever is located on the opposite side of the first groove relative to the center of the operated part, and the contact portion between the pressing part and the operated part is located on the side of the first groove relative to the connection portion between the operated part and the lever. According to the above structure, the lever can be easily rotated by the operating part.

[0013] Furthermore, in the aircraft door handle mechanism of the present invention, the inner handle may be mounted to the inner handle sleeve via the second pin. This allows the operating part to be supported using the second pin for mounting the inner handle, eliminating the need for a separate component to support the operating part and simplifying the structure of the aircraft door handle mechanism.

[0014] Furthermore, in the aircraft door handle mechanism of the present invention, the operated part may also be in the shape of a circular plate. This facilitates manufacturing and allows the operated part to have the largest possible area without interfering with other components, thus facilitating contact with the operating part.

[0015] Furthermore, in the aircraft door handle mechanism of the present invention, the axial length of the second groove may be greater than the axial length of the engaging portion. When the engaging portion is in the first state, when the outer handle sleeve moves axially relative to the inner handle sleeve, the axial position of the engaging portion in the second groove changes. When the outer handle sleeve moves relative to the inner handle sleeve to the position closest to the other side of the axial direction, the engaging portion is located at one end of the axial direction in the second groove. Thus, without the need for additional limiting members, the axial movement range of the outer handle sleeve can be limited by the engaging portion.

[0016] Furthermore, in the aircraft door handle mechanism of the present invention, the first groove may extend axially to the other axial end of the inner handle sleeve. According to the above structure, the first groove can be easily formed.

[0017] Furthermore, the aircraft door handle mechanism of the present invention may also include an elastic force-applying member housed in the inner handle sleeve. When the outer handle is locked by the locking mechanism, the elastic force-applying member is supported on the inner circumferential surface of the inner handle sleeve and applies force to the outer handle sleeve axially to the other side. Thus, when the locking mechanism is unlocked, the outer handle pops out under the action of the elastic force-applying member, facilitating its use. Attached Figure Description

[0018] Figure 1 This is a schematic cross-sectional view illustrating an embodiment of an aircraft cabin door handle mechanism according to the present invention.

[0019] Figure 2 This is an exploded perspective view schematically illustrating an embodiment of the aircraft cabin door handle mechanism of the present invention.

[0020] Figure 3 yes Figure 2 A magnified view of a portion of the image.

[0021] Figure 4 yes Figure 2 A magnified view of a portion of the image.

[0022] Figure 5 yes Figure 2 A magnified view of a portion of the image.

[0023] Figure 6 This is a schematic side view of the inner handle sleeve of an aircraft door handle mechanism according to an embodiment of the present invention.

[0024] Figure 7 yes Figure 6 AA sectional view.

[0025] Figure 8 This is a perspective view schematically illustrating some components of an aircraft cabin door handle mechanism according to an embodiment of the present invention.

[0026] Figure 9 This is a cross-sectional view of an aircraft door handle mechanism showing the engagement of the engaging part with the radially overlapping first and second grooves.

[0027] Figure 10 This is a cross-sectional view of an aircraft door handle mechanism showing the engagement part disengaged from the first and second grooves towards the inner periphery.

[0028] Symbol Explanation

[0029] 1 First pin; 2 Inner handle sleeve pin (second pin); 3 Outer handle locking hook pin; 4 Pin component; 5 Pin component; 10 Inner handle assembly; 11 Inner handle sleeve; 12 Inner handle; 20 Outer handle assembly; 21 Outer handle sleeve; 22 Outer handle; 30 Inner handle lock; 31 Rod part; 32 Operated part; 33 First through hole; 34 Engaging part; 40 Operating part; 41 Second through hole; 42 Pressing part; 50 Locking mechanism; 51 Outer handle lock button; 52 Outer handle lock torsion spring; 60 Outer handle box; 70 Elastic force application component; 80 Rocker arm component; 81 Cylinder part; 82 Rocker arm; 90 Handle support; 100 Aircraft cabin door handle mechanism; 111 Main body; 112 Support part; 113 Support part through hole; 122 Inner handle through hole; 123 First opening; 221 Outer handle opening; 311 First rod section; 312 Second rod section; 511 Hook section; 1111 Large diameter section; 1112 Small diameter section; 1113 Ring-shaped section; S1 First groove; S2 Second groove. Detailed Implementation

[0030] Hereinafter, with reference to the accompanying drawings, the technical solutions of embodiments and modifications of the present invention will be described. Furthermore, the scope of the present invention is not limited to the following embodiments and modifications, and can be arbitrarily modified within the scope of the technical concept of the present invention. In addition, in the following drawings, for ease of understanding of each structure, the actual construction may sometimes differ from the scale, quantity, etc., in each construction.

