An aircraft seat provided with a roll-up energy absorber

Abstract

The application relates to the technical field of aviation seats, and discloses an aviation seat provided with a rolling energy absorber, which comprises a mounting seat, a supporting shaft is fixedly installed on the inner side of the rear end of the mounting seat, a seat cushion framework and a bracket are rotationally connected to the supporting shaft, a rolling elastic piece is arranged through the seat cushion framework, a rotation conversion piece is arranged between the seat cushion framework and the bracket, and a hydraulic energy absorbing piece is fixedly installed on the outer side of the rolling elastic piece. The driving shaft is driven to rotate the worm disc, drive the sliding block to move outward along the sliding groove, and drive the piston disc to slide in the hydraulic cylinder. In the same way, when the driving shaft is reversely rotated for resetting by the elastic driving of the coil spring, the reciprocating pushing piece pulls the piston rod inward, the hydraulic oil passes through the oil hole to apply friction to the hole wall of the oil hole, thereby applying opposite resistance to the piston disc, thereby inhibiting the rotation of the driving shaft, absorbing the energy of the vibration of the seat cushion framework relative to the bracket, and damping.

Description

Technical Field

[0001] This invention relates to the field of aircraft seat technology, specifically to an aircraft seat equipped with a retractable energy absorber. Background Technology

[0002] Aircraft seats are specialized equipment that meets aviation safety standards. Modern seats utilize lightweight composite materials and are ergonomically optimized to reduce passenger fatigue. Furthermore, to cope with turbulence during flight, aircraft seats incorporate shock-absorbing and energy-dampening structures inside, increasing vibration damping and enhancing seating comfort.

[0003] Chinese patent CN113562179B, filed on August 30, 2021, discloses a fall-resistant seat using a compression tube energy absorber. The seat includes a seat column, an upper crossbar, a lower crossbar, a compression tube, a seat plate assembly, and a compression seat assembly. The seat column serves as the main frame of the seat and is fixedly installed. The upper and lower crossbars are slidably fitted onto the seat columns on both sides at their ends. The compression tube is parallel to the seat column, with its upper and lower ends connected and fixed to the upper and lower crossbars, respectively. The seat plate assembly is fixedly mounted on the lower crossbar, and the compression seat assembly is fixedly mounted on the seat column. The compression seat assembly includes a pair of parallel compression rollers with a gap between them. The lower part of the compression tube has a narrowed, flattened section. The compression tube passes through the flattened section, passes down through the gap between the compression rollers, and is then secured to the compression rollers. During fall protection, the compression rollers roll and compress the compression tube from both sides. This invention has a simple structure, reduces the weight of the seat, has fewer parts, and high reliability. The parallel arrangement of the compression tube with the seat column ensures the effectiveness of the seat's fall-resistant energy absorption.

[0004] In this technical solution, in the event of a crash, the energy of the seat during descent can be absorbed by squeezing the extrusion tube with extrusion rollers; however, it is difficult to effectively reduce the high-frequency vibration of the seat when the aircraft is experiencing turbulence; moreover, the energy-absorbing structure requires a relatively long length to absorb energy, so the seat installation requires a large space, which allows for further improvements. Summary of the Invention

[0005] Technical problems to be solved

[0006] To address the shortcomings of existing technologies, this invention provides an aircraft seat equipped with a retractable energy absorber, which has the advantages of a small space occupied by the energy-absorbing structure and the ability to absorb and dampen high-frequency vibrations of the seat. It solves the problems of long energy-absorbing structures occupying a large space and being difficult to effectively absorb and dampen high-frequency vibrations of the seat.

