A sightseeing aircraft seat disassembly and assembly device

Abstract

This utility model relates to the field of sightseeing aircraft seat disassembly and assembly technology, specifically a sightseeing aircraft seat disassembly and assembly device, including a seat body, a base frame, and disassembly components. During disassembly, simply move the limiting component to release the limiting plate lock, and the sliding column can be pulled upward along the sliding groove, simultaneously disengaging from the limiting groove. The disassembly time for a single seat is reduced from 20 minutes using traditional bolts to 10 seconds. During installation, the sliding column is inserted into the sliding groove, the limiting plate is rotated to make the limiting groove lock the sliding column, and then the limiting component is used to lock it. No screwdrivers or other tools are needed throughout the process, increasing installation efficiency by 90%. It is especially suitable for quick adjustments to seat layouts during flight intervals, such as switching between sightseeing seats and regular seats. The sliding columns and limiting plates on both sides of the seat adopt a symmetrical design, which can be operated simultaneously to achieve "one-click unlocking / locking," avoiding the tedious process of disassembling and assembling multiple bolts one by one. A single person can complete the seat disassembly and assembly, saving 50% of manpower compared to traditional two-person collaboration.

Description

Technical Field

[0001] This utility model relates to the field of sightseeing aircraft seat disassembly and assembly technology, specifically a sightseeing aircraft seat disassembly and assembly device. Background Technology

[0002] As is well known in the aviation operations sector, sightseeing aircraft require frequent seat disassembly and assembly to meet diverse cabin layout needs, such as temporarily adjusting seat spacing, increasing or decreasing the number of seats, and switching between business and leisure modes. This is a well-known practical requirement in the industry.

[0003] Existing sightseeing aircraft seats are generally fixed to the fuselage floor structure with bolts. A single set of seats requires 12-16 bolts for multi-point rigid connection. A single complete disassembly and assembly process, including disassembly, installation, and torque calibration, takes as long as 20-30 minutes. This inefficiency is particularly prominent in high-frequency modification scenarios. When the seat position needs to be adjusted frequently, the time-consuming disassembly and assembly process leads to wasted time. Summary of the Invention

[0004] Technical problems to be solved

[0005] To overcome the problem of long assembly and disassembly times in existing sightseeing aircraft seat disassembly and assembly devices, this utility model provides a sightseeing aircraft seat disassembly and assembly device that is easy to disassemble and assemble.

[0006] Technical solution

[0007] To achieve the above objectives, this utility model provides the following technical solution: a sightseeing aircraft seat disassembly and assembly device, comprising:

[0008] Seat body;

[0009] A base frame, which is detachably mounted at the bottom of the seat body; and

[0010] A disassembly assembly is mounted on the base frame. The disassembly assembly includes a sliding column, which is rotatably disposed on both sides of the seat body. Support plates are fixedly disposed on both sides of the base frame, and sliding grooves are formed on the support plates. The sliding column is slidably disposed with the sliding grooves. A rotation groove is formed on the side of the base frame, and a limit plate is rotatably disposed in the rotation groove. A limit groove is formed on the limit plate, and the limit groove is slidably disposed with the sliding column. A limit assembly is installed on the side of the base frame.

[0011] Preferably, the limiting component includes a sliding groove, which is formed on the side of the base frame. A sliding column is fixedly disposed in the sliding groove, and a slider is slidably disposed in the sliding groove. The slider is slidably disposed with the sliding column. A limiting rod is fixedly disposed on the top of the slider. A support block is fixedly disposed on the side of the base frame. A through hole adapted to the limiting rod is formed on the support block, and the limiting rod is slidably disposed with the through hole.

[0012] Furthermore, a first spring is fixedly installed inside the slide groove, the first spring is sleeved on the slide column, and the first spring is fixedly installed with the slider.

[0013] Furthermore, a pull plate is fixedly installed on the limiting rod.

[0014] In a further embodiment, a sleeve is fixedly installed around the bottom of the seat body, a sleeve rod is slidably installed inside the sleeve, the sleeve rod is rotatably installed with the sliding column, one end of a second spring is fixedly installed inside the sleeve, and the other end of the second spring is fixedly installed with the sleeve rod.

[0015] Based on the aforementioned scheme, several shock-absorbing dampers are fixedly arranged in a matrix on both sides of the top of the base frame, and a support plate is fixedly arranged between the top of the shock-absorbing dampers, with the top of the support plate fitting against the bottom of the sleeve rod.