[0031] In the following description, the direction parallel to the central axis of the inner handle sleeve is referred to as the "axial direction". The direction around the central axis of the inner handle sleeve is referred to as the "circumferential direction". The direction perpendicular to the central axis of the inner handle sleeve is referred to as the "radial direction".

[0032] This invention relates to an aircraft door handle mechanism with an inner handle lock and a clutch device. The aircraft door handle mechanism has an inner handle lock to prevent cabin personnel from accidentally opening the door due to misoperation or accidental contact with the inner handle, thus ensuring flight safety; and it has a clutch device that allows the inner handle to move synchronously with the outer handle when the outer handle is operated; while the outer handle remains stationary when the inner handle is operated.

[0033] <First Implementation>

[0034] Figure 1 This is a schematic cross-sectional view illustrating the aircraft door handle mechanism 100 according to the first embodiment of the present invention. Figure 2 This is an exploded perspective view schematically showing the aircraft cabin door handle mechanism 100. Figures 3-5 yes Figure 2 A magnified view of a portion of the image. Figure 6This is a schematic side view of the inner handle sleeve 11 of the aircraft door handle mechanism 100. Figure 7 yes Figure 6 AA sectional view. Figure 8 This is a perspective view schematically showing some components of the aircraft cabin door handle mechanism 100.

[0035] This embodiment provides an aircraft door handle mechanism 100, for example, for an aircraft door, the door being opened and closed via the aircraft door handle mechanism 100. The aircraft door handle mechanism 100 includes an inner handle assembly 10, an outer handle assembly 20, an inner handle lock 30, and an operating part 40.

[0036] The inner handle assembly 10 includes an inner handle sleeve 11 and an inner handle 12. The inner handle 12 is mounted on one axial side of the inner handle sleeve 11. Figure 1 The end of the middle (upper side).

[0037] The inner handle sleeve 11 includes an annular main body 111 and a pair of support portions 112 disposed on one axial end of the main body 111 and protruding to one axial side. The inner handle sleeve 11 may be a single component.

[0038] The aircraft door handle mechanism 100 also includes an inner handle sleeve pin (equivalent to the "second pin" of the present invention) 2, which is supported on a pair of support portions 112. The inner handle 12 can be mounted on the inner handle sleeve 11 via the inner handle sleeve pin 2.

[0039] In this embodiment, such as Figure 7 As shown, the main body 111 includes: a cylindrical large-diameter portion 1111; a cylindrical small-diameter portion 1112 located axially closer to the large-diameter portion 1111; and an annular portion 1113 located axially closer to the small-diameter portion 1112. The inner diameter of the large-diameter portion 1111 can be larger than the inner diameter of the small-diameter portion 1112. The outer diameter of the large-diameter portion 1111 can be larger than the outer diameter of the small-diameter portion 1112. The inner diameter of the annular portion 1113 can be approximately the same as the inner diameter of the small-diameter portion 1112. The outer diameter of the annular portion 1113 can be larger than the outer diameter of the small-diameter portion 1112.

[0040] A pair of support portions 112 are disposed on one axial end of the annular portion 1113 and protrude to one axial side. The pair of support portions 112 are radially opposite each other. The radial distance between the pair of support portions 112 may be larger than the inner diameter of the small-diameter portion 1112.

[0041] Each of the pair of support parts 112 is provided with a radially penetrating support part through hole 113. The two ends of the inner handle sleeve pin 2 are inserted into the support part through holes 113 of the pair of support parts 112.

[0042] The inner handle 12 extends generally in a direction intersecting the axial direction, for example, having a direction towards the other side of the axial direction at one end in the length direction.Figure 1 The inner handle support portion 121 extends from the middle and lower side, and the inner handle support portion is provided with an inner handle through hole 122 for the inner handle sleeve pin 2 to pass through. Figure 1 In the example, two inner handle through holes 122 are provided across the operating part 40.