[0007] Technical solution

[0008] To achieve the goal of minimizing the space occupied by the aforementioned energy-absorbing structure and effectively absorbing and damping high-frequency vibrations of the seat, this invention provides the following technical solution: An aircraft seat equipped with a retractable energy absorber, comprising a mounting base, two upwardly extending arms fixedly mounted at the rear end of the mounting base, a connecting shaft fixedly mounted between the top ends of the two extending arms, a backrest frame rotatably connected to the connecting shaft, a support shaft fixedly mounted on the inner side of the rear end of the mounting base, a seat cushion frame and a bracket rotatably connected to the support shaft, the bracket being located below the seat cushion frame, a retractable elastic element penetrating through the seat cushion frame, a rotating conversion element between the seat cushion frame and the bracket, a hydraulic energy-absorbing element fixedly mounted on the outer side of the retractable elastic element, and a lifting drive element between the bottom of the bracket and the mounting base.

[0009] Preferably, the retractable elastic element includes a drive shaft rotatably connected through the bracket, a covering cylinder is fixedly installed in the middle of the drive shaft, and a coil spring is fixedly installed on the outer wall of the covering cylinder; the hydraulic energy-absorbing element includes a sealing cover fixedly installed at the bottom of the bracket, a partition is fixedly installed in the middle of the sealing cover; the drive shaft is rotatably connected through the partition, and the end of the coil spring away from the covering cylinder is fixedly installed at the bottom of the partition.

[0010] Preferably, a hydraulic cylinder is fixedly arranged on the top of the partition, and a piston rod is slidably connected to one end of the hydraulic cylinder near the drive shaft. A piston disc is fixedly installed at one end of the piston rod inside the hydraulic cylinder. The hydraulic cylinder is filled with hydraulic oil, and an oil passage hole is provided on the piston disc. A reciprocating pusher is provided between the piston rod and the drive shaft.

[0011] Preferably, the oil passage includes an annular cavity formed inside the piston disc, and the piston disc has an array of through holes one on the side near the piston rod and an array of through holes two on the side away from the piston rod. Both through holes one and through holes two are connected to the annular cavity, and the number of through holes one and through holes two is equal. Each through hole one is located in the middle between two adjacent through holes two.

[0012] Preferably, flow-blocking blocks are arranged in an array on the inner wall of the annular cavity, with each flow-blocking block located in the middle between through hole one and through hole two.

[0013] Preferably, the reciprocating pusher includes a support cover fixedly installed at the bottom of the bracket, the bottom of the support cover having an array of grooves, a spiral disk rotatably connected inside the support cover, a drive shaft fixedly inserted through the center of the spiral disk, the drive shaft rotatably connected through the center of the support cover, a slider slidably connected inside the grooves, the slider being threadedly connected to the bottom of the spiral disk; the slider and the piston rod correspond one-to-one, and the slider and the piston rod are fixedly installed.

[0014] Preferably, the lower half of the sealing cover contains lubricating oil, and the edge of the partition has an array of through-holes for oil leakage. The piston disc has a circular oil delivery channel inside. The upper half of the drive shaft has a through-hole for spraying, which communicates with the oil delivery channel. The opening of the spray hole faces the gap between the bottom of the volute disc and the bottom wall of the support cover. A conveying shaft is rotatably connected inside the oil delivery channel. A spiral blade is fixedly installed on the surface of the conveying shaft and fits against the inner wall of the oil delivery channel. A reverse transmission component is provided between the bottom end of the conveying shaft and the bottom of the covering cylinder.

[0015] Preferably, the reverse transmission component includes an array of fixed rods fixed to the bottom of the covering cylinder, a ring gear fixedly installed at the bottom end of the fixed rod, a second gear meshing inside the ring gear, the second gear being rotatably connected to the bottom wall of the sealing cover, and a first gear fixedly installed at the bottom end of the conveying shaft, the first gear meshing with the second gear.

[0016] Preferably, the rotating conversion component includes two guide frames fixedly installed on the top of the bracket, with a sliding shaft inserted through the middle of the two guide frames. Two rollers are fixedly installed on the sliding shaft, and the rollers roll inside the guide frames. A push plate is hinged to the sliding shaft, and a crossbar is hinged to the top of the push plate. The crossbar is rotatably connected to the bottom of the seat cushion frame. A rack plate is rotatably connected to the sliding shaft, and the rack plate is slidably connected to the top of the bracket. A gear three is fixedly installed at the top of the drive shaft, and the rack plate meshes with the gear three.

