CN117902047A - Aircraft seat and aircraft - Google Patents

Abstract

The invention relates to an aircraft seat and an aircraft. The aircraft seat comprises: a headrest; a back plate; and a seat pan pivotally mounted to the back panel and configured to pivot relative to the back panel from a seat pan stowed position to a seat pan deployed position for seating a user and to automatically pivot from the seat pan deployed position to the seat pan stowed position in response to a user's exit. The aircraft seat is further provided with a display configured to be displaced as the seat pan pivots. The aircraft comprises the aircraft seat. The aircraft seat and the aircraft provided by the invention can facilitate a crew to observe the condition in the cabin when sitting on the aircraft seat, and ensure the utilization rate of cabin space.

Description

Aircraft seat and aircraft

Technical Field

The present invention relates to the field of aircraft, and more particularly to an aircraft seat and an aircraft having the aircraft seat.

Background technique

The contents in this section merely provide background information related to the present invention and may not constitute prior art.

The space on an aircraft is usually limited, and certain areas in the aircraft's passenger cabin or cockpit require special attention in terms of comprehensive safety and space limitations, especially areas where seats are located near any emergency exits or safety doors of the aircraft, or areas where crew members (passenger cabin crew, load managers, cockpit crew, etc.) are mainly located during aircraft operation.

Seats located in certain emergency areas near emergency exit doors and main cabin doors are often designed so that one or more components of the seat can be manually or automatically placed in a stowed position when the seat is not occupied by an occupant, such as the seat cushion or seat pan and tray table. This is necessary to reduce the amount of space occupied by the seat to avoid obstructing passengers or crew members trying to go around or pass by the seat during rapid exit from the aircraft cabin.

The placement of seats or equipment in these areas or the design of the seats themselves must ensure that the crew's visual partition (also called field of view) is also unobstructed. During the flight of the aircraft, the crew is required to have a visual partition of at least 50% of the cabin area. By turning the head and body within a range of 15°, this requirement is increased to at least 80% of the entire cabin. This visual partition ensures that the crew can easily observe the condition of the cabin, especially during takeoff and landing of the aircraft, the crew must always observe the condition of the occupants and equipment to ensure safety. In view of these requirements for the field of view, aircraft designers usually avoid arranging seats in certain positions due to the limitation of the visual range, which makes it impossible to use the space in the cabin of the aircraft with maximum efficiency.

Therefore, it is desirable to improve the design of aircraft seats to accommodate more seats in the passenger cabin and/or to achieve a more efficient seating arrangement in the aircraft, while also ensuring that the seat design complies with emergency exit and crew vision requirements.

Summary of the invention

One object of the present invention is to provide an aircraft seat which, when arranged near an aircraft emergency exit area, takes up less space when not in use than when in use. Another object of the present invention is to provide an improved design of an aircraft seat for crew members, so that the crew members seated on the aircraft seat can easily observe the conditions in the main cabin without giving up the use of part of the cabin space available for installing the seat.

Provided is an aircraft seat, comprising: a headrest; a back panel, the back panel being located below the headrest; and a seat panel, the seat panel being pivotably mounted to the back panel, and being configured to be pivotable relative to the back panel from a seat panel stowed position to a seat panel deployed position for a user to sit on, and being automatically pivotable from the seat panel deployed position to the seat panel stowed position in response to the user leaving. The aircraft seat is also provided with a display, the display being configured to receive and display images in the cabin of the aircraft or other images, and the display being configured to shift with the pivoting of the seat panel, when the seat panel is pivoted to the seat panel deployed position, the display shifts to a display standby position, and as the seat panel is pivoted to the seat panel stowed position, the display shifts to a display stowed position.

The display may be mounted to the first end of the support rod, and the support rod may be configured to pivot with the pivoting of the seat pan.

The display may be mounted to the support rod via a connection device, the connection device may include: a first connection member, the first connection member is pivotally mounted to the first end of the support rod; and a second connection member, the display is mounted to the first end of the second connection member, and the second end of the second connection member is pivotally mounted to the first connection member. One of the first connection member and the second connection member may be configured to pivot about a pivot axis transverse to the support rod to adjust the pitch angle of the display, and the other of the first connection member and the second connection member may be configured to pivot about a pivot axis parallel to the support rod to adjust the lateral angle of the display.

The second end of the support rod may be mounted to the front end portion of the seat plate or the pivot shaft of the seat plate, and the support rod may be configured to be pivotable relative to the seat plate.

The second end of the support rod may be pivotally mounted to the side of the back panel.Alternatively, the second end of the support rod may be pivotally mounted to a bulkhead on which the aircraft seat is mounted and may be mounted proximate to the side of the back panel.

The aircraft seat may further include a linkage mechanism configured to correspondingly pivot the pivot shaft of the support rod according to the pivot shaft of the seat panel.

