A composite energy-absorbing safety seat for fall protection

Abstract

This invention discloses a composite energy-absorbing safety seat for fall protection, comprising a seat body, a fixed support unit, a pull rod energy-absorbing unit, a switch unit, an electromagnetic energy-absorbing unit, and an aluminum honeycomb energy-absorbing unit. The electromagnetic energy-absorbing unit is installed between the seat and the body; the switch unit is installed beside the electromagnetic energy-absorbing unit; and the aluminum honeycomb energy-absorbing unit is installed on the upper side of the lower central frame. This invention achieves buffering and load reduction protection for the occupant by employing an integrated active and passive composite energy absorption method. The fixed support unit and switch unit serve as auxiliary energy-absorbing mechanisms, the passive energy absorption of the pull rod energy-absorbing unit and the aluminum honeycomb energy-absorbing unit serves as the main buffering energy absorption mechanism, and the active energy absorption of the electromagnetic energy-absorbing unit serves as the main electromagnetic buffering force control mechanism. The buffering force is adjusted according to the occupant's mass, reducing the peak occupant load, improving the robustness of the fall-resistant seat, and increasing the occupant survival rate in fall-affected conditions.

Description

Technical Field

[0001] This invention relates to the field of aircraft occupant safety protection technology, and in particular to a composite energy-absorbing safety seat for crash protection. Background Technology

[0002] In the field of occupant safety protection technology under aircraft crash conditions, the most effective method currently is to install specialized energy-absorbing safety seats that can eject occupants from the cockpit. Upon impact with the ground, various energy-absorbing components on the seat reduce the impact load transmitted to the occupant to a tolerable level. Common aircraft crashworthiness solutions often use two pillars behind the seat as a fixed base. The occupant seat can move relative to the pillars, while the energy-absorbing device is fixed at one end to the pillars and to the aircraft, and at the other end to the seat and to the occupant. When the seat moves relative to the pillars, the energy-absorbing device begins to absorb energy, adjusting the occupant load during the crash. To meet the 20g static load requirement for aircraft seats, the most common solution is to add two carbon fiber tubes between the pillars and the seat. During the crash, the carbon fiber tubes absorb energy and deform, adjusting the occupant load. However, this method has a long production cycle and is too expensive, hindering further large-scale production and use.

[0003] In the field of impact-response energy absorption, energy absorption methods can be categorized into passive, active, semi-active, and composite energy absorption, depending on whether external energy is required. Passive energy absorption is the most widely used, with relatively mature engineering technology, and has seen large-scale product applications in aviation, aerospace, and automotive fields. Active and semi-active energy absorption are relatively new and both require external energy input to achieve their buffering and energy absorption functions. Passive energy absorption methods offer high reliability and stability and have gained widespread industry recognition. However, their energy absorption capacity is entirely dependent on the energy absorption structure, requiring a complete structural change to adapt to different energy absorption scenarios. Furthermore, due to the relatively simple buffering process, the magnitude of the buffering force cannot be adjusted. While protecting occupant safety, this may harm occupant health and cannot meet the future occupant safety requirements of vehicle systems.

[0004] Active and semi-active energy absorption are relatively new energy absorption methods that can overcome the shortcomings of traditional passive energy absorption, such as poor environmental adaptability and uncontrollable buffering force. However, these methods have a large demand for external energy and encounter resistance in terms of weight and space when deployed locally, making them difficult to apply. At the same time, they place very high demands on the reliability of the active energy absorption control system. Once the system fails, the remaining structure has almost no buffering capacity, which may cause more serious consequences. Summary of the Invention

[0005] 1. Technical problems to be solved

[0006] The purpose of this invention is to solve the problems of existing active energy-absorbing safety seats having a large external energy requirement and encountering weight and space resistance when deployed locally, making them difficult to apply. Therefore, this invention proposes a composite energy-absorbing safety seat for crash protection.

[0007] 2. Technical Solution

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] A composite energy-absorbing safety seat for crash protection includes a seat body, a fixed support unit, a pull rod energy-absorbing unit, a switch unit, an electromagnetic energy-absorbing unit, and an aluminum honeycomb energy-absorbing unit. The pull rod energy-absorbing unit, electromagnetic energy-absorbing unit, and aluminum honeycomb energy-absorbing unit are installed between the seat body and the fixed support unit. The seat body is connected to the aircraft body via four movable bushings and is fixed with screws. One end of the pull rod energy-absorbing unit is installed below the suspension hinge of the fixed support unit, and the other end is installed on the energy-absorbing pull rod hinge and connected to the seat body, and fixed with screws. The switch unit and the electromagnetic energy-absorbing unit are both installed in the space below the intermediate frame. The switch unit is suspended below the intermediate frame, and one end of the electromagnetic energy-absorbing unit is suspended below the intermediate frame. The other end is connected to the seat body via the electromagnetic energy-absorbing unit hinge and fixed with screws. The aluminum honeycomb energy-absorbing unit is installed on the lower intermediate frame, connected to the seat body via the aluminum honeycomb bracket, and fixed with screws.

[0010] The fixed support unit includes a hanger, a guide rail, a movable bushing, and a central frame. The guide rail is connected to the aircraft cabin and is installed parallel and securely on the aircraft. The guide rails are connected to each other through the central frame to keep them in the same plane and parallel. The top of the guide rail is connected to the hanger and installed in the cavity of the hanger. The movable bushing is fixedly installed to the seat body and connected to the guide rail, allowing it to move up and down via the guide rail.

[0011] The energy-absorbing unit includes an inner cylinder of the energy-absorbing pull rod, an outer cylinder of the energy-absorbing pull rod, a hinge of the energy-absorbing pull rod, an annular aluminum honeycomb panel, and an energy-absorbing pull rod assembly. The upper end of the inner cylinder of the energy-absorbing pull rod is connected to the hanging hinge via the inner cylinder hinge, and the lower end of the outer cylinder of the energy-absorbing pull rod is connected to the energy-absorbing pull rod hinge via the outer cylinder hinge. The fixed mounting surface of the energy-absorbing pull rod hinge is installed on the seat body. The annular aluminum honeycomb panel is installed between the outer cylinder of the energy-absorbing pull rod and the inner cylinder of the energy-absorbing pull rod. The lower side of the upper end cover of the outer cylinder of the energy-absorbing pull rod is between the upper side of the lower bottom surface of the inner cylinder of the energy-absorbing pull rod. The energy-absorbing pull rod assembly is installed between the lower bottom surface of the inner cylinder of the energy-absorbing pull rod and the first layer panel of the outer cylinder of the energy-absorbing pull rod.