[0016] Furthermore, based on the aforementioned scheme, a rotating shaft is rotatably provided on the side of the base frame, a gravity plate is fixedly provided at one end of the rotating shaft, the gravity plate is eccentrically provided with the rotating shaft, and a rotating rod is fixedly provided at the other end of the rotating shaft, the rotating rod being in contact with the bottom of the support plate.

[0017] Furthermore, based on the aforementioned solution, mounting plates are fixedly installed around the bottom perimeter of the base frame.

[0018] Beneficial effects

[0019] This sightseeing aircraft seat disassembly and assembly device allows for easy disassembly. Simply move the limiting component to release the limiting plate, and the sliding column can be pulled upwards along the sliding groove, simultaneously disengaging from the limiting groove. The disassembly time for a single seat is reduced from 20 minutes using traditional bolts to 10 seconds. During installation, the sliding column is inserted into the sliding groove, the limiting plate is rotated to lock the sliding column in place, and then the limiting component is used to lock it in place. No screwdrivers or other tools are required throughout the process, increasing installation efficiency by 90%. It is especially suitable for quick adjustments to seat layouts during flight intervals (such as switching between sightseeing seats and regular seats). The sliding columns and limiting plates on both sides of the seat are symmetrically designed and can be operated simultaneously to achieve "one-click unlocking / locking," avoiding the tedious process of disassembling and assembling multiple bolts one by one. A single person can complete the seat disassembly and assembly, saving 50% of manpower compared to traditional two-person collaboration. Attached Figure Description

[0020] Figure 1 This is a side view of the structure of this utility model;

[0021] Figure 2 This is a schematic diagram of the structure of the main body of the seat of this utility model;

[0022] Figure 3 This utility model Figure 2 A magnified schematic diagram of the local structure at point A;

[0023] Figure 4 This is a schematic diagram of the disassembly assembly of this utility model;

[0024] Figure 5 This utility model Figure 4 A magnified schematic diagram of the local structure at point B;

[0025] Figure 6 This is a schematic diagram of the structure of the base frame of this utility model;

[0026] Figure 7 This utility model Figure 6 A magnified schematic diagram of the structure at point C.

[0027] In the diagram: 1. Seat body; 2. Base frame; 3. Disassembly assembly; 4. Sliding column; 5. Support plate; 6. Sliding groove; 7. Rotating groove; 8. Limiting plate; 9. Limiting groove; 10. Limiting assembly; 11. Sliding groove; 12. Sliding column; 13. Sliding block; 14. Limiting rod; 15. Support block; 16. Through hole; 17. First spring; 18. Pull plate; 19. Sleeve; 20. Sleeve rod; 21. Second spring; 22. Shock absorption damping; 23. Support plate; 24. Rotating shaft; 25. Gravity plate; 26. Rotating rod; 27. Mounting plate. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0029] See Figures 1-7A sightseeing aircraft seat assembly and disassembly device, through the coordinated design of modular elastic connection and multiple mechanical locking, achieves efficient assembly and disassembly of the seat body 1 and the base frame 2. The core solution is as follows: the seat body 1 is vertically guided by the sliding column 4 and the sliding groove 6 of the support plate 5 of the base frame 2. After the limiting plate 8 rotates, it achieves horizontal locking through the "L"-shaped limiting groove 9. The spring-driven limiting rod 14 of the limiting component 10 is inserted into the through hole 16 of the support block 15 to form a secondary anti-misoperation protection. This device reduces the assembly and disassembly time of a single seat to less than 10 seconds, improves efficiency by 90% compared with traditional bolt connection, supports single-person operation, saves 50% of manpower, and at the same time reduces the energy of flight vibration transmitted to the seat by 60% through the gravity adaptive vibration reduction system, significantly improving passenger comfort.

[0030] First, refer to Figure 2 In this embodiment, the seat body 1 adopts an aerospace-grade aluminum alloy frame with an integrated honeycomb reinforcing rib structure inside. The surface is covered with leather that has passed FAR25.853 flame retardant certification. The bottom four corners are fixed with sleeves 19. The inner wall of the sleeves 19 is inlaid with self-lubricating copper sleeves. The sleeve rod 20 is rotatably connected to the sliding column 4 through a deep groove ball bearing. A compression spring is installed at the bottom of the sleeve 19, which provides an upward elastic force under normal conditions, so that the sliding column 4 maintains an upward trend in the unlocked state, which facilitates automatic disengagement from the limiting groove 9 during quick disassembly.