The linkage mechanism may include a sensor and an electric motor, the sensor may be configured to detect the pivoting of the pivot shaft of the seat plate, and the electric motor may be configured to drive the pivot shaft of the support rod to pivot according to the detection result of the sensor.

The monitor storage position can be located in one of the following locations: above the headrest; below the seat pan; or in the headrest.

The aircraft seat may also include an armrest, which may be configured to pivot with the pivoting of the seat pan, and the display supported by the armrest, which may be foldable or capable of being rolled up or otherwise retracted so that the display may be housed in the armrest.

Preferably, the display screen of the display can be implemented as a flexible display screen, which means that the display screen can be deformed in reverse. Flexible OLED is an example of such a display screen.

There is also provided an aircraft comprising an aircraft seat according to any of the above summaries.

The aircraft seat may be mounted to a bulkhead within the cabin of the aircraft, and the bulkhead may also be mounted with an additional display located above the headrest of the aircraft seat.

The cabin may be a passenger cabin or a cockpit of an aircraft.

The aircraft seat and aircraft according to the present invention can meet the requirements of emergency exits and crew field of view, making it convenient for crew members to observe the conditions in the cabin while sitting in the aircraft seats. Flight attendants do not need to stand or walk around in the cabin to observe the conditions in the cabin, and do not need to give up the use of part of the available space of the seats in the cabin in order to meet the crew's field of view requirements, thereby ensuring that the utilization rate of the cabin space is improved, which is conducive to higher density or more efficient seat arrangements in the aircraft.

The characteristics and other advantages of the present invention will become apparent in the following non-limiting detailed description.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments of the present invention will be described below by way of example only with reference to the accompanying drawings. In the accompanying drawings, the same features or components are represented by the same reference numerals, and the drawings are not necessarily drawn to scale, and in the accompanying drawings:

FIG1 shows a view of an aircraft seat according to a first embodiment of the invention;

2 to 5 show an example of a connection device between a display and a support rod of an aircraft seat according to a first embodiment of the present invention;

FIG6 shows a modified example of the connection device between the display and the support rod of the aircraft seat according to the first embodiment of the present invention;

FIG7 is a view showing an aircraft seat according to a second embodiment of the present invention;

8 to 11 show schematic diagrams of an aircraft seat according to a third embodiment of the present invention;

FIG12 is a schematic diagram showing a linkage mechanism of an aircraft seat according to a third embodiment of the present invention;

13 is a schematic diagram showing a modified example of the linkage mechanism of the aircraft seat according to the third embodiment of the present invention;

14 to 17 show schematic diagrams of an aircraft seat according to a fourth embodiment of the present invention;

FIG18 shows a schematic diagram of an aircraft seat according to a fifth embodiment of the present invention;

FIG19 shows a schematic diagram of an aircraft seat according to a sixth embodiment of the present invention;

20 to 22 show schematic diagrams of an armrest of an aircraft seat according to a sixth embodiment of the present invention;

FIG23 is a schematic diagram showing a modified example of an armrest of an aircraft seat according to a sixth embodiment of the present invention;

FIG24 is a schematic diagram showing another modified example of the armrest of the aircraft seat according to the sixth embodiment of the present invention; and

FIG25 shows a schematic diagram of an aircraft seat according to a seventh embodiment of the present invention; and

FIG. 26 shows a perspective view of an aircraft in which an aircraft seat according to the invention is installed.

Detailed ways

The following description is merely exemplary in nature and is not intended to limit the present invention, its application and use. It should be understood that in all of the accompanying drawings, similar reference numerals indicate the same or similar parts and features. The various drawings only schematically represent the concepts and principles of the embodiments of the present invention, and do not necessarily show the specific dimensions and proportions of the various embodiments of the present invention. Specific parts in specific drawings may be exaggerated to illustrate the relevant details or structures of the embodiments of the present invention.

In the description of the embodiments of the present invention, the directional terms related to "up", "down", "left" and "right" used are described by the up, down, left and right positions of the views shown in the accompanying drawings. In addition, in this article, the terms related to "front end" and "rear end" used are described by the direction faced by the user shown in the accompanying drawings. Relative to the direction faced by the user, the end located on the front side is defined as the "front end", and the end located on the back side is defined as the "rear end". In practical applications, the positional relationships of "up", "down", "left" and "right" used in this article can be defined according to actual conditions, and these relationships can be reversed. In addition, in this article, the conjunction "or" can include the meaning of "and/or", unless the context clearly indicates otherwise.

The aircraft seat according to the present invention is described in conjunction with its application as a crew seat in a passenger cabin of an aircraft. FIG1 shows a view of an aircraft seat 10 according to a first embodiment of the present invention, showing a crew U seated in the aircraft seat 10 .

As shown in FIG1 , the aircraft seat 10 is arranged in the aisle near the cabin door in the aircraft passenger cabin, and is arranged between the bulkheads W1 and W2 which are opposite to each other, so as not to hinder the movement of passengers in the passenger cabin as much as possible. The bulkheads W1 and W2 can be, for example, the outer wall panels of the compartments such as the onboard toilet or the pantry.