[0012] The switching unit comprises a power latch, a capacitor power supply, a switching circuit box, a trigger rod, and a guide rod limiter. The power latch is installed on the middle frame and is relatively fixed to the middle frame. The other end of the power latch is connected to the capacitor power supply. Two wires extend from the end of the capacitor power supply and are connected to the switching circuit box. Wires extend from the switching circuit box to form a circuit with the electromagnetic energy absorption unit. The trigger rod is installed on the guide rod limiter and extends into the lower hole of the switching circuit box. The guide rod limiter is fixedly connected to the seat body.

[0013] The electromagnetic energy absorption unit includes an outer cylinder suspension hinge, an inner cylinder of the electromagnetic energy absorption unit, an outer cylinder of the electromagnetic energy absorption unit, a lower hinge of the inner cylinder, and a hinge of the electromagnetic energy absorption unit. The outer cylinder suspension hinge is installed on the central frame. The inner cylinder and the outer cylinder of the electromagnetic energy absorption unit are connected by a central magnetic conductor, restricting their relative vertical movement to one dimension. The lower hinge of the outer cylinder is connected to the hinge of the electromagnetic energy absorption unit, thereby fixing the outer cylinder of the electromagnetic energy absorption unit to the seat body.

[0014] The aluminum honeycomb energy-absorbing unit includes an aluminum honeycomb bracket, an aluminum honeycomb, and an aluminum honeycomb hinge. The aluminum honeycomb bracket is installed on the back of the seat body and fixed to the seat body. The aluminum honeycomb is installed on the pressure-bearing surface of the bracket, and the other end is connected to the aluminum honeycomb hinge. One end of the aluminum honeycomb hinge is connected to the aluminum honeycomb, and the other end is connected to the lower middle frame. The aluminum honeycomb energy-absorbing unit contains two aluminum honeycombs. The one installed on the left side of the electromagnetic energy-absorbing unit is the left aluminum honeycomb, and the one installed on the right side of the electromagnetic energy-absorbing unit is the right aluminum honeycomb.

[0015] Preferably, the hanger includes a cavity fixed to the guide rail and a hinge connected to the pull rod energy absorption unit, serving to fix the guide rail and connect the pull rod energy absorption unit. The movable bushing includes a sleeve that cooperates with the guide rail and a bushing mounting plate fixed to the seat body. The middle frame includes a fixed cylinder connected to the guide rail and a truss connected between the fixed cylinders. The fixed support unit includes two middle frames, one installed between the four movable bushings on the guide rail and the other middle frame installed below the four movable bushings on the guide rail.

[0016] Preferably, the inner cylinder of the energy-absorbing pull rod includes an inner cylinder hinge, a limiting block, and a lower bottom surface of the inner cylinder. The inner cylinder hinge is connected to the hanging hinge. The lower bottom surface of the inner cylinder is connected to the energy-absorbing pull rod assembly and the annular aluminum honeycomb panel. The outer cylinder of the energy-absorbing pull rod includes an upper end cover, a first layer panel, a second layer panel, a third layer panel, and an outer cylinder hinge. The upper end cover and the limiting block are spaced a certain distance apart to prevent the energy-absorbing unit of the pull rod from being compressed. The outer cylinder hinge is connected to the energy-absorbing pull rod hinge. The energy-absorbing pull rod hinge includes an energy-absorbing pull rod hinge surface and a fixed mounting surface. The energy-absorbing pull rod hinge surface is connected to the outer cylinder hinge and remains relatively fixed to the outer cylinder. The fixed mounting surface is fixedly connected to the seat body. The annular aluminum honeycomb panel is a specially sized annular filled aluminum honeycomb panel designed according to the shape of the outer cylinder and the inner cylinder of the energy-absorbing pull rod.

[0017] Preferably, the energy-absorbing tie rod assembly is a buffer energy-absorbing structure composed of multiple tie rod assemblies evenly distributed on the circumference. The tie rod assembly includes a thick tie rod, a medium tie rod, and a thin tie rod. During the buffer energy absorption process, the thick tie rod first contacts the first layer panel of the outer cylinder, absorbs energy, and then breaks. The medium tie rod then contacts and stretches the second layer panel of the outer cylinder. After absorbing energy, the thin tie rod contacts and stretches the third layer panel of the outer cylinder, and the energy absorption process of the energy-absorbing tie rod assembly ends.

[0018] Preferably, the switch circuit box includes a negative wire, a switch circuit shell, a switch circuit hinge, a magnet, a positive wire, a magnetic chuck, and a magnetic stop. The positive and negative wires extend from the switch circuit shell and are connected to the electromagnetic energy absorption unit. The switch circuit hinge is located inside the switch circuit shell and is connected to the wire extending from the capacitor power supply. The magnetic chuck is connected to the switch circuit hinge and can rotate one-dimensionally around the switch circuit hinge. The magnet can attract and fix the magnetic chuck and fix the magnetic chuck under normal working conditions. The magnetic stop can fix the magnetic chuck during an impact.

[0019] Preferably, the trigger guide rod includes an insulated trigger head and a deformable straight rod. The insulated trigger head contacts the magnetic paddle, and its lower end is connected to the deformable straight rod. The insulated trigger head is insulated to prevent accidental activation and avoid the formation of an additional closed circuit. The deformable straight rod is an easily deformable straight rod that can withstand a small tensile force. After completing the triggering task, the deformable straight rod breaks under tensile force and separates from the insulated trigger head without hindering the operation of other parts of the system. The lower end of the deformable straight rod is connected to a guide rod limiter. The guide rod limiter includes a limiter fixing surface, a limiter plane, and a fixing post. The limiter fixing surface is installed on the seat body and fixed to the seat body. The limiter plane is perpendicular to the limiter fixing surface and is used to support the fixing post. The fixing post is located on the limiter plane and contacts and is fixed to the deformable straight rod.