[0031] The chassis 2 is made of high-strength titanium alloy through laser additive manufacturing process. It has internally welded cross-shaped reinforcing plates and a surface coated with polytetrafluoroethylene anti-friction coating. The chassis 2 has positioning seats at the four corners and is rigidly connected to the aircraft floor structure through pre-embedded bolts. Silicone rubber dampers are arranged in a matrix on both sides of the top. The top of the dampers is fixed with curved support plates 23. The surface of the support plates 23 is micro-textured and forms flexible contact with the sleeve rod 20 at the bottom of the seat body 1 to absorb vertical and horizontal vibrations during flight.

[0032] Then, refer to Figure 3 In this embodiment, the sliding column 4 is a cylindrical structure, and the surface is formed with a uniform hard chrome layer by flash plating process, with a hardness of 900-1000 Vickers. The wear resistance is improved by 30% compared with traditional hard chrome plating. The base frame 2 is fixed with support plates 5 on both sides, and the support plates 5 have through sliding grooves 6. The inner wall of the groove is pasted with polyimide wear-resistant pads. The sliding column 4 and the pads are fitted with a gap to ensure smooth sliding and no metal friction noise.

[0033] The limiting plate 8 is injection molded from high-strength polypropylene composite material, with anti-slip textured surface. The base frame 2 has a dovetail-shaped rotating groove 7 on its side, with a self-lubricating bearing installed inside. The limiting plate 8 is fixed to the inner ring of the bearing by a pin and can rotate around a horizontal axis. The "L"-shaped limiting groove 9 on the limiting plate 8 is precisely matched with the annular groove in the middle of the sliding column 4. When the limiting plate 8 is rotated to the locked position, the bottom of the limiting groove 9 fits against the bottom surface of the groove in the sliding column 4, forming a mechanical rigid connection.

[0034] Secondly, see Figure 5 In this embodiment, a dovetail-shaped slide groove 11 is provided on the side of the base frame 2. A chrome-plated slide column 12 is fixed in the groove. The slider 13 is sleeved on the slide column 12 and can slide along the column. A spiral compression spring is installed at the bottom of the slide groove 11. Under normal conditions, it pushes the slider 13 to move upward. A guide boss is provided at the top of the slider 13, which cooperates with the limiting slot at the top of the slide groove 11 to prevent the slider 13 from falling out.

[0035] The top of the slider 13 is vertically fixed with a limiting rod 14. The rod body is made of 304 stainless steel with precision machining and nickel plating. The support block 15 is fixed to the side of the base frame 2. A stepped through hole 16 is opened in the middle. The hemispherical protrusion at the top of the limiting rod 14 cooperates with the conical concave surface in the through hole 16 to form a self-centering locking structure. The pull plate 18 adopts an ergonomic design and is covered with anti-slip rubber. It is hinged to the bottom of the limiting rod 14 through a pin. The lifting angle during operation conforms to human mechanics and the force is easy to apply.

[0036] See again Figure 7 In this embodiment, a gravity plate 25 is installed on the side of the base frame 2 via an eccentric rotating shaft 24. The two ends of the shaft are supported by double-row angular contact bearings. The gravity plate 25 is made of high-density lead alloy casting, and its center of gravity is offset from the rotating shaft 24 by a certain distance. A rotating rod 26 is fixed at the other end of the shaft. The rod has a hollow structure and is filled with viscoelastic damping material. When the aircraft accelerates or decelerates, the gravity plate 25 rotates around the shaft due to inertia. The rotating rod 26 pushes the support plate 23 to press down the damper, dynamically adjusting the damping stiffness. When flying at level, the gravity plate 25 returns to its original position, and the rotating rod 26 releases the support plate 23, restoring the initial damping state.

[0037] In addition, see Figure 2 In this embodiment, the rapid seat-changing operation process for high-density sightseeing flights is as follows: Flight attendants simultaneously lift the pull plate 18 with both hands, overcoming the spring force to disengage the limiting rod 14 from the through hole 16 of the support block 15, and simultaneously rotate the limiting plates 8 on both sides to the unlocked position (the limiting groove 9 is parallel to the axis of the sliding column 4). The seat body 1 is lifted upwards, and the sliding column 4 is pulled out along the sliding groove 6, simultaneously disengaging from the limiting groove 9. The disassembly of a single seat takes about 8 seconds. During installation, the seat body 1 is aligned with the support plate 5 of the base frame 2, the sliding column 4 is inserted into the sliding groove 6, the sleeve rod 20 compresses the spring to the position where the limiting plate 8 is rotated to trigger the rotation angle, the limiting plate 8 is rotated 90°, the limiting groove 9 locks the groove of the sliding column 4, the pull plate 18 is released, and the spring pushes the limiting rod 14 to automatically insert into the through hole 16 to complete the locking. The installation takes about 10 seconds. When the limiting plate 8 is rotated into place, the internal micro switch triggers the cabin control system, and the indicator light shows green. If the limiting rod 14 is not fully inserted, the system will sound a buzzer alarm to prevent the seat from becoming loose during flight.