[0043] The outer handle assembly 20 includes an outer handle sleeve 21 and an outer handle 22. The outer handle sleeve 21 is coaxially disposed with the inner handle sleeve 11, and a portion (more specifically, the portion on the axial side) is located on the inner circumference of the inner handle sleeve 11. The outer handle sleeve 21 is axially movable relative to the inner handle sleeve 11. The outer handle sleeve 21 is, for example, cylindrical. The outer handle 22 is disposed at the end of the outer handle sleeve 21 on the opposite axial side. The outer handle 22 extends integrally in a direction intersecting the axial direction.

[0044] The outer handle assembly 20 also includes a locking mechanism 50. When the outer handle sleeve 21 moves relative to the inner handle sleeve 11 to a predetermined axial position (in this embodiment, the position closest to the axial side), the locking mechanism 50 can lock the outer handle 22.

[0045] The outer handle assembly 20 also includes an outer handle box 60. The outer handle box 60 is installed on the hatch and is used to store the outer handle 22. The outer handle box 60 is fixedly provided with an outer handle locking hook 3.

[0046] In this embodiment, the locking mechanism 50 includes an outer handle lock hook pin 3, an outer handle lock button 51, and an outer handle lock torsion spring 52. However, it is not limited to this, and the locking mechanism 50 may also adopt other known structures capable of locking the outer handle.

[0047] The outer handle lock button 51 is pivotally connected to the outer handle via a pin member 4 and has a hook portion 511 on one axial side end.

[0048] The outer handle 22 has an outer handle opening 221. The outer handle lock button 51 is mounted on the outer handle 22 such that its axially opposite surface, i.e., the second pressing surface, protrudes from the outer handle opening 221. The outer handle lock button 51 can be configured such that when the outer handle sleeve 21 moves relative to the inner handle sleeve 11 to a predetermined axial position, the hook part 511 contacts the outer handle lock pin 3, and under the action of the outer handle lock pin 3, overcomes the force of the outer handle lock torsion spring 52, causing the outer handle lock button 51 to rotate, thereby causing the hook part 511 to hook onto the outer handle lock pin 3.

[0049] Furthermore, pressing the second pressing surface can change the hook portion 511 from a locked state (hooked to the outer handle lock pin 3) to an unlocked state (not hooked to the outer handle lock pin 3). The outer handle lock torsion spring 52 is sleeved on the pin member 4, and one end abuts against the pin member 5 fixed to the outer handle 22. In the locked state, the outer handle lock torsion spring 52 applies force to the outer handle lock button 51 in the direction that keeps the hook portion 511 hooked to the outer handle lock pin 3, ensuring that the outer handle lock button is in the closed position.

[0050] In addition, the aircraft door handle mechanism 100 also includes a rocker arm 82 for driving a lower-level mechanism (such as a door rotation mechanism or linkage mechanism, thereby opening the door). In this embodiment, the aircraft door handle mechanism 100 includes a rocker arm member 80. The rocker arm member 80 has a cylindrical portion 81 and a rocker arm 82. The cylindrical portion 81 is coaxially disposed with the inner handle sleeve 11 and splines it engages with the inner handle sleeve 11 on its outer peripheral side. The rocker arm 82 is disposed on the outer peripheral surface of the cylindrical portion 81. For example, an external spline is provided on the outer peripheral surface of the inner handle sleeve 11 (large diameter portion 1111), and an internal spline is provided on the inner peripheral surface of the cylindrical portion 81 to engage with the external spline. Thus, both the inner handle sleeve 11 and the rocker arm member 80 are splines, and the splines of the inner handle sleeve 11 and the rocker arm member 80 can mesh with each other, so that when the inner handle sleeve 11 is rotated, the rocker arm member 80 moves synchronously with the inner handle sleeve 11.

[0051] In addition, the rocker arm assembly 80 can be rotatably supported on the hatch via the handle support 90 (the handle support 90 is used to support the rocker arm assembly 80 and the inner handle assembly 10).

[0052] In the aircraft door handle mechanism of the present invention, the inner handle locking function and the clutch function are realized by the inner handle lock 30, the operating part 40 and the first groove S1 and the second groove S2 described below.

