Aircraft seat

Abstract

The invention relates to an aircraft seat, which comprises a seat body (1) and a mounting seat assembly, and comprises a seat slide rail (3) provided with a chute (31); the mounting buckle seats (2) are connected to the lower ends of chair legs of the chair body (1), supporting blocks (21) extending in the direction perpendicular to the sliding direction are arranged on the mounting buckle seats (2) in the sliding direction, and connecting seats (22) and fixing seats (24) are arranged on the upper surfaces of the mounting buckle seats (2); the locking assembly (5) is provided with a locking block (57) and a rod assembly, and the lower end of the rod assembly is connected with the locking block (57); the fixing assembly (6) is provided with a fixing bolt (61) and a limiting part, the lower end of the fixing bolt (61) is connected with the limiting part, the locking block (57) is installed in the sliding groove (31) in a shape matching mode, the rod assembly penetrates through the connecting base (22) and can rotate in the connecting base (22), and the fixing bolt (61) penetrates through the fixing base (24) in a screwed mode and abuts against the sliding groove (31) through the limiting part.

Description

Technical Field

[0001] The invention relates to the field of aircraft parts, and in particular to an aircraft seat which is easy to disassemble and install. Background Art

[0002] Aircraft seats are basic seating facilities for passengers in flight, usually installed in the cockpit and cabin, usually in a 3-4-3 or 3-3 form. During installation, the seats are usually fixedly connected to the seat rails through the leg lock connectors of the chair legs. The seat rails are installed in the aircraft floor to ensure that the aircraft is in a stable state after installation.

[0003] However, most of the current seats are fixed to the floor by bolts. During installation, the seat must be aligned with the fixed seat, and the bolts must be aligned with the threaded holes and tightened, which makes the operation process more complicated. In the prior art, there are also some seats for quick disassembly and installation to solve the problem of complicated installation process mentioned above. For example, the applicant Hubei Hangyu Jiatai Aircraft Equipment Co., Ltd. applied for Chinese invention patent application CN108674667A entitled "Aircraft Seat and Its Quick-Release Leg Lock" on April 28, 2018, disclosing a quick-release leg lock for an aircraft seat. The lock includes a lock body, a pressure block and an elastic support device. The lock body is installed on the floor slide rail. The pressure block is connected to the lock body through the main lock body rotating pin, and is locked or unlocked by a quick-lock fastening screw and a quick-lock buckle pin. After unlocking, the elastic support device can lift the pressure block to facilitate quick disassembly. The locking or unlocking operation can be completed by rotating the quick-lock fastening screw (only 1 / 4 turn is required). However, during installation, the operator needs to align the arc block of the main body with the arc groove of the seat slide rail, and there are still complicated operations of multiple alignments, and the problem of the complicated installation process is not further solved.

[0004] In addition, the Chinese utility model patent CN219029741U entitled "A mechanism for connecting the legs of aircraft seats" submitted by the patentee Zhejiang Jiahang Technology Co., Ltd. discloses a mechanism for connecting the legs of aircraft seats. The mechanism mainly includes a guide rail, a spring, an expansion top block, an extension rod, and a locking and snap-fit ​​assembly. By inserting the chair legs into the guide rail, automatic locking is achieved by utilizing the cooperation of the spring and the expansion top block. At the same time, the design of the pressing rod and the collar can quickly release the locking state, simplifying the disassembly process and improving operational efficiency. However, as the spring used to elastically fix the expansion block is used for a long time, its elasticity will decrease, making it impossible to provide sufficient jacking force for the expansion top block, resulting in the inability to ensure that the expansion rod and the fixing rod remain in contact, causing the seat to loosen.

[0005] In summary, the installation method of aircraft seats in the prior art requires multiple installation and alignment of parts during the installation process, which makes the installation process relatively complicated. In addition, apart from the initial replacement of new parts after the seat becomes loose, there is no way to compensate for the problem of decreased spring elasticity, which causes the problem of decreased stability of the seat due to looseness. Summary of the invention

[0006] The present invention is completed in view of the above problems, and its purpose is to provide an aircraft seat which is easy to install and disassemble and has high stability.