[0038] To adapt to emergency seating changes in high-altitude and low-temperature environments, the silicone rubber damper of the underframe 2 has been replaced with a memory metal spring, which maintains stable elasticity within a temperature range of -40℃ to 80℃, ensuring that the vibration damping performance does not decrease in low-temperature environments. The hard chrome plating layer on the surface of the sliding column 4 has been changed to a low-temperature plating process, which improves the adhesion between the plating layer and the substrate and prevents low-temperature embrittlement. The surface of the gravity plate 25 is sprayed with an anti-icing coating to prevent icing from affecting inertial rotation in high-altitude environments. Fluorescent positioning marks are set on the edges of the support plate 5 of the underframe 2, which are clearly visible under the emergency lighting in the cabin, allowing the crew to quickly align the position of the sliding groove 6 in the dark.

[0039] Finally, see Figure 4 In this embodiment, the mechanical locking of the limiting rod 14 and the support block 15 is changed to electromagnetic adsorption, and the pull plate 18 is replaced with an electromagnetic switch. The cabin control system sends a command, the electromagnetic coil is energized to generate attraction, and the limiting rod 14 is adsorbed to the support block 15. When unlocking, the power is cut off and released, and the operation time is shortened to 5 seconds, which is suitable for regional sightseeing aircraft with high density layout.

[0040] The sliding column 4 has been changed to a three-stage telescopic structure with a built-in hydraulic buffer. When inserted into the sliding groove 6, the buffer automatically adjusts its stroke to avoid hard collisions and extend the life of the components. It is especially suitable for high-turnover flights with frequent disassembly and assembly.

[0041] The main frame of the seat is now made of carbon fiber composite material and filled with aluminum foam core material, reducing the weight by 30% while improving impact resistance. The vibration damping of the underframe 2 is now made of graphene-modified silicone rubber, which improves weather resistance by 2 times and adapts to the high salt spray environment of sightseeing aircraft at sea.

[0042] The surface of the sliding column 4 is coated with a self-healing coating. When microcracks appear in the coating, the microcapsules in the coating break and release the repair agent, which automatically fills the defects and extends the service life of the sliding column 4 to 3 times that of traditional hard chrome plating.

[0043] Working principle:

[0044] Before using the sightseeing aircraft seat removal and installation device, first release the limit lock:

[0045] Pull the pull plates 18 on both sides of the limit rod 14 with both hands to overcome the elastic force of the first spring 17, and pull the limit rod 14 out of the through hole 16 of the support block 15 to release the lock on the limit plate 8.

[0046] The limiting plate 8 loses its limit within the rotating groove 7 and can rotate freely.

[0047] Pull out sliding column 4:

[0048] Lift the seat body 1 upwards, and the sliding columns 4 on both sides slide upwards along the sliding groove 6 of the support plate 5, while disengaging from the limiting groove 9 of the limiting plate 8, thus separating the seat body 1 from the base frame 2. The entire disassembly process takes about 10 seconds and requires no tools.

[0049] Seat Quick Installation Process

[0050] Align and insert sliding bar 4:

[0051] Align the sliding post 4 at the bottom of the seat body 1 with the sliding groove 6 of the support plate 5 of the base frame 2, and insert it vertically downwards until the bottom of the sliding post 4 contacts the limiting groove 9 of the limiting plate 8.

[0052] Locking limit plate 8:

[0053] Rotate the two limiting plates 8 to make the limiting groove 9 lock the side of the sliding column 4, forming a circumferential lock.

[0054] When the pull plate 18 is released, the limiting rod 14 automatically inserts into the through hole 16 of the support block 15 under the action of the first spring 17, locking the position of the limiting plate 8 and preventing it from rotating.

[0055] Automatic shock absorption reset:

[0056] When the seat body 1 falls, the sleeve rod 20 compresses the second spring 21 inside the sleeve 19, the bottom support plate 23 contacts the shock-absorbing damper 22, the gravity plate 25 rotates eccentrically with the rotating shaft 24, and the rotating rod 26 pushes the support plate 23 to finely adjust its position, ensuring that the seat is placed smoothly without the need for torque calibration.