[0053] like Figure 7 As shown, the inner handle sleeve 11 has a first groove S1 recessed from the inner circumference of the inner handle sleeve 11 to the outer circumference. In this embodiment, the first groove S1 is provided in the large diameter portion 1111. The first groove S1 can extend axially to the other axial end of the inner handle sleeve 11. Furthermore, the first groove S1 may not penetrate the inner handle sleeve 11 radially, or it may penetrate the inner handle sleeve 11 radially.

[0054] like Figure 5 and Figure 8 As shown, the outer handle sleeve 21 has a second groove S2 that extends radially through the outer handle sleeve 21.

[0055] like Figure 4As shown, the inner handle lock 30 has a lever portion 31, an actuated portion 32, and an engaging portion 34. The lever portion 31 extends into the interior of the inner handle sleeve 11 and has a first through hole 33 midway along its axial direction. The actuated portion 32 is disposed at one axial end of the lever portion 31 for contacting the operating portion 40. The engaging portion 34 protrudes outward from the other axial end of the lever portion 31.

[0056] The aircraft door handle mechanism 100 also includes a first pin 1, which is supported on the inner handle sleeve 11 (small diameter portion 1112). The first pin 1 passes through the first through hole 33 and supports the rod portion 31 so that it can rotate. In this embodiment, the first pin 1 and the second pin 2 form an angle when viewed axially. However, this is not a limitation; the first pin 1 and the second pin 2 can form any angle when viewed axially, or they can be parallel to each other.

[0057] The rod portion 31 has a first rod portion 311 on the axial side of the first through hole 33 and a second rod portion 312 on the axial side of the first through hole 33. The operable portion 32 is disposed on the axial side end of the first rod portion 311. The shape of the operable portion 32 is not particularly limited. Preferably, the operable portion 32 is in the shape of a circular plate, which facilitates processing and allows the operable portion 32 to have the largest possible area without interfering with other components, thus facilitating contact with the operating portion 40.

[0058] The operating unit 40 can be used to make the engaging part 34 engage with the radially overlapping first groove S1 and second groove S2 in a first state and disengage it from the first groove S1 and second groove S2 in a second state. In the second state, the inner handle sleeve 11 can rotate circumferentially relative to the outer handle sleeve 21.

[0059] The operating part 40 is disposed, for example, inside the inner handle support part 121. The shape of the operating part 40 is not particularly limited. For example, the operating part 40 is generally cylindrical. The operating part 40 is provided with a second through hole 41. The inner handle sleeve pin 2 passes through the second through hole 41 to support the operating part 40 so that it can rotate.

[0060] like Figure 9 As shown, the inner handle 12 has a first opening 123. The axial side surface of the operating part 40, namely the first pressing surface, protrudes from the first opening 123. The operating part 40 can be rotated by pressing the first pressing surface, so that the engaging part 34 is in a first state and a second state.

[0061] like Figure 3As shown, the operating part 40 has a pressing part 42 at the other end in the axial direction. The pressing part 42 protrudes axially to the other end of the operating part 40, for example, along the edge. In the circumferential direction around the central axis of the operating part 40, the pressing part 42 is located at a position offset from the second through hole 41. When viewed along the central axis of the operating part 40, the pressing part 42 is, for example, arc-shaped. By rotating the operating part 40, the pressing part 42 contacts and presses the operated part 32, thereby causing the rod part 31 to rotate. Preferably, when viewed in the axial direction, the connection portion between the operated part 32 and the rod part 31 is located on the opposite side of the first groove S1 relative to the center of the operated part 32, and the contact portion between the pressing part 42 and the operated part 32 is located on the side of the first groove S1 relative to the connection portion between the operated part 32 and the rod part 31. Thus, the rod part 31 can be easily rotated by the operating part 40 (and the engaging part 34 can be easily disengaged from the first groove S1 and the second groove S2 towards the inner circumference).

[0062] Preferably, the lever 31 is configured such that, when the engaging part 34 is in the first state, the first lever 311 is along the axial direction, and the second lever 312 is inclined toward the first groove S1 as it moves toward the other side of the axial direction. As a result, the lever 31 can be easily rotated by the operating part 40. Moreover, compared to the case where the second lever 312 is formed by extending to the other side of the axial direction and then bending toward the first groove S1, it is less likely to interfere with the outer handle sleeve 21. The lever 31 can be rotated at a larger angle, which facilitates the operation of the inner handle lock 30.