[0017] Preferably, the lifting drive component includes a drive motor fixedly installed on the bottom wall of the mounting base, the output end of the drive motor is connected to a threaded rod, a U-shaped slide is threadedly connected to the threaded rod, the U-shaped slide is slidably connected to the bottom wall of the mounting base, and a support arm is hinged between the front end of the U-shaped slide and the bracket.

[0018] Compared with the prior art, the present invention provides an aircraft seat equipped with a retractable energy absorber, which has the following beneficial effects:

[0019] 1. This aircraft seat equipped with a retractable energy absorber uses a drive shaft to rotate a volute disk, which in turn moves a slider outward along a groove. This, combined with the connecting action of the piston rod, causes the piston disk to slide inside a hydraulic cylinder. Similarly, when the drive shaft is rotated in the opposite direction to reset via the elasticity of a coil spring, the reciprocating pusher pulls the piston rod inward, causing the piston disk to slide in the opposite direction inside the hydraulic cylinder. Hydraulic oil passing through the oil passage hole applies friction to the hole wall, thus creating a counterforce on the piston disk, thereby inhibiting the rotation of the drive shaft and absorbing the energy of the seat frame's vibration relative to the support frame, thus providing shock absorption.

[0020] 2. The aircraft seat equipped with a retractable energy absorber, when the drive shaft and the covering cylinder rotate, through the transmission action of the ring gear, gear one and gear two, drives the conveying shaft to rotate in the opposite direction, causing the lubricating oil in the lower half of the sealing cover to flow upward along the oil delivery channel. Then the lubricating oil is sprayed into the inside of the support cover through the spray hole, and lubricating oil is sprayed onto the support cover, the volute disc and the slider. After that, the lubricating oil falls to the surface of the partition and flows back into the lower half of the sealing cover through the oil leakage hole. Attached Figure Description

[0021] Figure 1 This is a three-dimensional structural diagram of an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0022] Figure 2 This is a three-dimensional exploded view of an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0023] Figure 3 This is a three-dimensional structural diagram of a rotating conversion component and a lifting drive component for an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0024] Figure 4 This is a three-dimensional structural diagram of a hydraulic energy-absorbing component for an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0025] Figure 5 This is a right-side cross-sectional view of a hydraulic energy-absorbing component for an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0026] Figure 6 This is a three-dimensional structural diagram of a reciprocating pusher and a retractable elastic member of an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0027] Figure 7 This is a three-dimensional cross-sectional schematic diagram of a retractable elastic element for an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0028] Figure 8 This is a bottom view of the retractable elastic element structure of an aircraft seat equipped with a retractable energy absorber, as proposed in this invention.

[0029] Figure 9 This is a three-dimensional structural diagram of the piston disc of an aircraft seat equipped with a retractable energy absorber, as shown in the front view of the present invention.

[0030] Figure 10 This is a three-dimensional structural diagram of the food tray of an aircraft seat equipped with a retractable energy absorber, as shown in the rear view of the present invention.

[0031] In the diagram: 100, mounting base; 200, backrest frame; 300, support shaft; 400, seat cushion frame; 500, bracket; 600, retractable elastic element; 700, rotation conversion element; 800, hydraulic energy-absorbing element; 900, lifting drive element;

[0032] 101. Extending arm; 102. Connecting shaft; 601. Drive shaft; 602. Covering cylinder; 603. Coil spring; 604. Conveying shaft; 605. Spiral blade; 606. Spray nozzle; 607. Fixing rod; 608. Ring gear; 609. Gear one; 610. Gear two;

[0033] 701. Guide frame; 702. Sliding shaft; 703. Roller; 704. Push plate; 705. Crossbar; 706. Rack plate; 707. Gear three;