The aircraft seat 10 includes a headrest 11, a back panel 12 and a seat panel 13. The headrest 11 and the back panel 12 are fixedly mounted on the bulkhead W1. The seat panel 13 is an automatic rebound seat panel, which is pivotally mounted to the back panel 12. Specifically, the rear end of the seat panel 13 is pivotally mounted to the back panel 12. The seat panel 13 can be pivoted relative to the back panel 12 to a seat panel unfolded position for the user to sit down in response to the force applied by the user (for example, the flight attendant U), as shown in FIG1; and can be automatically pivoted toward the back panel 12 to a seat panel stowed position in response to the flight attendant U leaving the seat panel 13. In the seat panel stowed position, the seat panel 13 is folded on the back panel 12, thereby reducing the space occupied by the seat panel 13. Preferably, the automatic rebound connection device between the seat plate 13 and the back plate 12 adopts a damping connection device, so that when the seat plate 13 is about to pivot to the seat plate stowed position, the pivoting of the seat plate 13 toward the back plate 12 can be slowed down, thereby avoiding a large impact. The damping connection device can adopt any suitable type of damping connection device. For example, the damping connection device can be similar to a damping hinge connection device installed between a cabinet body and a cabinet door of furniture.

In addition, as shown in FIG1 , the aircraft seat 10 is also equipped with a display 15. The display 15 can receive information from a camera (not shown) for monitoring the images in the passenger cabin or other images, and display the images monitored by the camera on the display screen of the display 15. In addition, the display 15 is configured to shift with the pivoting of the seat panel 13, so that the attendant U can conveniently observe the status of the passengers in the passenger cabin when sitting on the aircraft seat 10, and the attendant U does not need to walk back and forth in the passenger cabin to confirm the status of the passengers, and does not need to give up the use of part of the available space of the passenger seat in the passenger cabin in order to meet the attendant's field of vision requirements. The display 15 is installed to the seat panel 13 via a support rod 14, and the support rod 14 is configured to pivot with the pivoting of the seat panel 13, so that the display 15 can shift with the pivoting of the seat panel 13.

In the example shown in the figure, the display 15 is mounted to the first end of the support rod 14, and the opposite second end of the support rod 14 is pivotally mounted to the front end of the seat plate 13, so that the support rod 14 can pivot with the seat plate 13, and the support rod 14 can also pivot relative to the seat plate 13. The pivotable connection between the support rod 14 and the seat plate 13 can be achieved by a pivot connection mechanism with a self-locking function, so that the support rod 14 can be pivoted and locked at any angle relative to the seat plate 13. The pivot connection mechanism with a self-locking function can adopt any suitable self-locking pivot connection mechanism. For example, the self-locking pivot connection mechanism adopted can be similar to the self-locking pivot connection mechanism used in a laptop computer for adjusting and locking the angle between the display screen and the body, or can be a self-locking gas spring.

When the attendant U sits on the seat plate 13 of the aircraft seat 10, as the seat plate 13 pivots to the seat plate unfolded position, the display 15 shifts to the display standby position in front of the attendant U. As shown in FIG1 , the display 15 in the display standby position is located within the field of view V of the attendant U, so that the attendant U can observe the passenger seats in the passenger cabin and the passengers sitting on the passenger seats through the images in the passenger cabin displayed on the display 15. In addition, the attendant U can also apply force to the support rod 14 as needed to pivot the support rod 14 relative to the seat plate 13, as shown by the double-headed arrow K1 in FIG1 , so as to adjust the display 15 located at the first end of the support rod 14 to a suitable position within the field of view V of the attendant U. When the attendant U stands up from the seat panel 13, the seat panel 13 automatically pivots to the seat panel stowed position, and the support rod 14 also automatically pivots toward the bulkhead W1 along with the pivoting of the seat panel 13, so that the display 15 is shifted to the display stowed position above the headrest 11 of the aircraft seat 10 without the need for additional operation by the attendant U.

Preferably, the display 15 can be pivoted relative to the support rod 14 to adjust the angle of the display screen of the display 15 .

FIG. 2 to FIG. 5 show an example of a connection device between the display 15 and the support rod 14. As shown in FIG. 2, the connection device 20 between the display 15 and the support rod 14 includes a first connection member 21 and a second connection member 22. The first connection member 21 is pivotally mounted to the first end of the support rod 14. The display 15 is mounted to the first end of the second connection member 22, and the opposite second end of the second connection member 22 is pivotally mounted to the first connection member 21. In this example, the first connection member 21 can be pivoted relative to the support rod 14 about a pivot axis A1 that is transverse to the support rod 14, as shown by the double-headed arrow K2 in FIG. 2, to adjust the pitch angle of the display 15. For example, the first connection member 21 can be pivoted from the notch 141 at the first end of the support rod 14 to the outside about the pivot axis A1, as shown in FIG. 2; or, the first connection member 21 can be pivoted about the pivot axis A1 into the notch 141, as shown in FIG. 5. The second connecting member 22 can pivot relative to the first connecting member 21 around the pivot axis A2 parallel to the support rod 14, as shown by the double-headed arrow K3 in FIG2 , so as to adjust the lateral angle of the display 15. In the example shown in the figure, the second end of the second connecting member 22 connected to the first connecting member 21 is provided with a hook portion 221, which is arc-shaped and hooked to the mounting handle (not shown in the figure) of the first connecting member 21, so that the second connecting member 22 can pivot around the mounting handle of the first connecting member 21.