[0020] Preferably, the inner cylinder of the electromagnetic energy absorption unit includes an inner cylinder support, an upper actuating coil, a lower actuating coil, and a brake. The inner cylinder support is located in the lower cavity of the inner cylinder and is used to fix the upper and lower actuating coils. The brake is installed at the bottom of the inner cylinder support. The outer cylinder of the electromagnetic energy absorption unit includes an end cap, a resistive energy absorption rod, an upper spring, a central magnetic conductor, an excitation coil, a lower spring, and the bottom surface of the inner cylinder. The end cap is installed on the upper side of the outer cylinder to assist the relative movement between the inner and outer cylinders. Three resistive energy absorption rods are installed at an angle inside the outer cylinder. One end of the upper spring is installed under the end cap, and the other end is suspended. The central magnetic conductor is installed in the middle. A common section is located between the inner and outer cylinders of the electromagnetic energy absorption unit. The excitation coil is fixed on the central magnetic conductor and is also within the common section. One end of the lower spring is fixed to the bottom surface of the inner cylinder.

[0021] Preferably, the aluminum honeycomb bracket includes a bracket mounting surface, a bracket reinforcing rib, and a bracket bearing surface. The bracket mounting surface is fixedly installed with the seat body, and the bracket reinforcing rib is obliquely fixed between the bracket mounting surface and the bracket bearing surface.

[0022] 3. Beneficial effects

[0023] Compared with the prior art, the advantages of this invention are:

[0024] (1) In this invention, the electromagnetic active module is used to achieve buffer control for occupants of different masses, reduce the peak load on the occupants during the crash, and achieve load force compliance control; the mechanical switch unit can buffer and absorb energy in staggered time with passive buffer structures such as the lever, and the mechanical structure can improve the robustness of the system, which is beneficial to the installation and deployment of the device.

[0025] (2) In this invention, the passive buffer energy absorption device includes aluminum honeycomb, tie rod, etc., which can quickly provide buffering in the initial stage of the crash. At the same time, when the electromagnetic buffer device fails, the passive buffer energy absorption device can still play a certain role in buffering and absorbing energy, thus improving the robustness of the system. Although the magnetic buffer unit requires external power supply, it can use a capacitor power supply, which is a fast and large discharge device, as an energy storage unit. It does not require additional power supply from the aircraft's electrical system and is not affected by the failure of the electromechanical system during the aircraft's runaway, thus increasing the reliability of the crash-resistant seat.

[0026] (3) In this invention, the safety seat is easy to process and install. Compared with traditional carbon fiber tubes, this device is simpler to process, and can achieve mass production of original parts, realizing large-scale manufacturing and installation; at the same time, the seat is simple to use. Before takeoff, the occupant only needs to install a capacitor power supply that matches his own weight on the back of the seat. During the crash, the electromagnetic system automatically enters the working state without any extra operation. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of a composite energy-absorbing safety seat for fall protection proposed in this invention;

[0028] Figure 2 This is a schematic diagram of a composite energy-absorbing safety seat for fall protection proposed in this invention;

[0029] Figure 3 This invention provides an overall assembly drawing and detailed drawings of some parts of a composite energy-absorbing safety seat fixing bracket unit for fall protection.

[0030] Figure 4 This invention provides an overall assembly drawing and a cross-sectional schematic diagram of a composite energy-absorbing safety seat pull rod energy-absorbing unit for fall impact protection.

[0031] Figure 5 The figures show a vertical and a horizontal cross-sectional view of a composite energy-absorbing safety seat energy-absorbing rod for fall impact protection proposed in this invention.

[0032] Figure 6 This invention provides an overall assembly drawing and a cross-sectional view of the switch circuit box for a composite energy-absorbing safety seat switch unit for fall protection.

[0033] Figure 7 This invention provides an assembly drawing and a cross-sectional view of an electromagnetic energy-absorbing unit for a composite energy-absorbing safety seat used for fall impact protection.

[0034] Figure 8 This invention presents an assembly drawing and detailed drawings of some parts of an aluminum honeycomb energy-absorbing unit for a composite energy-absorbing safety seat used for crash protection.

[0035] In the diagram: 1-Seat body, 11-Seat neck support, 12-Seat backrest, 13-Seat surface, 2-Fixed bracket unit, 21-Hanger, 211-Cavity, 212-Hanging hinge, 22-Guide rail, 23-Moving bushing, 231-Sleeve, 232-Busting plate, 24-Middle frame, 241-Fixed barrel, 242-Truss, 2411-Middle middle frame, 2412-Lower middle frame, 3-Tie rod energy absorption unit, 31-Energy-absorbing tie rod inner cylinder, 311-Inner cylinder hinge, 312-Limit stop, 313-Energy-absorbing tie rod inner cylinder 32-Outer cylinder of energy-absorbing tie rod, 321-Upper end cover of outer cylinder of energy-absorbing tie rod, 322-Third layer panel of outer cylinder, 323-Second layer panel of outer cylinder, 324-First layer panel of outer cylinder, 325-Outer cylinder hinge, 33-Hinge of energy-absorbing tie rod, 331-Hinge surface of energy-absorbing tie rod, 332-Fixed mounting surface, 34-Annular aluminum honeycomb panel, 35-Energy-absorbing tie rod assembly, 351-Thick tie rod, 352-Medium tie rod, 353-Thin tie rod, 4-Switch unit, 41-Power supply buckle, 42-Capacitor power supply, 43-Switch circuit box, 43 1-Negative wire, 432-Switch circuit housing, 433-Switch circuit hinge, 434-Magnet, 435-Positive wire, 436-Magnetic pull tab, 44-Trigger rod, 441-Insulated trigger head, 442-Deformation straight rod, 45-Guide rod limiter, 451-Limiter fixing plane, 452-Limiter plane, 453-Fixing column, 5-Electromagnetic energy absorption unit, 51-Inner cylinder hanging hinge, 52-Electromagnetic energy absorption unit inner cylinder, 521-Inner cylinder support, 522-Upper actuating coil, 523-Excitation coil, 524- 525-Bracing coil, 53-Outer cylinder of electromagnetic energy absorption unit, 531-End cap, 532-Energy dissipation guide rod, 533-Upper spring, 534-Central magnetic conductor, 535-Lower spring, 536-Bottom surface of inner cylinder, 54-Lower hinge of electric inner cylinder, 55-Hinge of electromagnetic energy absorption unit, 6-Aluminum honeycomb energy absorption unit, 61-Aluminum honeycomb bracket, 611-Bracket mounting surface, 612-Bracket reinforcing rib, 613-Bracket bearing surface, 6111-Left aluminum honeycomb, 6112-Right aluminum honeycomb, 62-Aluminum honeycomb, 63-Aluminum honeycomb hinge. Detailed Implementation