[0057] Elastic release during disassembly:

[0058] When the limit rod 14 is pulled, the first spring 17 is compressed and stored energy. After the sliding column 4 is pulled out, the second spring 21 between the sleeve 19 and the sleeve rod 20 of the seat body 1 extends, assisting the seat to quickly detach from the base frame 2.

[0059] Automatic locking during installation:

[0060] When the sliding column 4 is inserted into the sliding groove 6, the inclined surface of the limiting groove 9 of the limiting plate 8 guides the sliding column 4 to fall. After the limiting plate 8 is rotated, the limiting groove 9 and the slot of the sliding column 4 are precisely matched, and the limiting rod 14 is automatically inserted into the through hole 16 to complete the locking, forming a three-step quick installation of "insertion-rotation-locking".

[0061] High-frequency disassembly and assembly optimization

[0062] Efficient two-person collaborative operation (optional):

[0063] One person holds the main seat 1, while another person simultaneously pulls the side panels 18, which can further shorten the disassembly time to 5 seconds, suitable for emergency layout adjustments.

[0064] Gravity-assisted positioning:

[0065] The gravity plate 25 on the side of the base frame 2 is eccentrically set with the rotating shaft 24. When the seat is installed in place, the gravity plate 25 rotates due to its own weight, which drives the rotating rod 26 to lightly press the support plate 23, ensuring the seat is level and reducing subsequent fine-tuning procedures.

[0066] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A sightseeing aircraft seat disassembly and assembly device, characterized in that, include: Seat body (1); The base frame (2) is detachably mounted on the bottom of the seat body (1); as well as The disassembly assembly (3) is installed on the base frame (2). The disassembly assembly (3) includes a sliding column (4). The sliding column (4) is rotatably disposed on both sides of the seat body (1). Support plates (5) are fixedly disposed on both sides of the base frame (2). A sliding groove (6) is provided on the support plate (5). The sliding column (4) is slidably disposed with the sliding groove (6). A rotating groove (7) is provided on the side of the base frame (2). A limiting plate (8) is rotatably disposed in the rotating groove (7). A limiting groove (9) is provided on the limiting plate (8). The limiting groove (9) is slidably disposed with the sliding column (4). A limiting assembly (10) is installed on the side of the base frame (2).

2. The sightseeing airplane seat dismounting device according to claim 1, characterized by The limiting component (10) includes a slide groove (11), which is opened on the side of the base frame (2). A slide column (12) is fixedly installed in the slide groove (11), and a slider (13) is slidably installed in the slide groove (11). The slider (13) is slidably installed with the slide column (12). A limiting rod (14) is fixedly installed on the top of the slider (13). A support block (15) is fixedly installed on the side of the base frame (2). A through hole (16) adapted to the limiting rod (14) is opened on the support block (15), and the limiting rod (14) is slidably installed with the through hole (16).

3. The sightseeing airplane seat dismounting device according to claim 2, characterized by A first spring (17) is fixedly installed inside the slide groove (11). The first spring (17) is sleeved on the slide column (12). The first spring (17) is fixedly installed with the slider (13).

4. The sightseeing airplane seat dismounting device according to claim 3, characterized by A pull plate (18) is fixedly installed on the limiting rod (14).

5. The sightseeing airplane seat dismounting device according to claim 4, characterized by A sleeve (19) is fixedly installed around the bottom of the seat body (1). A sleeve rod (20) is slidably installed inside the sleeve (19). The sleeve rod (20) is rotatably installed with the sliding column (4). One end of a second spring (21) is fixedly installed inside the sleeve (19). The other end of the second spring (21) is fixedly installed with the sleeve rod (20).

6. The sightseeing airplane seat dismounting device according to claim 5, wherein The top two sides of the base frame (2) are fixedly provided with a number of shock-absorbing dampers (22) in a matrix. The top of the shock-absorbing dampers (22) is fixedly provided with a support plate (23). The top of the support plate (23) is in contact with the bottom of the sleeve rod (20).

7. The sightseeing airplane seat dismounting device according to claim 6, characterized by The base frame (2) is rotatably provided with a rotating shaft (24) on its side. A gravity plate (25) is fixedly provided at one end of the rotating shaft (24). The gravity plate (25) is eccentrically provided with the rotating shaft (24). A rotating rod (26) is fixedly provided at the other end of the rotating shaft (24). The rotating rod (26) is in contact with the bottom of the support plate (23).

8. The sightseeing airplane seat dismounting device according to claim 7, characterized by Mounting plates (27) are fixedly installed around the bottom of the base frame (2).

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