When the display 15 is displaced to the display standby position shown in FIG. 1 as the seat plate 13 is unfolded, the display screen 151 of the display 15 faces the attendant U. At this time, the first connecting member 21 is partially located outside the notch 141 of the support rod 14, and the hook 221 of the second connecting member 22 is located outside the notch 141 of the support rod 14, as shown in FIG. 2. At this time, if the current pitch angle position of the display screen 151 of the display 15 is not particularly suitable for the attendant U, the attendant U can apply force to the display 15 to pivot the display 15 relative to the support rod 14 around the pivot axis A1 via the second connecting member 22 and the first connecting member 21. For example, the display 15 can be pivoted toward the attendant U to the position shown in FIG. 3. In the position shown in FIG. 3, the display 15 is pivoted to be substantially perpendicular to the support rod 14. In addition, the attendant U can also apply force to the display 15 to pivot the display 15 relative to the first connecting member 21 around the pivot axis A2 via the second connecting member 22 to adjust the lateral angle of the display 15.

When the use is finished, the attendant U can place the display 15 in the position shown in FIG. 2 , and directly stand up and leave the seat panel 13 of the aircraft seat 10 without performing additional operations on the display 15 or the support rod 14. As the seat panel 13 is retracted to the seat panel retracted position, the display 15 and the support rod 14 pivot toward the bulkhead W1, and the display 15 is shifted to the display storage position. Since the angle between the support rod 14 and the seat panel 13 is less than 180 degrees, during the process of the support rod 14 pivoting with the seat panel 13, the display 15 located at the first end of the support rod 14 will first approach the bulkhead W1 or the headrest 11. Due to the damping connection between the seat panel 13 and the back panel 12, the pivoting of the seat panel 13 will slow down, avoiding a large collision between the display 15 and the bulkhead W1 or the headrest 11. Preferably, the frame 152 and/or the housing of the display screen 151 of the display 15 are made of flexible materials, so that when the display 15 is pivoted with the seat plate 13, when the display 15 contacts the bulkhead W1 or the headrest 11, the impact and wear on the display screen 151 are reduced. Alternatively, when the attendant U is ready to stand up, the attendant U can push the support rod 14 so that the angle between the support rod 14 and the seat plate 13 is approximately 180 degrees, thereby preventing the display 15 from contacting the bulkhead W1 or the headrest 11 first when the display 15 is displaced with the pivoting of the seat plate 13.

As the seat panel 13 continues to pivot to the seat panel stowed position, the contact between the display 15 and the bulkhead W1 or the headrest 11 causes the display 15 and the support rod 14 to pivot relative to the seat panel 13 to be substantially in line with the seat panel 13, and the display 15 is shifted to the display stowed position above the headrest 11. At this time, the display screen 151 of the display 15 faces the bulkhead W1. Preferably, an additional display D can be provided at a suitable position of the bulkhead W1 (for example, a position above the headrest 11), so that when the attendant U stands, even if the display screen 151 of the display 15 faces the bulkhead W1 and is not visible, the attendant U can observe the situation in the passenger cabin through the additional display D.

In addition, when the attendant U is ready to stand up, the attendant U can pivot the display 15 relative to the support rod 14 around the pivot axis A1 to the position shown in FIG. 4 via the second connecting member 22 and the first connecting member 21, and further pivot until the first connecting member 21 is finally accommodated in the recess 141 of the support rod 14, as shown in FIG. 5. Then, when the attendant U stands up and leaves the seat panel 13, as the seat panel 13 is retracted to the seat panel retracted position, the support rod 14 pivots toward the bulkhead W1, so that the display 15 is shifted to the display retracted position above the headrest 11. At this time, the back side 153 of the display 15 faces the bulkhead W1, and the display screen 151 faces outward, so that the attendant U can still observe the situation in the passenger cabin through the display screen 151 when standing up.

The connection means between the display 15 and the support bar 14 is not limited to the form of the connection means 20 shown in Figures 2 to 5. Figure 6 shows a modified example of the connection means between the display 15 and the support bar 14.