[0036] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0037] Example 1:

[0038] like Figure 1As shown, a composite energy-absorbing safety seat for fall protection includes a seat body 1, a fixed support unit 2, a pull rod energy-absorbing unit 3, a switch unit 4, an electromagnetic energy-absorbing unit 5, and an aluminum honeycomb energy-absorbing unit 6. The pull rod energy-absorbing unit 3, the electromagnetic energy-absorbing unit 5, and the aluminum honeycomb energy-absorbing unit 6 are installed between the seat body 1 and the fixed support unit 2 for buffering and absorbing energy during a fall.

[0039] In this invention, such as Figure 2 As shown, the seat body 1 is connected to the aircraft body via four movable bushings 23 and is fixed with screws. One end of the pull rod energy absorption unit 3 is installed below the hanging hinge 212 of the fixed bracket unit 2, and the other end is installed on the energy absorption pull rod hinge 33 and connected to the seat body 1, and is fixed with screws. The switch unit 4 and the electromagnetic energy absorption unit 5 are both installed in the space below the intermediate frame 2411. The switch unit 4 is suspended below the intermediate frame 2411, and one end of the electromagnetic energy absorption unit 5 is suspended below the intermediate frame 2411, and the other end is connected to the seat body 1 via the electromagnetic energy absorption unit hinge 55 and is fixed with screws. The aluminum honeycomb energy absorption unit 6 is installed on the lower intermediate frame 2412 and connected to the seat body 1 via the aluminum honeycomb bracket 61 and is fixed with screws.

[0040] In this invention, such as Figure 3 As shown, the fixed support unit 2 includes a suspender 21, a guide rail 22, a movable bushing 23, and a central frame 24. The guide rail 22 is connected to the aircraft cabin and is installed parallel and securely on the aircraft. The guide rails 22 are connected to each other through the central frame 24 to keep the guide rails 22 always in the same plane and parallel. The top of the guide rail 22 is connected to the suspender 21 and installed in the cavity 211 of the suspender 21. The movable bushing 23 is fixedly installed to the seat body 1 and connected to the guide rail 22, and can move up and down through the guide rail 22. The hanger 21 includes a cavity 211 that is fixed to the guide rail 22 and a hinge 212 that is connected to the tie rod energy absorption unit 3. It serves to fix the guide rail 22 and connect the tie rod energy absorption unit 3. The movable bushing 23 includes a sleeve 231 that cooperates with the guide rail 22 and a bushing mounting plate 232 that is fixed to the seat body 1. This ensures vertical freedom while the seat body 1 is connected to the guide rail 22. The middle frame 24 includes a fixed cylinder 241 that is connected to the guide rail 22 and a truss 242 that connects the fixed cylinders 241. The fixed cylinders 241 make the connection between the middle frame 24 and the guide rail 22 more secure. The truss 242 controls the position of the two fixed cylinders 241, thereby ensuring that the two guide rails 22 are parallel and coplanar, and at the same time providing a path for force transmission through the guide rails 22. The fixed support unit contains two intermediate frames 24. One is installed on the guide rail 22 between the four movable bushings 23 and is called the intermediate intermediate frame 2411. The other is installed on the guide rail 22 below the four movable bushings 23 and is called the lower intermediate frame 2412.

[0041] In this invention, such as Figure 4As shown, the energy-absorbing unit 3 includes an inner cylinder 31, an outer cylinder 32, a hinge 33, an annular aluminum honeycomb panel 34, and an energy-absorbing rod assembly 35. The upper end of the inner cylinder 31 is connected to the suspension hinge 212 via the inner cylinder hinge 311 to secure it to the aircraft. The lower end of the outer cylinder 32 is connected to the hinge 33 via the outer cylinder hinge 325. The outer cylinder 32 is mounted on the seat body 1 via the mounting surface 332 of the hinge 33 to secure it to the seat body 1. An annular aluminum honeycomb panel 34 is installed between the outer cylinder 32 and the inner cylinder 31 of the energy-absorbing tie rod, specifically inside the cavity on the inner side of the outer cylinder 32 and the outer side of the inner cylinder 31, between the lower side of the upper end cap 321 of the outer cylinder and the upper side of the lower bottom surface 313 of the inner cylinder. An energy-absorbing tie rod assembly 35 is installed between the lower bottom surface 313 of the inner cylinder and the first layer panel 324 of the outer cylinder. The annular aluminum honeycomb panel 34 and the energy-absorbing tie rod assembly 35 work together to buffer and absorb energy during the impact.