[0034] 801. Sealing cover; 802. Partition plate; 803. Oil leakage hole; 804. Hydraulic cylinder; 805. Piston rod; 806. Piston disc; 807. Annular cavity; 808. Through hole one; 809. Through hole two; 810. Flow baffle; 811. Support cover; 812. Slide groove; 813. Scroll plate; 814. Sliding block;

[0035] 901. Drive motor; 902. Threaded rod; 903. U-shaped carriage; 904. Support arm. Detailed Implementation

[0036] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] Please see Figures 1-2 An aircraft seat equipped with a retractable energy absorber includes a mounting base 100. Two upwardly extending extension arms 101 are fixedly mounted at the rear end of the mounting base 100. A connecting shaft 102 is fixedly mounted between the top ends of the two extension arms 101. A backrest frame 200 is rotatably connected to the connecting shaft 102. An angle adjuster (not shown in the figure) is provided between the extension arms 101 and the backrest frame 200. The angle adjuster is based on prior art and will not be described further in this application.

[0038] A support shaft 300 is fixedly installed on the inner rear end of the mounting base 100. A seat cushion frame 400 and a bracket 500 are rotatably connected to the support shaft 300. The bracket 500 is located under the seat cushion frame 400. The support shaft 300 supports the seat cushion frame 400 and the bracket 500. The seat cushion frame 400 and the bracket 500 can rotate relative to each other to adjust the seat cushion tilt angle of the aviation seat. This, in conjunction with adjusting the tilt angle of the backrest frame 200, makes the passenger ride more comfortable. A retractable elastic element 600 is installed through the seat cushion frame 400. A rotation conversion element 700 is installed between the seat cushion frame 400 and the bracket 500. A hydraulic energy-absorbing element 800 is fixedly installed on the outside of the retractable elastic element 600. When the aircraft is in turbulence, the seat cushion frame 400 will vibrate at a high frequency relative to the bracket 500. Through the transmission action of the rotation conversion element 700, the retractable elastic element 600 is driven to rotate back and forth. Then, the hydraulic energy-absorbing element 800 absorbs energy and increases the resistance of the rotation of the retractable elastic element 600.

[0039] Please see Figure 3 A lifting drive component 900 is provided between the bottom of the bracket 500 and the mounting base 100. The lifting drive component 900 includes a drive motor 901 fixedly mounted on the bottom wall of the mounting base 100. The output end of the drive motor 901 is connected to a threaded rod 902, and a U-shaped slide 903 is threadedly connected to the threaded rod 902. The U-shaped slide 903 is slidably connected to the bottom wall of the mounting base 100, and a support arm 904 is hinged between the front end of the U-shaped slide 903 and the bracket 500. The drive motor 901 drives the threaded rod 902 to rotate, causing the U-shaped slide 903 to slide on the bottom wall of the mounting base 100. Combined with the connecting action of the support arm 904, this causes the bracket 500 to deflect relative to the support shaft 300, adjusting the tilt angle between the bracket 500 and the seat cushion frame 400.

[0040] Please see Figures 4-5 and Figure 8 The retractable elastic element 600 includes a drive shaft 601 that is rotatably connected to the bracket 500. A covering cylinder 602 is fixedly mounted in the middle of the drive shaft 601. The lower half of the drive shaft 601 passes through the center of the covering cylinder 602, and the bottom end of the drive shaft 601 is lower than the bottom end of the covering cylinder 602. A coil spring 603 is fixedly mounted on the outer wall of the covering cylinder 602.

[0041] The hydraulic energy-absorbing component 800 includes a sealing cover 801 fixedly installed at the bottom of the bracket 500, with a partition 802 fixedly installed in the middle of the sealing cover 801. A drive shaft 601 is rotatably connected to the partition 802, and a coil spring 603 is fixedly installed at its end away from the covering cylinder 602 at the bottom of the partition 802. When the seat cushion frame 400 deflects downward relative to the bracket 500, the drive shaft 601 and the covering cylinder 602 are rotated by the transmission action of the rotation conversion component 700, causing the coil spring 603 to twist. Then, under the elastic action of the coil spring 603, the drive shaft 601 and the covering cylinder 602 rotate in opposite directions, and in conjunction with the transmission action of the rotation conversion component 700, the seat cushion frame 400 deflects upward relative to the bracket 500 to return to its original position.