As shown in FIG6 , the connection device 20A between the display 15 and the support rod 14 includes a first connection member 21A and a second connection member 22A. The first end of the first connection member 21A is pivotally mounted to the first end of the support rod 14, so that the first connection member 21A can pivot relative to the support rod 14 around a pivot axis B1 parallel to the support rod 14, as shown by the double-headed arrow K4 in FIG7 , so as to adjust the lateral angle of the display 15. The opposite second end of the first connection member 21A is provided with a concave mounting portion 211. The second connection member 22A is provided with a convex mounting portion 221. The convex mounting portion 221 is mounted to the concave mounting portion 211 of the first connection member 21A, and can pivot relative to the first connection member 21A in the concave mounting portion 211 around a pivot axis B2 transverse to the support rod 14, as shown by the double-headed arrow K5 in FIG6 , so as to adjust the pitch angle of the display 15. In the example shown in the figure, the concave mounting portion 211 is an open concave portion with a C-shaped cross section, and the convex mounting portion 221 is a column portion with a C-shaped cross section. The second connecting member 22A is also provided with a connecting plate 222 and a mounting plate 223, and the convex mounting portion 221 is connected to the mounting plate 223 via the connecting plate 222. The convex mounting portion 221, the connecting plate 222 and the mounting plate 223 can be formed integrally. The display 15 is fixedly mounted on the mounting plate 223 of the second connecting member 22A. When installed, the convex mounting portion 221 of the second connecting member 22A is aligned with the concave mounting portion 211 of the first connecting member 21A, and the connecting plate 222 of the second connecting member 22A is aligned with the opening of the concave mounting portion 211 of the first connecting member 21A, and the second connecting member 22A is mounted to the first connecting member by sliding in the direction of the pivot axis B2. In the figure, in order to show the structure of the first connecting member 21A and the second connecting member 22A, the end cap at the end of the concave mounting portion 211 is not shown. By installing the second connecting member 22A and the first connecting member 21A and the first connecting member 21A and the support rod 14, the display 15 is pivotably installed to the support rod 14, so that the display 15 can pivot relative to the support rod 14 along the direction indicated by the double-headed arrow K4 or the direction indicated by the double-headed arrow K5, thereby adjusting the angle of the display 15.

The aircraft seat 10 according to the first embodiment of the present invention is introduced above. The aircraft seat 10 according to the first embodiment of the present invention is provided with a display 15, which can facilitate the crew to observe the status of passengers in the passenger cabin during the flight of the aircraft, and the display 15 can be displaced with the pivoting of the seat plate 13, and automatically move to the display standby position and the display storage position as the seat plate 13 is unfolded and retracted, without the need for additional actions by the crew, so the crew can observe the situation in the passenger cabin through the display 15 when sitting in the aircraft seat 10, and the crew does not need to stand or walk in the passenger cabin to observe the situation in the passenger cabin, and there is no need to give up the use of part of the available space of the passenger seat in the passenger cabin to meet the crew's field of vision requirements, thereby ensuring the effective use of the space in the passenger cabin.

FIG7 shows an aircraft seat 10A according to a second embodiment of the present invention. The aircraft seat 10A has substantially the same construction as the aircraft seat 10 according to the first embodiment of the present invention, and the aircraft seat 10A is also equipped with a display 15, and the difference lies only in the installation position of the support rod 14A of the aircraft seat 10A for installing the display 15. In the following, only the difference between the aircraft seat 10A and the aircraft seat 10 will be described, and the same parts of the aircraft seat 10A and the aircraft seat 10 will be represented by the same reference numerals, and will not be described repeatedly.

As shown in FIG7 , in the aircraft seat 10A, the second end of the support rod 14A is mounted to the pivot shaft at the rear end of the seat panel 13 so as to be able to pivot with the seat panel 13. As the seat panel 13 pivots to the seat panel deployment position, the support rod 14A can pivot to the position shown in FIG7 so that the display 15 is in the display standby position; and when the attendant U leaves the seat panel 13, as the seat panel 13 pivots to the seat panel stowed position, the support rod 14A pivots toward the bulkhead W1 so as to shift the display to the display stowed position above the headrest 11. Preferably, the support rod 14A is mounted to be able to pivot relative to the seat panel 13, so that the attendant U can pivot the support rod 14A relative to the seat panel 13 by applying force to the support rod 14A as needed, as shown by the double-headed arrow K6 in FIG7 , thereby adjusting the display 15 located at the first end of the support rod 14A to a suitable position within the field of view V of the attendant U.

The connection between the display 15 and the support rod 14A may adopt the connection device 20 or the connection device 20A in the aircraft seat 10 according to the first embodiment of the present invention, and the description thereof will not be repeated here.

The aircraft seat 10A according to the second embodiment of the present invention can achieve similar beneficial technical effects as the aircraft seat 10 of the first embodiment.

8 to 13 show schematic diagrams of an aircraft seat 10B according to a third embodiment of the present invention. The aircraft seat 10B has substantially the same structure as the aircraft seat 10 according to the first embodiment of the present invention, and the aircraft seat 10B is also equipped with a display 15, the only difference being the installation of a support rod 14B for installing the display 15 of the aircraft seat 10B.