[0007] According to a first aspect of the present invention, an aircraft seat is provided, and more particularly, an aircraft seat capable of being quickly installed or disassembled. The aircraft seat comprises a seat body and a mounting seat assembly, wherein the mounting seat assembly comprises:

[0008] A seat slide rail, wherein the seat slide rail is provided with a slide groove in a sliding direction;

[0009] A mounting buckle seat, which is connected to the lower end of the chair leg of the seat body, the mounting buckle seat is provided with a support block extending perpendicular to the sliding direction in the sliding direction, and the upper surface of the mounting buckle seat is provided with a connecting seat and a fixing seat;

[0010] A locking assembly, the locking assembly comprising a locking block and a rod assembly, wherein the lower end of the rod assembly is connected to the locking block; and

[0011] The fixing assembly comprises a fixing bolt and a limiting part, wherein the lower end of the fixing bolt is connected to the limiting part.

[0012] The locking block is installed in the slide groove in a form-fitting manner, the support block abuts against the upper surface of the seat slide rail, the rod assembly passes through the connecting seat, and the rod assembly can rotate in the connecting seat, and the fixing bolt is screwed through the fixing seat and abuts against the slide groove through the limiting portion. Preferably, the locking assembly also includes a limiting rod, which is installed at the top of the rod assembly and is used to operate the rotation of the locking block during installation and removal.

[0013] It should be noted that the term "longitudinal" in the present invention refers to the sliding direction along the slide groove, and the term "lateral" refers to the direction perpendicular or substantially perpendicular to the sliding direction along the slide groove. Figure 3 As shown, D1 is the "longitudinal" direction, which is parallel or substantially parallel to the sliding direction of the slide groove, D2 is the vertical direction, and D3 is the "lateral" direction, which is perpendicular to both D1 and D2.

[0014] The present invention provides a locking assembly and a fixing assembly. When installing the seat, the mounting buckle seat on which the seat body is mounted is inserted into the target position inside the slide groove, and the position of the locking block is changed from the longitudinal direction to the transverse direction by manually rotating the limit rod. At this time, the limit part is abutted against the bottom of the slide groove by rotating the fixing bolt. As the fixing bolt is further tightened, the locking block is lifted in the vertical direction and further abuts against the upper edge of the slide groove, so that the friction between the locking block and the slide groove is increased, thereby achieving stable installation of the aircraft seat. This installation process eliminates the multiple alignment operations between components, such as bolts and threaded holes, in the prior art, and is easy to achieve rapid installation or disassembly of the aircraft seat.

[0015] Preferably, in another embodiment of the present invention, the locking assembly further comprises at least two elastic limiting mechanisms, and the elastic limiting mechanisms comprise:

[0016] A sliding hole, the upper end of which abuts against the upper edge of the sliding groove;

[0017] a first spring disposed in the sliding hole; and

[0018] Two limiting balls are respectively arranged at the two ends of the first spring.

[0019] The first spring makes the two limiting balls contact the slide grooves, and the two elastic limiting heads have a vertical direction, are arranged in the locking block, and are respectively arranged on both sides of the locking block. Preferably, the two elastic limiting mechanisms are symmetrically arranged in the locking block. Preferably, the locking assembly has at least four elastic limiting mechanisms, which are arranged in the locking block, and two are respectively arranged on both sides of the locking block. More preferably, the four elastic limiting mechanisms are symmetrically arranged in the locking block.

[0020] In another embodiment of the present invention, a guide groove extending along the sliding direction is provided at the abutment position between the slide groove and the two limiting balls, and the limiting balls abut against the guide groove.

[0021] By setting up an elastic limiting mechanism, during the installation process, when the limiting rod is manually rotated to change the position of the locking block from the longitudinal direction to the transverse direction, the locking block is in a relatively fixed state with the guide groove, i.e., the seat slide rail, through the elastic limiting mechanism, so that the locking block and the seat slide rail are further fixed. In addition, since the elastic limiting mechanism is set up, the friction between the locking block and the slide groove is reduced through the action of the spring and the limiting ball, which is more conducive to installation.