[0042] In this invention, such as Figure 5 As shown, the inner cylinder 31 of the energy-absorbing tie rod includes an inner cylinder hinge 311, a limiting block 312, and a lower bottom surface 313 of the inner cylinder. The inner cylinder hinge 311 is connected to the lifting hinge 212, so that the inner cylinder 31 of the energy-absorbing tie rod is fixed to the aircraft cabin. The lower bottom surface 313 of the inner cylinder is connected to the energy-absorbing tie rod assembly 35 and the annular aluminum honeycomb panel 34, providing a stress point. The outer cylinder 32 of the energy-absorbing tie rod includes an upper end cap 321, a first layer panel 324, a second layer panel 323, a third layer panel 322, and an outer cylinder hinge 325. The upper end cap 321 of the outer cylinder is spaced a certain distance from the limiting block 312 to prevent the tie rod energy-absorbing unit 3 from being compressed. Panel 324, outer cylinder second layer panel 323, and outer cylinder third layer panel 322 are the main load-bearing panels during the stretching process of the energy-absorbing tie rod assembly 35. The outer cylinder hinge 325 is connected to the energy-absorbing tie rod hinge 33. The energy-absorbing tie rod hinge 33 includes an energy-absorbing tie rod hinge surface 331 and a fixed mounting surface 332. The energy-absorbing tie rod hinge surface 331 is connected to the outer cylinder hinge 325 and is relatively fixed to the energy-absorbing tie rod outer cylinder 32. The fixed mounting surface 332 is fixedly connected to the seat body 1 to realize the force transmission between the energy-absorbing tie rod outer cylinder 32 and the seat body 1. The annular aluminum honeycomb panel 34 is a special-sized annular filled aluminum honeycomb panel designed according to the shape of the energy-absorbing tie rod outer cylinder 32 and the energy-absorbing tie rod inner cylinder 31.

[0043] In this invention, such as Figure 5As shown, the energy-absorbing tie rod assembly 35 is a buffer energy-absorbing structure composed of multiple tie rod assemblies evenly distributed on the circumference. The tie rod assembly includes a thick tie rod 351, a medium tie rod 352, and a thin tie rod 353. During the buffer energy absorption process, the thick tie rod 351 first contacts the first layer panel 324 of the outer cylinder, and after absorbing energy, it breaks through the contact of the medium tie rod 352 and the second layer panel 323 of the outer cylinder. After absorbing energy through the contact of the thin tie rod 353 and the third layer panel 322 of the outer cylinder, the energy absorption process of the energy-absorbing tie rod assembly 35 ends.

[0044] In this invention, such as Figure 6 As shown, the switch unit 4 comprises a power latch 41, a capacitor power supply 42, a switch circuit box 43, a trigger rod 44, and a guide rod limiter 45. The power latch 41 is installed on the intermediate frame 2411 and is relatively fixed to the intermediate frame 2411. The other end of the power latch 41 is connected to the capacitor power supply 42. Two wires extend from the end of the capacitor power supply 42 and are connected to the switch circuit box 43. Wires extend from the switch circuit box 43 and form a circuit with the electromagnetic energy absorption unit 5. The trigger rod 44 is installed on the guide rod limiter 45 and extends into the switch circuit box 43 from the lower hole. The guide rod limiter 45 is fixedly connected to the seat body 1. When a fall occurs, the seat body 1 moves the guide rod limiter 45, triggering the switch circuit box 43 to form a closed circuit, adjusting the electromagnetic damping magnitude to achieve buffer energy absorption.

[0045] In this invention, the switch circuit box 43 includes a negative electrode wire 431, a switch circuit shell 432, a switch circuit hinge 433, a magnet 434, a positive electrode wire 435, a magnetic pluck 436, and a magnetic stop block 437. The positive electrode wire 435 and the negative electrode wire 431 extend from the switch circuit shell 432 and are connected to the electromagnetic energy absorption unit 5. The switch circuit hinge 433 is located inside the switch circuit shell 432 and is connected to the wire extending from the capacitor power supply 42. The magnetic pluck 436 is connected to the switch circuit hinge 433 and can rotate one-dimensionally around the switch circuit hinge 433. The magnet 434 can attract and fix the magnetic pluck 436 and fix the magnetic pluck 436 under normal working conditions. The magnetic stop block 437 can fix the magnetic pluck 436 during a fall.

[0046] In this invention, such as Figure 6Section C indicates that the trigger rod 44 includes an insulated trigger head 441 and a deformable straight rod 442. The insulated trigger head 441 is in contact with the magnetic pawl 436, and its lower end is connected to the deformable straight rod 442. The insulated trigger head 441 uses an insulated head to prevent accidental triggering and avoid the formation of an additional closed circuit. The deformable straight rod 442 is a freely deformable straight rod that can withstand a small tensile force. After completing the triggering task, the deformable straight rod 442 breaks under tensile force and separates from the insulated trigger head 441, without hindering the operation of other parts of the system. The lower end of the deformable straight rod 442 is connected to the guide rod limiter 45. The guide rod limiter 45 includes a limiter fixing surface 451, a limiter plane 452, and a fixing post 453. The limiter fixing surface 451 is installed on the seat body 1 and fixed to the seat body 1. The limiter plane 452 is perpendicular to the limiter fixing surface 451 and is used to support the fixing post 453. The fixing post 453 is located on the limiter plane 452 and contacts the deformable straight rod 442 and is fixed to the deformable straight rod 442.

[0047] In this invention, such as Figure 7 As shown, the electromagnetic energy absorption unit 5 includes an outer cylinder suspension hinge 51, an inner cylinder 52, an outer cylinder 53, a lower inner cylinder hinge 54, and a hinge 55. The outer cylinder suspension hinge 51 is mounted on the intermediate frame 2411. The inner cylinder 52 and the outer cylinder 53 are connected by a central magnetic conductor 534, restricting their movement to one-dimensional relative vertical motion. The lower outer cylinder hinge 54 is connected to the hinge 55, and the outer cylinder 53 is fixed to the seat body 1 via the electromagnetic energy absorption unit 5. The inner cylinder 52 includes an inner cylinder support 521, an upper actuation coil 522, a lower actuation coil 523, and a brake 524. The inner cylinder support 521 is located in the lower cavity of the inner cylinder 52 and is used to fix the upper actuation coil 522 and the lower actuation coil 523. The brake 524 is mounted on the bottom of the inner cylinder support 521. The outer cylinder of the electromagnetic energy absorption unit includes an end cap 531, a resistance energy absorption rod 532, an upper spring 533, a central magnetic conductor 534, an excitation coil 535, a lower spring 536, and an inner cylinder bottom surface 537. The end cap 531 is installed on the upper side of the outer cylinder 53 of the electromagnetic energy absorption unit to assist the relative movement between the inner cylinder 52 and the outer cylinder 53 of the electromagnetic energy absorption unit. The resistance energy absorption rod 532 is installed inside the outer cylinder 53 of the electromagnetic energy absorption unit at a 120° angle, with a total of three rods. One end of the upper spring 533 is installed under the end cap 531, and the other end is suspended. The central magnetic conductor 534 is installed in the middle, with a common section between the inner cylinder 52 and the outer cylinder 53 of the electromagnetic energy absorption unit. The excitation coil 535 is fixed on the central magnetic conductor 534 and is also within the common section. One end of the lower spring 536 is fixed on the inner cylinder bottom surface 537.