Figures 8 and 9 show the aircraft seat 10B in a folded state, and Figures 10 and 11 show the aircraft seat 10B in an unfolded state. Figures 8 and 10 are front views of the aircraft seat 10B, and Figures 9 and 11 are side views of the aircraft seat 10B.

The display 15 of the aircraft seat 10B is arranged to the side of the back panel 12 via the support rod 14B. The display 15 is mounted to the first end of the support rod 14B, and the opposite second end of the support rod 14B is pivotally mounted to the side of the back panel 12 and is arranged to pivot with the pivoting of the seat panel 13. When the seat panel 13 is pivoted from the seat panel stowed position shown in Figures 8 and 9 to the seat panel deployed position shown in Figures 10 and 11, the support rod 14B is correspondingly pivoted to the position shown in Figures 10 and 11, so that the display 15 is in the display standby position.

To this end, the aircraft seat 10B is provided with a linkage mechanism 30, which is configured to pivot the pivot shaft of the support rod 14B accordingly according to the pivot of the pivot shaft of the seat plate 13, so that the display 15 is displaced accordingly. FIG12 shows a schematic diagram of the linkage mechanism 30. As shown in FIG12, the linkage mechanism 30 is configured as a link mechanism, including a first link 31, a second link 32, and a third link 33. The first link 31 is partially fixedly connected (e.g., welded) to the pivot shaft 135 of the seat plate 13, preferably, fixed to the pivot shaft 135 in the radial direction of the pivot shaft 135, so that the suspension end of the first link 31 is located outside the pivot shaft 135. The second link 32 is partially fixedly mounted (e.g., welded) to the pivot shaft 145 of the support rod 14B, preferably, fixed to the pivot shaft 145 in the radial direction of the pivot shaft 145, so that the suspension end of the second link 32 is located outside the pivot shaft 145. A sliding universal joint 34 is mounted on the second link 32, and the sliding universal joint 34 can slide along the second link 32 within a certain range. One end of the third link 33 is hinged to the suspension end of the first link 31, and the other end of the third link 33 is hinged to the sliding universal joint 34. When the pivot shaft 135 of the seat plate 13 is pivoted as shown by arrow T1 to pivot the seat plate 13, the pivoting of the pivot shaft 135 drives the first link 31 to pivot, and drives the second link 32 to pivot via the third link 33 and the sliding universal joint 34, and thereby drives the pivot shaft 145 of the support rod 14B to pivot as shown by arrow T2, so that the pivoting of the seat plate 13 causes the support rod 14B to pivot in linkage. The linkage mechanism 30 can be accommodated inside the back plate 12 and is not visible from the outside, so as not to affect the appearance of the aircraft seat 10B.

In the above example, the linkage mechanism 30 is designed as a mechanical linkage mechanism. However, the present invention is not limited thereto. In other examples according to the present invention, the linkage mechanism 30 can also be designed as an electric mechanism, so that the entire structure is more compact. FIG. 13 shows a linkage mechanism 30A according to a modified example. As shown in FIG. 13 , the linkage mechanism 30A includes a sensor S and an electric motor M. The sensor S is configured to detect the pivoting of the pivot shaft 135 of the seat plate 13. The electric motor M drives the pivot shaft 145 of the support rod 14B to pivot accordingly according to the detection result of the sensor S.

The aircraft seat 10B according to the third embodiment of the present invention can achieve similar advantageous technical effects as the aircraft seat 10 of the first embodiment and the aircraft seat 10A of the second embodiment.

14 to 17 show schematic diagrams of an aircraft seat 10C according to a fourth embodiment of the present invention. The aircraft seat 10C has substantially the same construction as the aircraft seat 10B according to the third embodiment of the present invention, the difference being only in the design of the display 15 of the aircraft seat 10C.

14 and 15 show a state where the aircraft seat 10C is stowed, and FIGS. 16 and 17 show a state where the aircraft seat 10C is unfolded, wherein FIGS. 14 and 16 are front views of the aircraft seat 10C, and FIGS. 15 and 17 are side views of the aircraft seat 10C.

The display 15C of the aircraft seat 10C is mounted to a first end of a support rod 14C, and an opposite second end of the support rod 14C is pivotally mounted to a side of the back panel 12 and is configured to pivot with the pivoting of the seat panel 13. The linkage between the support rod 14C and the seat panel 13 is achieved by the linkage mechanism 30 or the linkage mechanism 30A used in the aircraft seat 10B, and will not be described again here.