[0022] Preferably, in another embodiment of the present invention, a long rack is provided at the bottom of the slide groove in the sliding direction, and a limiting tooth seat is connected to the lower end of the limiting portion, and the limiting tooth seat is meshed with the long rack. The relative position between the mounting buckle seat and the seat slide rail in the sliding direction is further limited by the meshing of the limiting tooth seat and the long rack, and the position of the seat body in the sliding direction is further fixed.

[0023] Preferably, a sliding member is provided on the lower surface of the mounting buckle seat, for example, the sliding member can be implemented as a gear, preferably a rolling gear, which is meshed with the long rack and can drive the mounting buckle seat to slide in the sliding groove along the sliding direction, so as to facilitate the movement of the mounting buckle seat, that is, the seat body, during the installation process. The present invention provides a sliding member on the lower surface of the mounting buckle seat, so that during the installation process, when the mounting buckle seat is moved along the sliding direction, the movement is smoother, and the time required to move the mounting buckle seat to the target position is reduced.

[0024] Preferably, in another embodiment of the present invention, the rod assembly includes a rotating rod and a movable rod, the movable rod is sleeved in the rotating rod, the movable rod and the rotating rod cannot rotate relative to each other, and a second spring is arranged between the movable rod and the rotating rod, and both ends of the second spring are fixedly connected to the movable rod and the rotating rod respectively.

[0025] In another embodiment of the present invention, the locking assembly further comprises a threaded sleeve, the threaded sleeve is screwed into the connecting seat, and the rod assembly is rotatably connected in the threaded sleeve.

[0026] When wear occurs between the locking block and the slide groove resulting in inconsistency in the vertical dimension, or when the elastic force of the second spring decreases with use, the threaded sleeve is screwed to change its position in the vertical direction, thereby changing the relative distance between the locking block and the mounting buckle seat, so that the upper surface of the locking block in the horizontal state always remains in contact with the upper edge of the slide groove, avoiding unnecessary replacement of the spring when the elastic force decreases, thereby ensuring the stability of the seat body after installation.

[0027] In another embodiment of the present invention, an anti-loosening component is further provided on the top of the fixing seat to prevent the fixing bolt from loosening. For example, it can be achieved by an anti-loosening washer, and in the present invention, it is achieved by a limiting plate, and the position of the limiting plate can be elastically fixed by a limiting hemisphere. When there is no external force on the fixing bolt, it will not loosen, thereby enhancing the stability of the structure.

[0028] In addition, in another embodiment of the present invention, an aircraft seat is provided with a foldable footrest, and the user can adjust the height of the foldable footrest in the vertical direction according to actual needs to provide foot support and further improve riding comfort. When not needed, the foldable footrest can be folded up to help increase the user's leg room.

[0029] Therefore, the present invention provides an aircraft seat that is easy to install or disassemble and also has multiple limiting fixing devices, thereby reducing multiple alignments of parts during the installation process and simplifying the installation process. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The following drawings are only used to provide a further understanding of the present invention, constitute a part of this specification, and are used to explain the principles of the present invention, but do not constitute a limitation of the present invention.

[0031] In the diagram:

[0032] Figure 1 is a schematic diagram of the overall structure of an aircraft seat according to an embodiment of the present invention;

[0033] Figure 2 is another overall structural schematic diagram of an aircraft seat according to an embodiment of the present invention;

[0034] Figure 3 is a schematic diagram of a mounting base assembly according to an embodiment of the present invention;

[0035] Figure 4 is an exploded view of a mounting base assembly according to an embodiment of the present invention;

[0036] Figure 5 is a cross-sectional view of a mounting seat assembly along a sliding direction according to an embodiment of the present invention;

[0037] Figure 6 A cross-sectional view of a mounting buckle seat along a sliding direction according to an embodiment of the present invention;

[0038] Figure 7 It is a schematic diagram of the structure of the matching installation buckle seat, the support block, the connecting seat, the limiting seat and the fixing seat according to an embodiment of the present invention;

[0039] Figure 8 is an exploded view of a locking assembly according to an embodiment of the present invention;