[0048] In this invention, such as Figure 8As shown, the aluminum honeycomb energy-absorbing unit 6 includes an aluminum honeycomb bracket 61, aluminum honeycomb 62, and aluminum honeycomb hinge 63. The aluminum honeycomb bracket 61 is installed on the back of the seat body 1 and fixed to the seat body 1. The aluminum honeycomb 62 is installed on the bracket's pressure-bearing surface 613, and its other end is connected to the aluminum honeycomb hinge 63. One end of the aluminum honeycomb hinge 63 is connected to the aluminum honeycomb 62, and the other end is connected to the lower middle frame 2412. The aluminum honeycomb energy-absorbing unit 6 contains two aluminum honeycombs 62. The one installed on the left side of the electromagnetic energy-absorbing unit 5 is the left aluminum honeycomb 6111, and the one installed on the right side of the electromagnetic energy-absorbing unit 5 is the right aluminum honeycomb 6112. The two work together to assist in buffering and absorbing energy. The aluminum honeycomb bracket 61 includes a bracket mounting surface 611, a bracket reinforcing rib 612, and a bracket pressure-bearing surface 613. The bracket mounting surface 611 is fixedly installed to the seat body 1. The bracket reinforcing rib 612 is inclined and fixed between the bracket mounting surface 611 and the bracket pressure-bearing surface 613, transmitting the pressure generated during the compression and energy absorption process of the aluminum honeycomb 62 to the seat body 1.

[0049] In this invention, the specific buffering and energy absorption process of a composite energy-absorbing safety seat for crash protection is as follows: The main function of the composite energy-absorbing safety seat is that during a crash, the aircraft body and the occupant fall together, and the speed of the fixed support unit 2, which is fixed to the aircraft body, drops rapidly to 0. The fixed support unit 2 and the seat body 1 undergo relative displacement, and the pull rod energy-absorbing unit 3 and the aluminum honeycomb energy-absorbing unit 6 generate passive buffering force. Subsequently, the switching unit 4 is turned on, and the electromagnetic energy-absorbing unit 5 works to form instantaneous electromagnetic damping. The pull rod energy-absorbing unit 3, the aluminum honeycomb energy-absorbing unit 6 and the electromagnetic energy-absorbing unit 5 together provide buffering force and adjust the magnitude of the load force borne by the occupant during the crash.

[0050] In this invention, the switching unit path is formed as follows: During the impact, a relative displacement occurs between the seat body 1 and the fixed support unit 2. At this time, the guide rod limiter 45 fixed to the seat body 1 and the switch circuit shell 432 connected to the intermediate frame 2411 undergo the same relative displacement. The insulating trigger head 441, which is stuck in the groove in the middle of the magnetic pluck 436, pulls the magnetic pluck 436 downward, contacts the magnetic stop block 437 and firmly attracts the magnetic pluck 436, so that the capacitor power supply 42 is connected to the positive wire 435, forming a closed path.

[0051] In this invention, the specific adjustment method of the electromagnetic energy absorption unit 5 is as follows: by means of impact simulation and impact test, the optimal damping curve of the load borne by the occupants of different masses under the action of the same set of buffer devices is obtained, and the electromagnetic damping range suitable for occupants of different mass ranges is found, thereby solving the required amount of capacitor power supply 42. In actual use, the occupants select capacitor power supply 42 with different amounts of power according to their own weight range and make corresponding replacements.

[0052] In this invention, the specific method for replacing the capacitor power supply 422 is as follows: different specifications of capacitor power supplies 42 are made into cylindrical shapes of the same size and are connected to the power supply buckle 41 by friction. Before takeoff, the occupants install a fully charged capacitor power supply 42 that matches their own weight onto the power supply buckle 41 and fix it to the power supply buckle 41 by friction. One end of the capacitor power supply 42 is connected to the negative wire 431 and the other end is connected to the switch circuit hinge 433 to ensure that a closed loop can be formed between the capacitor power supply 42 and the electromagnetic energy absorption unit 5 during the crash.

[0053] In this invention, the main functions of the fixed support unit 2 are: to fix it to the aircraft cabin, to fix the seat body 1 while ensuring the vertical degree of freedom, to provide a mounting fulcrum for the pull rod energy absorption unit 3, the electromagnetic energy absorption unit 5 and the aluminum honeycomb energy absorption unit 6 in the device, and to provide a force transmission path for the pull rod energy absorption unit 3, the electromagnetic energy absorption unit 5 and the aluminum honeycomb energy absorption unit 6.

[0054] In this invention, the main function of the pull rod energy absorption unit 3 is to provide buffering and energy absorption during the impact process. By adjusting the thickness of the thick pull rod 351, the medium pull rod 352 and the thin pull rod 353 in the energy absorption pull rod group 35 and the distribution of the annular honeycomb plate 34, the magnitude of the buffering force during the buffering and energy absorption process is controlled, thereby reducing the peak impact value.