As shown in FIG14 , the display storage position of the display 15C is located in the headrest 11C, and a part of the headrest 11C is configured to store the display 15C. Preferably, the display 15C adopts a foldable display screen. When in the display storage position, the two parts of the display 15C overlap each other, making the aircraft seat more compact as a whole. When the seat plate 13 pivots to the seat plate deployment position, the display 15C is shifted to the display standby position in the field of view in front of the crew via the support rod 14C along with the pivoting of the seat plate 13. Then, the crew unfolds the two overlapping parts of the display 15C as shown by the arrows shown in FIG17 , so that the display screen of the display 15C is unfolded, as shown in FIG16 and FIG17 , for the crew to use.

The aircraft seat 10C according to the fourth embodiment of the present invention can achieve similar advantageous technical effects as the aircraft seat 10B of the third embodiment.

FIG18 is a schematic diagram of an aircraft seat 10D according to a fifth embodiment of the present invention, showing a state where the aircraft seat 10D is stowed. The aircraft seat 10D has a substantially similar structure to the aircraft seat 10B according to the third embodiment of the present invention, and the difference is only in the display storage position of the display 15 of the aircraft seat 10D. As shown in FIG18 , the display storage position of the display 15 is located below the seat plate 13.

The aircraft seat 10D according to the fifth embodiment of the present invention can achieve similar advantageous technical effects as the aircraft seat 10B of the third embodiment.

19 to 22 show schematic diagrams of an aircraft seat 10E according to a sixth embodiment of the present invention. The aircraft seat 10E differs from the aircraft seats of the previous embodiments in that the aircraft seat 10E is provided with an armrest, and the monitor is supported and stored by the armrest.

FIG19 shows the state of the aircraft seat 10E being stowed. As shown in FIG19 , the aircraft seat 10E includes a headrest 11, a back panel 12, a seat panel 13, and also includes an armrest 16. One end of the armrest 16 is pivotally mounted to the side of the back panel 12, and is configured to be linked with the seat panel 13. As the seat panel 13 pivots to the seat panel stowed position, the armrest 16 is stowed to both sides of the back panel 12, as shown in FIG19. And, as the seat panel 13 pivots to the seat panel unfolded position, the armrest 16 is unfolded for use.

The aircraft seat 10E is provided with a display 15E, and the display 15E is a foldable display. FIG. 20 shows a three-dimensional view of the armrest 16. As shown in FIG. 20, the display 15E is folded and accommodated in the armrest 16, and a gripping portion 154 is provided on the back shell of the display 15E so that the flight attendant can grip it to unfold the display 15E in the direction indicated by the arrow so that the display screen 151 of the display 15E faces outward, as shown in FIG. 21. In the example shown in the figure, the gripping portion 154 can be implemented as a recessed portion that can accommodate the flight attendant's fingers. After the display 15E is unfolded to the state shown in FIG. 21, the display 15E can be pivoted upward to adjust the pitch angle to a suitable angle, as shown in FIG. 22.

The aircraft seat 10E according to the sixth embodiment of the present invention can achieve beneficial technical effects similar to those of the aircraft seats of the previous embodiments. In addition, the arrangement between the armrest 16 and the display 15E is not limited to the above implementation, and the armrest and the display can be modified in various ways as long as the display can be supported and stored by the armrest.

FIG23 shows a perspective view of an armrest 16F of a modified example. As shown in FIG23 , a hollow inner cavity is provided at the front end of the armrest 16F. The display 15F adopts a foldable display, which is supported and accommodated in the hollow inner cavity of the armrest 16F. The armrest 16F is also provided with a switch 161. When the armrest 16F is unfolded from the back plate as the seat plate is unfolded, the display 15F pops out from the armrest 16F by pressing the switch 161, as shown by the arrow in FIG23. Afterwards, the overlapping parts of the display 15F are unfolded, and the display screen of the display 15F is pivoted to a suitable angle for use.

FIG24 shows a perspective view of an armrest 16G of another modified example. As shown in FIG24 , the armrest 16G is provided with a receiving recess 162 and a reel 163. The reel 163 is pivotally mounted at the end of the armrest 16G, and can be pivoted to be accommodated in the receiving recess 162 of the armrest 16G, and can be pivoted to the outside from the receiving recess 162 of the armrest 16G. The display 15 includes a flexible display screen, and is accommodated by being wound in the reel 163 and pivoting the reel 163 to the receiving recess 162.

Fig. 25 shows a schematic diagram of an aircraft seat 10F according to a seventh embodiment of the present invention. The aircraft seat 10F has substantially the same configuration as the aircraft seat 10B according to the third embodiment of the present invention, except for the installation position of the support rod for supporting the display of the aircraft seat 10F.

As shown in FIG. 25 , the display 15 is mounted to a first end of a support rod 14F, and the opposite second end of the support rod 14F is pivotably mounted to a bulkhead W1 on which the aircraft seat 10F is mounted, and is mounted close to the side of the back plate 12 of the aircraft seat 10F. The support rod 14F is configured to pivot accordingly with the pivoting of the seat plate 13, so that the display 15 is displaced accordingly. The linkage between the support rod 14F and the seat plate 13 can use the linkage mechanism 30 or the linkage mechanism 30A in the aircraft seat 10B according to the third embodiment of the present invention, and will not be described again.