[0040] Fig. 9 An exploded view of a threaded sleeve, a rotating rod, and a second spring according to an embodiment of the present invention;

[0041] Fig.10 is a cross-sectional view of a mounting seat assembly according to an embodiment of the present invention;

[0042] Fig.11 for Fig.10 A schematic diagram of the enlarged structure at A in the middle;

[0043] Fig.12 An exploded view of a mounting buckle seat, a sliding member, a locking assembly and a fixing assembly according to an embodiment of the present invention;

[0044] Fig.13 is an exploded view of a mounting post and a T-block according to an embodiment of the present invention;

[0045] Fig.14 FIG. 1 is an exploded view of a fixing bolt and a mounting column according to an embodiment of the present invention. DETAILED DESCRIPTION

[0046] In order to enable those skilled in the art to better understand the scheme of the present application, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only embodiments of a part of the present application, rather than all embodiments.

[0047] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the terms used in this way can be interchanged where appropriate, so as to describe the embodiments of the present application described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions.

[0048] In the present application, the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical" and "horizontal" are based on the orientations or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0049] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those skilled in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances.

[0050] In addition, the terms "install", "set", "arrange", "have", "connect", and "socket" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediary medium, or it can be an internal connection between two devices, elements, or components. For those skilled in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0051] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. To make the scheme of the present invention clearer, the present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0052] like Figure 1 and Figure 2 The figures are respectively a schematic diagram of the overall structure of an aircraft seat according to an embodiment of the present invention and another schematic diagram of the overall structure of an aircraft seat according to an embodiment of the present invention. The present invention provides an aircraft seat that is easy to install and has a footrest structure. The aircraft seat comprises a seat body 1, a mounting buckle seat 2, a seat slide rail 3 laid on the floor, a locking assembly 5 and a fixing assembly 6. The mounting buckle seat 2 is fixedly connected to the lower end of the chair leg of the seat body 1, and the mounting buckle seat 2 is movably connected to the upper part of the seat slide rail 3.

[0053] like Figure 3 and Figure 4 As shown, they are respectively a schematic diagram of a mounting seat assembly according to an embodiment of the present invention and an exploded view of a mounting seat assembly according to an embodiment of the present invention. Two sets of hollow connection seats 22 are connected through the upper surface of the mounting buckle seat 2, a fixing seat 24 is fixedly connected to the rear side of the upper surface of the mounting buckle seat 2, a slide groove 31 is provided inside the seat slide rail 3, and a long rack 311 is fixedly connected to the bottom side of the inner side of the slide groove 31. Figure 5 , Figure 6 and Figure 7 As shown, the mounting buckle seat 2 is internally fixedly connected with two sets of sliding members 4, the connecting seat 22 is internally detachably connected with a locking assembly 5 for fixing the seat body 1, and the fixing seat 24 is internally connected with a fixing assembly 6 for limiting the movement of the seat body 1.