[0055] In this invention, the specific buffering and energy absorption process of the energy-absorbing tie rod assembly 35 is as follows: In the initial state, the inner cylinder 31 of the energy-absorbing tie rod assembly is fixed to the fixed support unit 2 and is rigidly connected to the body itself. The outer cylinder 32 of the energy-absorbing tie rod is connected to the seat body 2 through the energy-absorbing tie rod hinge 33 and is installed with screws to achieve a rigid connection with the occupant. During the crash, the occupant and the aircraft body move relative to each other. The annular aluminum honeycomb plate 34 located between the upper end cover 321 of the outer cylinder and the lower bottom surface 313 of the inner cylinder is compressed and absorbs energy, providing buffering force. The coarse tie rod 351 located between the lower bottom surface 313 of the inner cylinder and the first layer panel 324 of the outer cylinder bears the tension first and provides a larger buffering force. After deforming to a certain length, the coarse tie rod 351 is stretched. The buffering force provided by rod 351 gradually decreases. The end of the middle tie rod 352 contacts the second layer panel 323 of the outer cylinder, and the middle tie rod 352 deforms and elongates, providing a medium-sized buffering force. The buffering force provided by the middle tie rod 352 gradually decreases. The end of the thin tie rod 353 contacts the third layer panel 322 of the outer cylinder, and the thin tie rod 353 elongates under force, providing a buffering force. Subsequently, the energy-absorbing tie rod assembly 35 elongates and breaks, no longer providing a buffering force. The annular aluminum honeycomb panel 34 is continuously compressed throughout the process, always providing a buffering force. The tie rod energy-absorbing unit 3, through the cooperation of the energy-absorbing tie rod assembly 35 and the annular aluminum honeycomb panel 34, provides multi-stage buffering and energy absorption, adjusting the occupant load and ensuring the safety of the occupants.

[0056] In this invention, the function of the switching unit is to form a closed loop with the electromagnetic energy absorption unit 5 during the impact process, provide it with electrical energy to generate electromagnetic damping, and control the circuit switch in a mechanical manner.

[0057] In this invention, the working process of the electromagnetic energy absorption unit 5 is as follows: During the impact, the switch unit 4 is energized, causing the upper actuating coil 522 and the lower actuating coil 523 of the electromagnetic energy absorption unit 5 to simultaneously receive currents of the same magnitude and direction. An instantaneous electromagnetic field is formed between the upper actuating coil 522 and the lower actuating coil 523. At this time, the inner cylinder 52 and the outer cylinder 53 of the electromagnetic energy absorption unit undergo relative displacement. One end of the excitation coil 535 is wound around the central magnetic conductor 534, and the other end is connected in parallel with three resistive energy absorption rods to form a closed loop. The closed loop of the excitation coil cuts the electromagnetic field lines to generate current. The resistive energy absorption rods are used to convert the mechanical energy of the relative motion into internal energy, thereby realizing the buffering energy absorption process. During this process, the closed loop cuts the magnetic field lines to generate electromagnetic damping force. This damping force is related to the magnitude of the current and the relative motion speed. The electromagnetic damping force can be controlled by controlling the magnitude of the current. After the impact process is completed, the upper spring is compressed and stores a certain amount of elastic potential energy. At this time, the brake is activated, clamping and locking the inner cylinder of the electromagnetic energy absorption unit with the central magnetic conductor through friction, preventing the upper spring from rebounding.

[0058] In this invention, the function of the aluminum honeycomb energy absorption unit 6 is: during the impact, the aluminum honeycomb 62 compresses and absorbs energy, and transmits the compressive force to the seat body 1 through the aluminum honeycomb bracket 61 along the force transmission path of the bracket bearing surface 613, the bracket reinforcing rib 612 and the bracket mounting surface 611, thereby regulating the impact force borne by the seat body 1 during the impact and weakening the peak impact.

[0059] In this invention, the working process of the switch unit 4 is as follows: During the crash, the seat body 1 drives the guide rod limiter 45 to move relative to the aircraft cabin. The guide rod limiter 45 pushes the trigger guide rod 44 to move the magnetic paddle 436 from the magnetic block 437 to the magnet 434, so that a closed circuit is formed between the capacitor power supply 42 and the electromagnetic energy absorption unit 5.

[0060] In this invention, an electromagnetic active module is used to achieve buffer control for occupants of different masses, reducing the peak load experienced by occupants during a crash and achieving compliant load control. The mechanical switching unit can alternate with passive buffer structures such as levers to buffer and absorb energy over time. At the same time, the mechanical structure can improve the robustness of the system and facilitate the installation and deployment of the device.

[0061] In this invention, the passive buffer energy absorption device, including aluminum honeycomb, tie rods, etc., can quickly provide buffering in the initial stage of impact. At the same time, when the electromagnetic buffer device fails, the passive buffer energy absorption device can still play a certain role in buffering and absorbing energy, improving the robustness of the system. Although the magnetic buffer unit requires an external power supply, it can use a capacitor power supply, a fast and large discharge device, as an energy storage unit. It does not require additional power supply from the aircraft's electrical system and is not affected by the failure of the electromechanical system during the aircraft's runaway, thus increasing the reliability of the crash-resistant seat.

[0062] In this invention, the safety seat is easy to process and install. Compared with traditional carbon fiber tubes, this device is simpler to process, enabling mass production of original parts and large-scale manufacturing and installation. At the same time, the seat is easy to use. Before takeoff, the occupant only needs to install a capacitor power supply that matches their own weight on the back of the seat. During the crash, the electromagnetic system automatically enters the working state without any additional operation.