The aircraft seat 10F according to the seventh embodiment of the present invention can achieve similar advantageous technical effects as the aircraft seats of the aforementioned embodiments.

Fig. 26 shows a perspective view of an aircraft 1 equipped with the aircraft seat according to the present invention. By installing the aircraft seat according to the present invention, the crew can conveniently observe the conditions in the passenger cabin of the aircraft 1 while sitting on the aircraft seat, without giving up part of the available space in the passenger cabin to meet the crew's field of vision requirements, thereby ensuring that the space in the passenger cabin of the aircraft 1 is effectively utilized.

The above describes an exemplary embodiment of the aircraft seat according to the present invention in conjunction with the application of the aircraft seat in the crew seat of the aircraft's passenger cabin. However, it should be noted that the aircraft seat according to the present invention is not limited to being installed in the bulkhead of the passenger cabin to be used as a crew seat in the passenger cabin. In other examples according to the present invention, the aircraft seat can be installed to the bulkhead near each exit of the aircraft. For example, the bulkhead W1 on which the aircraft seat is installed can be the bulkhead of the cockpit of the aircraft, and preferably, the bulkhead W1 of the passenger cabin on which the aircraft seat is installed can also be installed with an additional display D, which can be located, for example, above the landing of the aircraft seat.

The exemplary embodiments of the aircraft seat and the aircraft according to the present invention are described in detail above. It should be understood that the present invention is not limited to the specific embodiments described and shown in detail above. Without departing from the spirit and scope of the present invention, those skilled in the art can make various modifications and variations to the present invention. All these modifications and variations fall within the scope of the present invention. Moreover, all the components described herein can be replaced by other technically equivalent components.

Claims (14)

1. An aircraft seat, the aircraft seat comprising:

A headrest;

A back plate positioned below the headrest; and

A seat pan pivotally mounted to the back panel and configured to pivot relative to the back panel from a seat pan stowed position to a seat pan deployed position for seating a user, and to automatically pivot from the seat pan deployed position to the seat pan stowed position in response to a departure of the user,

Wherein the aircraft seat is further provided with a display configured to be displaced as the seat pan pivots to the seat pan deployed position, the display being displaced to a display standby position when the seat pan pivots to the seat pan stowed position, and the display being displaced to a display stowed position as the seat pan pivots to the seat pan stowed position.

2. The aircraft seat of claim 1, wherein the display is mounted to a first end of a support bar and the support bar is configured to pivot with the pivoting of the seat pan.

3. The aircraft seat of claim 2, wherein the display is mounted to the support bar via a connection device comprising:

A first link pivotally mounted to the first end of the support bar; and

A second link, the display being mounted to a first end of the second link and a second end of the second link being pivotally mounted to the first link,

Wherein one of the first and second links is configured to pivot about a pivot axis transverse to the support bar to adjust a pitch angle of the display, and the other of the first and second links is configured to pivot about a pivot axis parallel to the support bar to adjust a lateral angle of the display.

4. The aircraft seat of claim 2, wherein the second end of the support bar is mounted to a front end of the seat pan or a pivot axis of the seat pan, and the support bar is configured to be pivotable relative to the seat pan.

5. The aircraft seat of claim 2, wherein the second end of the support bar is pivotally mounted to a side of the back panel, or

The second end of the support bar is pivotally mounted to a bulkhead in which the aircraft seat is mounted and is mounted proximate a side of the back panel.

6. The aircraft seat of claim 5, further comprising a linkage mechanism configured to pivot the pivot shaft of the support bar accordingly in response to pivoting of the pivot shaft of the seat pan.

7. The aircraft seat of claim 6, wherein the linkage comprises:

A sensor configured to detect a pivoting of a pivot shaft of the seat pan; and

And an electric motor that drives the pivot shaft of the support lever to pivot according to a detection result of the sensor.

8. The aircraft seat of claim 2, wherein the display stow position is located in one of: the upper part of the headrest; the lower part of the seat plate; or in the headrest.

9. The aircraft seat of claim 1, further comprising an armrest configured to pivot with the pivoting of the seat pan, and the display supported by the armrest, the display being capable of being folded or rolled to be housed in the armrest.

10. The aircraft seat of any one of claims 1-9, wherein a display screen of said display is a flexible display screen.

11. The aircraft seat of any one of claims 1-9, wherein said display is configured to receive and display a picture within a cabin of said aircraft.

12. An aircraft characterized by comprising an aircraft seat according to any one of claims 1-11.

13. The aircraft of claim 12 wherein the aircraft seat is mounted to a bulkhead within a cabin of the aircraft and the bulkhead is further mounted with an additional display located above a headrest of the aircraft seat.

14. The aircraft of claim 13 wherein the cabin is a passenger cabin or cockpit of the aircraft.