[0054] like Figure 8 As shown, the locking assembly 5 includes a threaded sleeve 51 and a rod assembly, wherein the rod assembly includes a rotating rod 52 and a locking block 57. The threaded sleeve 51 is threadedly connected to the inside of the connecting seat 22, and the rotating rod 52 is rotatably connected to the inside of the threaded sleeve 51. The upper surface of the rotating rod 52 is provided with a plug hole 521, and the outer side of the plug hole 521 is provided with four groups of vertical grooves 522 distributed in a cross shape. The inside of the plug hole 521 is slidably connected with a movable rod 53, as shown in FIG. Fig. 9As shown, a circular block 531 is fixedly connected to the upper surface of the movable rod 53, and a limiting rod 55 is fixedly connected to one side of the circular block 531. Four groups of vertical blocks 532 distributed in a cross are fixedly connected to the outer side of the movable rod 53. The four groups of vertical blocks 532 are respectively slidably connected to the inside of the vertical groove 522 on the corresponding side. The upper surface of the mounting buckle seat 2 and one side of the connecting seat 22 is fixedly connected to the limiting seat 23. The limiting seat 23 is provided with a limiting groove 231 for limiting the rotation of the limiting rod 55. The locking block 57 is fixedly connected to the lower end of the rotating rod 52 by a locking bolt 56. The thickness of the locking block 57 is consistent with the thickness of the sliding groove 31. Four groups of sliding holes 573 are provided inside the locking block 57. The upper and lower ends of the four groups of sliding holes 573 are penetrated by limiting holes 574. The diameter of the sliding hole 573 is larger than the diameter of the limiting hole 574. The inside of the four groups of sliding holes 573 is connected with an elastic limiting mechanism 58. Fig.10 and Fig.11 As shown, each group of elastic limiting mechanisms 58 includes a first spring 581, two placement rings 582 and two limiting balls 583. The first spring 581 is movably connected to the inside of the sliding hole 573. The two placement rings 582 respectively abut against the upper and lower ends of the first spring 581. The two limiting balls 583 are movably connected to the inside of the placement rings 582. The diameter of the limiting balls 583 is consistent with the size of the sliding hole 573. The edge of the limiting ball 583 away from the placement ring 582 abuts against the inner side of the limiting hole 574. Guide grooves 312 are provided on the upper and lower sides of the slide groove 31. The side of the limiting ball 583 away from the placement ring 582 abuts against the inside of the guide groove 312.

[0055] A threaded hole 241 is formed through the center of the upper surface of the fixing seat 24. The fixing assembly 6 includes a fixing bolt 61 and a limiting tooth seat 65. The fixing bolt 61 is threadedly connected to the inside of the threaded hole 241. Preferably, an anti-loosening assembly is also provided on the top of the fixing seat 24. Specifically, Fig.12 , Fig.13 and Fig.14 As shown, the anti-loosening assembly includes a limit plate 613, four groups of through holes 6131, four groups of mounting holes 243, a limit hemisphere 245 and a third spring 244. The limit plate 613 is fixedly connected to the outside of the fixing bolt 61 and located above the fixing seat 24. The upper surface of the limit plate 613 is equidistantly provided with four groups of through holes 6131. ​​The upper surface of the fixing seat 24 is equidistantly provided with four groups of mounting holes 243. The inside of the mounting hole 243 is fixedly connected with the third spring 244. The upper end of the third spring 244 is fixedly connected with the limit hemisphere 245. The limit hemisphere 245 elastically abuts against the inside of the through hole 6131. ​​The lower end of the fixing bolt 61 is rotatably connected with the mounting column 62. The outer side of the lower end of the mounting column 62 is fixed with a T-shaped block 64 through a connecting bolt 63. The limit tooth seat 65 is fixedly connected to the lower surface of the T-shaped block 64. The limit tooth seat 65 is matched and fixed with the long rack 311.

[0056] The present invention aims to simplify the installation process of aircraft seats. During installation, it is only necessary to insert the sliding member 4 into any position of the seat rail 3, and then push the seat body 1 to the desired position according to the installation spacing. Once the position of the seat body 1 is determined, the limit rod 55 is manually rotated to rotate it 90 degrees. In this process, the limit rod 55 drives the rotating rod 52 to rotate through the movable rod 53, and the rotating rod 52 drives the locking block 57 to rotate inside the slide groove 31. After rotating 90 degrees, the locking block 57 changes from longitudinal to transverse, so that it is firmly fixed inside the slide groove 31. At this time, the position of the seat body 1 is initially fixed.

[0057] During the rotation of the locking block 57, the limiting ball 583 is squeezed into the sliding hole 573, and the first spring 581 is compressed. When the locking block 57 is rotated to the right position, the limiting ball 583 is aligned with the guide groove 312. At this time, after the limiting ball 583 loses the squeezing force, the first spring 581 recovers its deformation, thereby applying elastic squeezing force to the limiting balls 583 at both ends, so that the limiting balls 583 abut against the inside of the guide groove 312, and the position of the locking block 57 is fixed.