[0042] Please see Figure 3 The rotating conversion component 700 includes two guide frames 701 fixedly installed on the top of the bracket 500. A sliding shaft 702 is inserted through the middle of the two guide frames 701. Two rollers 703 are fixedly installed on the sliding shaft 702 and roll inside the guide frames 701. A push plate 704 is hinged to the sliding shaft 702, and a crossbar 705 is hinged to the top of the push plate 704. The crossbar 705 is rotatably connected to the bottom of the seat cushion frame 400. When the seat cushion frame 400 deflects downward relative to the bracket 500, the push plate 704 pushes the sliding shaft 702 forward, and the rollers 703 roll inside the guide frames 701.

[0043] A rack plate 706 is rotatably connected to the sliding shaft 702. The rack plate 706 is slidably connected to the top of the bracket 500. A gear 3 707 is fixedly installed at the top of the drive shaft 601. The rack plate 706 meshes with the gear 3 707. Pulling the rack plate 706 forward by the sliding shaft 702 drives the gear 3 707 and the drive shaft 601 to rotate.

[0044] Please see Figures 4-5A hydraulic cylinder 804 is fixedly arranged on the top of the partition plate 802. A piston rod 805 is slidably connected to one end of the hydraulic cylinder 804 near the drive shaft 601. A piston disc 806 is fixedly installed at one end of the piston rod 805 inside the hydraulic cylinder 804. The hydraulic cylinder 804 is filled with hydraulic oil. An oil passage hole is opened on the piston disc 806. A reciprocating pusher is provided between the piston rod 805 and the drive shaft 601. When the seat frame 400 deflects towards the bracket 500, causing the drive shaft 601 to rotate, the reciprocating pusher pushes the piston rod 805 outward, thereby causing the piston disc 806 to slide inside the hydraulic cylinder 804, and hydraulic oil flows through the oil passage hole. Similarly, when the drive shaft 601 is driven to rotate in the opposite direction to reset by the elasticity of the coil spring 603, the reciprocating pusher pulls the piston rod 805 inward, causing the piston disc 806 to slide inside the hydraulic cylinder 804, and hydraulic oil flows in the opposite direction through the oil passage hole. The hydraulic oil passing through the oil passage hole applies friction to the hole wall, thereby applying opposite resistance to the piston disc 806, thus suppressing the rotation of the drive shaft 601. This absorbs the energy of the vibration of the seat frame 400 relative to the bracket 500, thus providing shock absorption.

[0045] Please see Figures 9-10 The oil passage includes an annular cavity 807 inside the piston disc 806. The piston disc 806 has an array of through holes 1 808 on the side near the piston rod 805 and an array of through holes 2 809 on the side away from the piston rod 805. Both through holes 1 808 and through holes 2 809 are connected to the annular cavity 807. The number of through holes 1 808 and through holes 2 809 is equal, and each through hole 1 808 is located in the middle between two adjacent through holes 2 809. This causes the through hole 1 808 and through hole 2 809 to be staggered. When the hydraulic oil passes through through hole 1 808 into the annular cavity 807, it will not be discharged directly from through hole 2 809. Therefore, when the piston disc 806 slides inside the hydraulic cylinder 804, the hydraulic oil passing through through hole 1 808 into the annular cavity 807 will be divided into two parts and flow in the annular cavity 807 in clockwise and counterclockwise directions, respectively. After that, it will be discharged into the hydraulic cylinder 804 from the adjacent through hole 2 809.