[0063] In this embodiment, the second groove S2 extends axially, and its axial length is greater than that of the engaging portion 34. When the engaging portion 34 is in the first state, the axial position of the engaging portion 34 in the second groove S2 changes as the outer handle sleeve 21 moves axially relative to the inner handle sleeve 11. When the outer handle sleeve 21 moves relative to the inner handle sleeve 11 to the position closest to the other side of the axial direction, the engaging portion 34 is preferably located at one end of the axial direction in the second groove S2. Thus, without the need for additional limiting members, the axial movement range of the outer handle sleeve 21 can be limited by the engaging portion 34.

[0064] Furthermore, the aircraft door handle mechanism 100 also includes an elastic force-applying member 70. The elastic force-applying member 70 is housed in the inner handle sleeve 11. When the outer handle is locked by the locking mechanism 50, the elastic force-applying member 70 (its axial end) is supported on the inner circumferential surface of the inner handle sleeve 11 and applies force to the outer handle sleeve 21 on the other axial side. Thus, when the outer handle lock button 51 is pressed to unlock, the outer handle 22 pops out of the outer handle box 60 under the action of the elastic force-applying member 70, facilitating the use of the outer handle 22 (at this time, the engaging portion 34 is still within the first groove S1 and the second groove S2). The elastic force-applying member can be, for example, a spring or other known elastic element. In this embodiment, the axial end of the spring, which is the elastic force-applying member 70, is supported on a step between the large-diameter portion 1111 and the small-diameter portion 1112. The elastic force-applying member 70 is located axially between this step and the outer handle sleeve 21.

[0065] The operation of the aircraft door handle mechanism 100 is explained below. Figure 9 This is a cross-sectional view of an aircraft door handle mechanism 100 showing the engagement of the engaging part 34 with the radially overlapping first groove S1 and second groove S2. Figure 10 This is a cross-sectional view of the aircraft door handle mechanism 100 showing the state in which the engaging part 34 is disengaged from the first groove S1 and the second groove S2 toward the inner periphery.

[0066] When the engaging part 34 of the inner handle lock 30 is in the first state, the outer handle 22 is rotated. The engaging part 34 is in the second groove S2. Therefore, the inner handle lock 30 rotates with the outer handle 22, and the engaging part 34 is in the first groove S1. Therefore, the inner handle sleeve 11 rotates with the inner handle lock 30, and the rocker arm component 80 can rotate with the inner handle sleeve 11 to realize the function of opening the hatch with the outer handle.

[0067] When the engaging part 34 of the inner handle lock 30 is in the first state, the operating part 40 is operated (pressed). At this time, the engaging part 34 disengages from the second slot S2 and the first slot S1, realizing the inner handle unlocking function. At this time, rotating the inner handle 12 causes the inner handle sleeve 11 to rotate with the inner handle 12, and also causes the rocker arm component 80 to rotate with the inner handle 12, realizing the inner handle opening the hatch function.

[0068] When the operating part 40 is operated (pressed), the engaging part 34 of the inner handle lock 30 disengages from the second groove S2 and the first groove S1, realizing the disengagement function of the inner and outer handles, that is, when the inner handle 12 is rotated, the outer handle 22 remains stationary.

[0069] When the operation unit 40 is not pressed, the engaging part 34 of the inner handle lock 30 is in the second groove S2 and the first groove S1. Since the outer handle 22 is in the outer handle box 60 (locked), the inner handle 12 cannot be rotated at this time, thus realizing the inner handle lock function. That is, the hatch cannot be opened without unlocking the inner handle lock 30.

[0070] The specific embodiments of the present invention have been described above in conjunction with the accompanying drawings. However, it is understood that the above description does not limit the present invention in any way, and the technical features of each embodiment can be combined with each other in any way to constitute new embodiments. Furthermore, those skilled in the art, after understanding the above specific embodiments, can make various other modifications and changes to the present invention as needed. These do not depart from the essence of the present invention.