[0058] Secondly, in the process of rotating the limit rod 55, it is necessary to pull the limit rod 55 upward to ensure that the limit rod 55 can pass over the limit seat 23. After the limit rod 55 is rotated into place, the position of the limit rod 55 is just parallel to the limit groove 231 on the limit seat 23. At this time, it is only necessary to press the limit rod 55 downward to fix it inside the limit groove 231, thereby performing a secondary fixation on the position of the locking block 57. At this time, the seat body 1 is firmly fixed above the seat slide rail 3 through the mounting buckle seat 2 connected thereto.

[0059] Finally, use a wrench to tighten the fixing bolt 61. During the process of rotating and descending, the fixing bolt 61 will indirectly drive the limiting tooth seat 65 to engage with the long rack 311. Once the limiting tooth seat 65 engages with the long rack 311, the seat body 1 cannot be pushed forward or backward.

[0060] In the process of using a wrench to rotate the fixing bolt 61, the limiting plate 613 and the limiting hemisphere 245 play an important role. When the fixing bolt 61 is rotated by the wrench, a through hole 6131 is opened on the surface of the limiting plate 613, and this through hole 6131 just corresponds to the limiting hemisphere 245 in the mounting hole 243. In the process of the fixing bolt 61 rotating, when the limiting tooth seat 65 is engaged with the long rack 311, the through hole 6131 on the limiting plate 613 will be aligned with the limiting hemisphere 245. At this time, the elastic force of the third spring 244 makes the limiting hemisphere 245 firmly squeezed inside the through hole 6131, thereby avoiding the loosening of the fixing bolt 61, effectively enhancing the stability of the seat body 1, not only simplifying the installation process, but also ensuring that the seat body 1 will not loosen due to vibration or other factors during the flight.

[0061] When wear occurs between the locking block 57 and the slide groove 31, resulting in dimensional inconsistency, the relative height of the locking block 57 and the mounting buckle seat 2 is changed by adjusting the position of the threaded sleeve 51, so that the upper surface of the locking block 57 in the horizontal state can always maintain abutment with the upper surface of the slide groove 31, ensuring the stability of the seat body 1 after installation.

[0062] The four groups of vertical blocks 532 are respectively slidably connected to the vertical slots 522 on the corresponding side. The advantage of this is that the movable rod 53 can slide up and down inside the insertion hole 521, but will not rotate relative to each other, thereby ensuring that when the limiting rod 55 is rotated, the limiting rod 55 can drive the rotating rod 52 to rotate through the movable rod 53.

[0063] Specifically, the left and right sides of the mounting buckle seat 2 are both fixedly connected with support blocks 21 , and the lower surface of the support block 21 abuts against the upper surface of the seat slide rail 3 .

[0064] The support block 21 is provided to increase the contact surface between the mounting buckle seat 2 and the seat slide rail 3, so that the contact between the mounting buckle seat 2 and the seat slide rail 3 is more uniform and stable. The increased contact area can disperse the pressure and load, reduce local stress concentration, thereby reducing structural stress, avoiding fatigue and damage caused by excessive stress, and extending the service life of the mounting buckle seat 2 and the seat slide rail 3.

[0065] Specifically, the sliding member 4 includes a mounting plate 41, two groups of side plates 42 and a rolling gear 43. The mounting plate 41 is fixed to the inner top wall of the mounting buckle 2 by bolts. The two groups of side plates 42 are respectively fixedly connected to the left and right sides of the mounting plate 41. The rolling gear 43 is rotatably connected between the two groups of side plates 42, and the rolling gear 43 is meshed on the long rack 311.

[0066] When installing the seat body 1, it is only necessary to place the rolling gear 43 inside the slide groove 31 so that it meshes with the long rack 311, making the process of installing the seat body 1 simpler and more intuitive. When the seat body 1 is pushed to move, the rolling gear 43 is indirectly driven to move on the long rack 311. Due to the design of the rolling gear 43, it can roll smoothly on the long rack 311, so that the movement of the seat body 1 is smoother and easier.

[0067] A hexagonal seat 511 is fixedly connected to the outer side of the threaded sleeve 51 .

[0068] When adjusting the position of the threaded sleeve 51 , the hexagonal seat 511 can be rotated by a wrench, thereby achieving the purpose of adjusting the position of the threaded sleeve 51 .