[0046] Because a second through-hole 809 is located in the middle between two adjacent through-holes 808, convection occurs at the second through-hole 809 when the hydraulic oil flows inside the annular cavity 807, increasing the resistance of the hydraulic oil inside the annular cavity 807 and thus suppressing the sliding speed of the piston disc 806 inside the hydraulic cylinder 804. Flow-blocking blocks 810 are arrayed on the inner wall of the annular cavity 807, each located in the middle between the first through-hole 808 and the second through-hole 809. Each flow-blocking block 810 consists of two bosses with an isosceles trapezoidal cross-section, increasing the flow velocity of the hydraulic oil as it passes through the flow-blocking block 810. When convection occurs at the second through-hole 809, the impact force is greater. Similarly, when the hydraulic oil passes through the second through-hole 809 into the annular cavity 807, convection still occurs inside the annular cavity 807, and finally, the hydraulic oil is discharged from the first through-hole 808 into the hydraulic cylinder 804.

[0047] Please see Figure 6 The reciprocating actuator includes a support cover 811 fixedly installed at the bottom of the bracket 500. The bottom of the support cover 811 has an array of grooves 812. A spiral disc 813 is rotatably connected inside the support cover 811. A gap is reserved between the bottom of the spiral disc 813 and the bottom wall of the support cover 811. A drive shaft 601 is fixedly connected through the center of the spiral disc 813 and rotatably connected through the center of the support cover 811. A slider 814 is slidably connected within the grooves 812 and threadedly connected to the bottom of the spiral disc 813. The slider 814 corresponds one-to-one with the piston rod 805, and the slider 814 and piston rod 805 are fixedly installed. Thus, when the drive shaft 601 rotates, it drives the spiral disc 813 to rotate, causing the slider 814 to slide along the grooves 812. This, in conjunction with the piston rod 805, drives the piston disc 806 to slide within the hydraulic cylinder 804.

[0048] Please see Figures 5-7 The lower half of the sealing cover 801 contains lubricating oil. Oil leakage holes 803 are arrayed and penetrated along the edge of the partition 802. The piston disc 806 has a circular oil delivery channel inside. The upper half of the drive shaft 601 has a through-hole 606, which communicates with the oil delivery channel. The opening of the through-hole 606 faces the gap between the bottom of the spiral disc 813 and the bottom wall of the support cover 811. Thus, lubricating oil passes through the oil delivery channel and the through-hole 606 into the interior of the support cover 811, lubricating the spaces between the spiral disc 813 and the support cover 811, the slider 814 and the spiral disc 813, and the slider 814 and the groove 812.

[0049] A conveying shaft 604 is rotatably connected within the oil delivery channel. A spiral blade 605 is fixedly mounted on the surface of the conveying shaft 604, and the spiral blade 605 adheres to the inner wall of the oil delivery channel. A reverse transmission component is provided between the bottom end of the conveying shaft 604 and the bottom of the covering cylinder 602. Thus, when the drive shaft 601 and the covering cylinder 602 rotate, the reverse transmission component drives the conveying shaft 604 to rotate in the opposite direction, causing the lubricating oil inside the sealing cover 801 to flow upwards along the oil delivery channel and be sprayed into the support cover 811 through the spray nozzle 606.

[0050] The reverse transmission component includes fixed rods 607 arrayed and fixed to the bottom of the covering cylinder 602. A ring gear 608 is fixedly mounted at the bottom end of each fixed rod 607. A second gear 610 meshes with the inner side of the ring gear 608. The second gear 610 is rotatably connected to the bottom wall of the sealing cover 801. A first gear 609 is fixedly mounted at the bottom end of the conveying shaft 604, and the first gear 609 meshes with the second gear 610. Through the transmission action of the ring gear 608, the second gear 610, and the first gear 609, the rotation directions between the covering cylinder 602 and the conveying shaft 604 are reversed.