Claims

1. An aircraft cabin door handle mechanism, characterized in that, include: An inner handle assembly, the inner handle assembly having an inner handle sleeve and an inner handle, the inner handle being mounted on the end of the inner handle sleeve on one axial side; An outer handle assembly, the outer handle assembly having an outer handle sleeve and an outer handle, the outer handle sleeve being coaxially configured with the inner handle sleeve and a portion of which is located on the inner circumferential side of the inner handle sleeve, and the outer handle being disposed at the end of the outer handle sleeve on the other axial side. An inner handle lock, the inner handle lock having an engaging portion; and Operations Department The inner handle sleeve has a first groove recessed from the inner circumference of the inner handle sleeve to the outer circumference. The outer handle sleeve is axially movable relative to the inner handle sleeve and has a second groove that penetrates the outer handle sleeve radially. The outer handle assembly includes a locking mechanism that locks the outer handle when the outer handle sleeve moves relative to the inner handle sleeve to a predetermined axial position. The operating part can be operated to make the engaging part engage with the first groove and the second groove that overlap radially, and to make it disengage from the first groove and the second groove inward and outward. In the second state, the inner handle sleeve can rotate circumferentially relative to the outer handle sleeve.

2. The aircraft door handle mechanism according to claim 1, characterized in that, It also includes a first pin, which supports the inner handle sleeve. The inner handle lock has: A rod portion that extends into the interior of the inner handle sleeve and has a first through hole midway along the axial direction; An operable part is disposed on one axial end of the rod and is used to contact the operating part. as well as The engaging portion protrudes outward from the other axial end of the rod portion toward the outer periphery. The first pin passes through the first through hole and supports the rod so that it can rotate.

3. The aircraft door handle mechanism according to claim 2, characterized in that, The rod portion has a first rod portion on one axial side relative to the first through hole and a second rod portion on the other axial side relative to the first through hole, and the operable portion is disposed at the axial side end of the first rod portion. The rod portion is configured such that, when the engaging portion is in the first state, the first rod portion is along the axial direction, and the second rod portion is tilted toward the direction closer to the first groove as it moves toward the other side of the axial direction.

4. The aircraft door handle mechanism according to claim 2, characterized in that, The inner handle sleeve includes an annular main body and a pair of support portions disposed on one axial end of the main body and protruding to one axial direction. The aircraft door handle mechanism also includes a second pin, which is supported on the pair of support portions. The operating part is provided with a second through hole, and the second pin passes through the second through hole to support the operating part so that it can rotate. The inner handle has a first opening, and the axial side surface of the operating part, i.e., the first pressing surface, protrudes from the first opening. The operating part can be rotated by pressing the first pressing surface, so that the engaging part is in a first state and a second state.

5. The aircraft door handle mechanism according to claim 4, characterized in that, The operating part has a pressing part at the other end in the axial direction. By rotating the operating part, the pressing part contacts and presses the operated part, thereby causing the lever to rotate. When viewed along the axial direction, the connection point between the operated part and the rod is located on the opposite side of the first groove relative to the center of the operated part, and the contact point between the pressing part and the operated part is located on the side of the first groove relative to the connection point between the operated part and the rod.

6. The aircraft door handle mechanism according to claim 4, characterized in that, The inner handle is mounted to the inner handle sleeve via the second pin.

7. The aircraft door handle mechanism according to claim 2, characterized in that, The operated part is in the shape of a circular plate.

8. The aircraft door handle mechanism according to claim 1, characterized in that, The axial length of the second groove is greater than the axial length of the engaging portion. When the engaging part is in the first state, when the outer handle sleeve moves axially relative to the inner handle sleeve, the axial position of the engaging part in the second groove changes. When the outer handle sleeve moves relative to the inner handle sleeve to the position closest to the other side of the axial direction, the engaging part is located at one end of the axial direction in the second groove.

9. The aircraft door handle mechanism according to claim 1, characterized in that, The first groove extends axially to the other axial end of the inner handle sleeve.

10. The aircraft door handle mechanism according to claim 1, characterized in that, It also includes an elastic force-applying component housed in the inner handle sleeve. When the outer handle is locked by the locking mechanism, the elastic force-applying component is supported on the inner circumferential surface of the inner handle sleeve and applies force to the outer handle sleeve in the opposite axial direction.

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