[0069] The lower end of the movable rod 53 is fixedly connected to a second spring 54 . The second spring 54 is located inside the insertion hole 521 , and the lower end of the second spring 54 is fixedly connected to the inner bottom wall of the insertion hole 521 .

[0070] When the limiting rod 55 is embedded in the limiting groove 231, the elastic tensile force of the second spring 54 can firmly and elastically fix the limiting rod 55 in the limiting groove 231 through the movable rod 53, thereby ensuring that the limiting rod 55 will not move due to external interference or vibration, and maintain the desired position or state, thereby ensuring that the position of the locking block 57 will not rotate by itself.

[0071] Specifically, both sides of the rotating rod 52 are fixedly connected with an insert block 524, a first movable hole 571 is provided on the upper surface of the mounting buckle seat 2, and slots 5711 are provided on both sides of the first movable hole 571. The insert block 524 is slidably connected to the inside of the slot 5711 on the corresponding side, and the lower end of the rotating rod 52 is inserted into the inside of the first movable hole 571. A first connecting hole 523 is penetrated through the lower end of one side of the rotating rod 52, and a first side hole 572 is penetrated through one side of the locking block 57. The first side hole 572 is connected to the first connecting hole 523, and the locking bolt 56 is threadedly penetrated through the first side hole 572 and the first connecting hole 523.

[0072] The rotating rod 52 and the locking block 57 are connected and fixed by the locking bolt 56, which is convenient for the subsequent maintenance and replacement of parts. Secondly, when inserting the rotating rod 52 into the first movable hole 571, the inserting block 524 can be aligned with the slot 5711, so that the rotating rod 52 and the locking block 57 can be quickly and accurately positioned, making the insertion of the locking bolt 56 easier.

[0073] like Fig.12 As shown, the lower end of the fixing bolt 61 is fixedly connected to a bottom column 611 , and the outer side of the bottom column 611 is rotatably connected to the inside of the mounting column 62 through a bearing 612 .

[0074] like Fig.13 and Fig.14 As shown, the bottom column 611 forms a rotating structure with the mounting column 62 through the bearing 612, and the mounting column 62 is fixedly connected to the T-block 64, which can ensure that when the fixing bolt 61 rotates in the threaded hole 241, it will not drive the mounting column 62 to rotate, but will only drive the mounting column 62 to move in the vertical direction, thereby indirectly achieving the purpose of adjusting the height of the T-block 64.

[0075] A second connecting hole 621 is formed at the lower outer end of the mounting column 62, a second movable hole 641 is formed on the upper surface of the T-block 64, second side holes 642 are formed at the front and rear sides of the T-block 64, the second side hole 642 penetrates the second movable hole 641, the lower end of the mounting column 62 is inserted into the second movable hole 641, and the connecting bolt 63 is threadedly penetrated into the second side hole 642 and the second movable hole 641.

[0076] The mounting column 62 and the T-block 64 are connected and fixed by connecting bolts 63 to facilitate subsequent maintenance and replacement of parts.

[0077] like Figure 6 As shown, two groups of side grooves 242 are provided on both sides of the interior of the mounting buckle seat 2, and two groups of side blocks 643 are fixedly connected to the left and right sides of the T-shaped block 64, and the side blocks 643 are slidably connected to the inside of the side groove 242 on the corresponding side.

[0078] When the fixing bolt 61 is rotated, the T-block 64 will be indirectly driven to move in the vertical direction. During the movement, the side block 643 will be driven to slide inside the side groove 242. The side groove 242 limits and positions the side block 643, ensuring that the side block 643 can move along the direction of the side groove 242.

[0079] In addition, according to an embodiment of the present invention, Figure 1 As shown, the aircraft seat can also be provided with a height-adjustable folding footrest 9. The user can adjust the position of the folding footrest 9 in the vertical direction as needed to meet the legroom requirements and improve the riding comfort.

[0080] The implementation of the present invention is not limited to the above-described embodiments, and can also be adjusted and optimized according to different design requirements and use environments. The protection scope of the present invention shall be based on the content of the claims, and is not limited to the above-described embodiments. Although the present invention has been described by specific embodiments, those skilled in the art, without departing from the spirit of the present invention, make various modifications, changes and combinations of the various embodiments and implementation methods of the present invention, which should be within the scope of the present invention.