[0051] When in use, when the aircraft experiences turbulence during flight, the seat frame 400 deflects back and forth relative to the bracket 500. When the seat frame 400 deflects towards the bracket 500, the push plate 704 pushes the sliding shaft 702 forward, the sliding shaft 702 pulls the rack plate 706 forward, which drives the gear 707 and the drive shaft 601 to rotate, and the coil spring 603 twists to store elastic potential energy.

[0052] The drive shaft 601 drives the scroll plate 813 to rotate, which in turn drives the slider 814 to move outward along the slide groove 812. In conjunction with the connecting action of the piston rod 805, the piston plate 806 slides inside the hydraulic cylinder 804. Similarly, when the drive shaft 601 is driven to rotate in the opposite direction to reset by the elasticity of the coil spring 603, the piston rod 805 is pulled inward by the reciprocating pusher, and the piston plate 806 slides in the opposite direction inside the hydraulic cylinder 804.

[0053] When the piston disc 806 slides inside the hydraulic cylinder 804, the hydraulic oil enters the annular cavity 807 through the through hole 1 808 (or through hole 2 809), and the flow rate increases when passing through the flow block 810, forming convection inside the annular cavity 807. After that, it flows into the hydraulic cylinder 804 through the through hole 2 809 (or through hole 1 808).

[0054] Hydraulic oil passes through the oil passage and applies friction to the wall of the oil passage, thereby applying the opposite resistance to the piston disc 806, thus suppressing the rotation of the drive shaft 601 and absorbing the energy of the vibration of the seat frame 400 relative to the bracket 500, thus achieving shock absorption.

[0055] When the drive shaft 601 and the covering cylinder 602 rotate, the transmission action of the ring gear 608, gear one 609 and gear two 610 drives the conveying shaft 604 to rotate in the opposite direction, causing the lubricating oil in the lower half of the sealing cover 801 to flow upward along the oil delivery channel. Then the lubricating oil is sprayed into the inside of the support cover 811 through the spray hole 606, and lubricating oil is sprayed onto the support cover 811, the volute disk 813 and the slider 814. After that, the lubricating oil falls to the surface of the partition plate 802 and flows back into the lower half of the sealing cover 801 through the oil leakage hole 803.