Claims

1. An aircraft seat, comprising a seat body (1) and a mounting seat assembly, the mounting seat assembly comprising: A seat slide rail (3), wherein the seat slide rail (3) is provided with a slide groove (31) in a sliding direction; A mounting buckle seat (2), the mounting buckle seat (2) being connected to the lower end of the chair leg of the chair body (1), the mounting buckle seat (2) being provided with a support block (21) abutting against the upper surface of the chair slide rail (3) in the sliding direction, and the upper surface of the mounting buckle seat (2) being provided with a connecting seat (22) and a fixing seat (24); A locking assembly (5), the locking assembly (5) comprising a locking block (57) and a rod assembly, the lower end of the rod assembly being connected to the locking block (57); and A fixing assembly (6), wherein the fixing assembly (6) comprises a fixing bolt (61) and a limiting portion, wherein the lower end of the fixing bolt (61) is connected to the limiting portion, Wherein, the locking block (57) is installed in the slide groove (31) in a shape-fitting manner, the support block (21) abuts against the upper surface of the seat slide rail (3), the rod assembly passes through the connecting seat (22), the rod assembly can rotate in the connecting seat (22), and the fixing bolt (61) is screwed through the fixing seat (24) and abuts against the slide groove (31) through the limiting portion.

2. The aircraft seat according to claim 1, characterized in that: The locking assembly (5) further comprises at least two elastic limiting mechanisms (58), wherein the elastic limiting mechanisms (58) comprise: A sliding hole (573), the upper end of the sliding hole (573) abutting against the sliding groove (31); a first spring (581), the first spring (581) being disposed in the sliding hole (573); and two limiting balls (583), the limiting balls (583) being arranged at two ends of the first spring (581), The first spring (581) causes the two limiting balls (583) to abut against the slide groove (31); the two elastic limiting mechanisms (58) have a stroke in the vertical direction, are arranged in the locking block (57), and are respectively arranged on both sides of the locking block (57).

3. The aircraft seat according to claim 1, characterized in that: The locking assembly (5) further comprises a limiting rod (55), wherein the limiting rod (55) is used to operate and rotate the locking block (57) during installation and removal.

4. The aircraft seat according to claim 2, characterized in that: A guide groove (312) extending along the sliding direction is provided at the abutment portion between the slide groove (31) and the two limiting balls (583), and the limiting balls (583) abut against the guide groove (312).

5. The aircraft seat according to claim 1, characterized in that: A long rack (311) is arranged at the bottom of the slide groove (31) in the sliding direction, and a limiting tooth seat (65) is connected to the lower end of the limiting portion, and the limiting tooth seat (65) is meshed with the long rack (311).

6. The aircraft seat according to claim 5, characterized in that: A sliding member (4) is provided on the lower surface of the mounting buckle seat (2); the sliding member (4) can be implemented as a gear, and the gear is meshed with the long rack (311).

7. The aircraft seat according to claim 1, characterized in that: The rod assembly comprises a rotating rod (52) and a movable rod (53); the movable rod (53) is sleeved in the rotating rod (52); the movable rod (53) and the rotating rod (52) cannot rotate relative to each other; a second spring (54) is provided between the movable rod (53) and the rotating rod (52); two ends of the second spring (54) are respectively fixedly connected to the movable rod (53) and the rotating rod (52).

8. The aircraft seat according to claim 1, characterized in that: The locking assembly (5) further comprises a threaded sleeve (51), wherein the threaded sleeve (51) is screwed into the connecting seat (22), and the rod assembly is rotatably connected in the threaded sleeve (51).

9. The aircraft seat according to claim 1, characterized in that: An anti-loosening component is also provided on the top of the fixing seat (24) to prevent the fixing bolt (61) from loosening.

10. The aircraft seat according to claim 1, characterized in that The aircraft seat is also provided with a folding footrest (9), and the user can adjust the position of the folding footrest (9) in the vertical direction according to needs.

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