[0056] Although embodiments of the 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 invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft seat equipped with a retractable energy absorber, comprising a mounting base (100), wherein two upwardly extending extension arms (101) are fixedly mounted at the rear end of the mounting base (100), a connecting shaft (102) is fixedly mounted between the top ends of the two extension arms (101), and a backrest frame (200) is rotatably connected to the connecting shaft (102), characterized in that: A support shaft (300) is fixedly installed on the inner rear end of the mounting base (100). A seat frame (400) and a bracket (500) are rotatably connected to the support shaft (300). The bracket (500) is located under the seat frame (400). A retractable elastic element (600) is provided through the seat frame (400). A rotating conversion element (700) is provided between the seat frame (400) and the bracket (500). A hydraulic energy-absorbing element (800) is fixedly installed on the outer side of the retractable elastic element (600). A lifting drive element (900) is provided between the bottom of the bracket (500) and the mounting base (100). The retractable elastic element (600) includes a drive shaft (601) that is rotatably connected to the bracket (500), a covering cylinder (602) is fixedly installed in the middle of the drive shaft (601), and a coil spring (603) is fixedly installed on the outer wall of the covering cylinder (602). The hydraulic energy-absorbing component (800) includes a sealing cover (801) fixedly installed at the bottom of the bracket (500), and a partition (802) is fixedly installed in the middle of the sealing cover (801). The drive shaft (601) is rotatably connected to the partition (802), and the end of the coil spring (603) away from the covering cylinder (602) is fixedly installed at the bottom of the partition (802); Hydraulic cylinders (804) are fixedly arranged on the top of the partition (802). A piston rod (805) is slidably connected to one end of the hydraulic cylinder (804) near the drive shaft (601). A piston disc (806) is fixedly installed at one end of the piston rod (805) inside the hydraulic cylinder (804). The hydraulic cylinder (804) is filled with hydraulic oil. An oil passage hole is opened on the piston disc (806). A reciprocating pusher is provided between the piston rod (805) and the drive shaft (601); The oil passage includes an annular cavity (807) formed inside the piston disc (806). The piston disc (806) has through holes one (808) arranged in an array on the side near the piston rod (805), and through holes two (809) arranged in an array on the side away from the piston rod (805). Both through holes one (808) and through holes two (809) are connected to the annular cavity (807). The number of through holes one (808) and through holes two (809) is equal, and each through hole one (808) is located in the middle between two adjacent through holes two (809). The annular cavity (807) is provided with an array of flow-blocking blocks (810) on its inner wall, and each flow-blocking block (810) is located in the middle between through hole one (808) and through hole two (809); The reciprocating pusher includes a cover (811) fixedly installed at the bottom of the bracket (500). The bottom of the cover (811) is provided with an array of grooves (812). A spiral disk (813) is rotatably connected inside the cover (811). The drive shaft (601) is fixed through the center of the spiral disk (813). The drive shaft (601) is rotatably connected through the center of the cover (811). A slider (814) is slidably connected inside the groove (812). The slider (814) is threadedly connected to the bottom of the spiral disk (813). The slider (814) corresponds one-to-one with the piston rod (805), and the slider (814) and piston rod (805) are fixedly installed; The rotating conversion component (700) includes two guide frames (701) fixedly installed on the top of the bracket (500). A sliding shaft (702) is inserted through the middle of the two guide frames (701). Two rollers (703) are fixedly installed on the sliding shaft (702). The rollers (703) roll inside the guide frames (701). A push plate (704) is hinged on the sliding shaft (702). A crossbar (705) is hinged to the top of the push plate (704). The crossbar (705) is rotatably connected to the bottom of the seat cushion frame (400). A rack plate (706) is rotatably connected to the sliding shaft (702). The rack plate (706) is slidably connected to the top of the bracket (500). A gear three (707) is fixedly installed at the top of the drive shaft (601). The rack plate (706) meshes with the gear three (707).

2. The aircraft seat equipped with a retractable energy absorber according to claim 1, characterized in that: The lower half of the sealing cover (801) contains lubricating oil, and the edge of the partition (802) is provided with an array of through-holes (803). The piston disc (806) has an oil delivery channel with a circular cross-section inside. The upper half of the drive shaft (601) is provided with a nozzle (606), which is connected to the oil delivery channel. The nozzle (606) opens towards the gap between the bottom of the vortex disk (813) and the bottom wall of the support cover (811). A conveying shaft (604) is rotatably connected inside the oil delivery channel. A spiral blade (605) is fixedly installed on the surface of the conveying shaft (604). The spiral blade (605) is attached to the inner wall of the oil delivery channel. A reverse transmission component is provided between the bottom end of the conveying shaft (604) and the bottom of the covering cylinder (602).

3. The aircraft seat equipped with a retractable energy absorber according to claim 2, characterized in that: The reverse transmission component includes a fixed rod (607) arrayed and fixed to the bottom of the covering cylinder (602). A ring gear (608) is fixedly installed at the bottom end of the fixed rod (607). A gear two (610) meshes with the inner side of the ring gear (608). The gear two (610) is rotatably connected to the bottom wall of the sealing cover (801). A gear one (609) is fixedly installed at the bottom end of the conveying shaft (604). The gear one (609) meshes with the gear two (610).

4. The aircraft seat equipped with a retractable energy absorber according to claim 1, characterized in that: The lifting drive component (900) includes a drive motor (901) fixedly installed on the bottom wall of the mounting base (100). The output end of the drive motor (901) is connected to a threaded rod (902). A U-shaped slide (903) is threadedly connected to the threaded rod (902). The U-shaped slide (903) is slidably connected to the bottom wall of the mounting base (100). A support arm (904) is hinged between the front end of the U-shaped slide (903) and the bracket (500).

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