[0063] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A composite energy-absorbing safety seat for crash protection, comprising a seat body (1), a fixed bracket unit (2), a pull rod energy-absorbing unit (3), an on-off unit (4), an electromagnetic energy-absorbing unit (5), and an aluminum honeycomb energy-absorbing unit (6), the pull rod energy-absorbing unit (3), the electromagnetic energy-absorbing unit (5), and the aluminum honeycomb energy-absorbing unit (6) being installed between the seat body (1) and the fixed bracket unit (2), characterized in that, The seat body (1) is connected to the aircraft body through four movable bushings (23) and fixed with screws. One end of the pull rod energy absorption unit (3) is installed below the hanging hinge (212) of the fixed bracket unit (2), and the other end is installed on the energy absorption pull rod hinge (33) and connected to the seat body (1) and fixed with screws. The switch unit (4) and the electromagnetic energy absorption unit (5) are both installed in the space below the middle frame (2411). The switch unit (4) is suspended below the middle frame (2411), and one end of the electromagnetic energy absorption unit (5) is suspended below the middle frame (2411), and the other end is connected to the seat body (1) through the electromagnetic energy absorption unit hinge (55) and fixed with screws. The aluminum honeycomb energy absorption unit (6) is installed on the lower middle frame (2412), connected to the seat body (1) through the aluminum honeycomb bracket (61), and fixed with screws. The fixed support unit (2) includes a gantry (21), a guide rail (22), a movable bushing (23), and two intermediate frames (24). The guide rail (22) is connected to the aircraft cabin and is installed parallel and fastened on the aircraft. The guide rails (22) are connected to each other through the intermediate frames (24) to keep the guide rails (22) always in the same plane and parallel. The top of the guide rail (22) is connected to the gantry (21) and installed in the cavity (211) of the gantry (21). The movable bushing (23) is fixedly installed to the seat body (1) and connected to the guide rail (22), and can move up and down through the guide rail (22). The energy-absorbing unit (3) includes an inner cylinder (31), an outer cylinder (32), a hinge (33), an annular aluminum honeycomb panel (34), and an energy-absorbing rod assembly (35). The inner cylinder (31) includes an inner cylinder hinge (311), a limiting block (312), and a lower bottom surface (313). The inner cylinder hinge (311) is connected to the hanging hinge (212). The lower bottom surface (313) of the inner cylinder is connected to the energy-absorbing rod assembly (35) and the annular aluminum honeycomb panel (34). The energy-absorbing tie rod outer cylinder (32) includes an upper end cap (321), a first layer panel (324), a second layer panel (323), a third layer panel (322), and an outer cylinder hinge (325). The upper end cap (321) of the energy-absorbing tie rod outer cylinder is spaced a certain distance from the limiting block (312) to prevent the tie rod energy-absorbing unit (3) from being compressed. The outer cylinder hinge (325) is connected to the energy-absorbing tie rod hinge (33). The energy-absorbing tie rod hinge (33) includes an energy-absorbing tie rod hinge surface (331) and a fixed mounting surface (332). The energy-absorbing tie rod hinge surface (331) is connected to the outer cylinder hinge (325) and is relatively fixed to the energy-absorbing tie rod outer cylinder (32). The fixed mounting surface (332) is fixedly connected to the seat body (1). The annular aluminum honeycomb panel (34) is a special-sized annular filled aluminum honeycomb panel designed according to the shape of the energy-absorbing tie rod outer cylinder (32) and the energy-absorbing tie rod inner cylinder (31). The upper end of the energy-absorbing tie rod inner cylinder (31) is connected to the hanging hinge (212) through the inner cylinder hinge (311). The lower end of the energy-absorbing tie rod outer cylinder (32) is connected to the outer cylinder hinge (212) through the outer cylinder hinge (311). The cylinder hinge (325) is connected to the energy-absorbing tie rod hinge (33), and is installed on the seat body (1) through the fixed mounting surface (332) of the energy-absorbing tie rod hinge (33). The annular aluminum honeycomb plate (34) is installed between the outer cylinder (32) and the inner cylinder (31) of the energy-absorbing tie rod. The lower side of the upper end cap (321) of the outer cylinder of the energy-absorbing tie rod is between the upper side of the lower bottom surface (313) of the inner cylinder of the energy-absorbing tie rod. The energy-absorbing tie rod assembly (35) is installed between the lower bottom surface (313) of the inner cylinder of the energy-absorbing tie rod and the first layer panel (324) of the outer cylinder of the energy-absorbing tie rod. The switching unit (4) consists of a power buckle (41), a capacitor power supply (42), a switching circuit box (43), a trigger rod (44), and a guide rod limiter (45). The power buckle (41) is installed on the middle frame (2411) and is relatively fixed to the middle frame (2411). The other end of the power buckle (41) is connected to the capacitor power supply (42). Two wires extend from the end of the capacitor power supply (42) and are connected to the switching circuit box (43). The switching circuit box (43) also extends wires to form a circuit with the electromagnetic energy absorption unit (5). The trigger rod (44) is installed on the guide rod limiter (45) and extends from the hole below the switching circuit box (43). The guide rod limiter (45) is fixedly connected to the seat body (1). The electromagnetic energy absorption unit (5) includes an outer cylinder hanging hinge (51), an inner cylinder (52), an outer cylinder (53), a lower inner cylinder hinge (54), and an electromagnetic energy absorption unit hinge (55). The outer cylinder hanging hinge (51) is installed on the intermediate frame (2411). The inner cylinder (52) and the outer cylinder (53) of the electromagnetic energy absorption unit are connected by a central magnetic conductor (534) and restricted to one-dimensional relative vertical movement. The lower outer cylinder hinge (54) is connected to the electromagnetic energy absorption unit hinge (55). The outer cylinder (53) of the electromagnetic energy absorption unit is fixed to the seat body (1) through the electromagnetic energy absorption unit (5). The aluminum honeycomb energy absorption unit (6) includes an aluminum honeycomb bracket (61), an aluminum honeycomb (62), and an aluminum honeycomb hinge (63). The aluminum honeycomb bracket (61) is installed on the back of the seat body (1) and fixed to the seat body (1). The aluminum honeycomb (62) is installed on the support bearing surface (613) and the other end is connected to the aluminum honeycomb hinge (63). One end of the aluminum honeycomb hinge (63) is connected to the aluminum honeycomb (62), and the other end is connected to the lower middle frame (2412). The aluminum honeycomb energy absorption unit (6) includes two aluminum honeycombs (62). The one installed on the left side of the electromagnetic energy absorption unit (5) is the left aluminum honeycomb (6111), and the one installed on the right side of the electromagnetic energy absorption unit (5) is the right aluminum honeycomb (6112).

2. A composite energy-absorbing safety seat for fall protection according to claim 1, characterized in that, The hanger (21) includes a cavity (211) that is fixed to the guide rail (22) and a hinge (212) that is connected to the tie rod energy absorption unit (3), which serves to fix the guide rail (22) and connect the tie rod energy absorption unit (3). The movable bushing (23) includes a sleeve (231) that cooperates with the guide rail (22) and a bushing mounting plate (232) that is fixed to the seat body (1). The middle frame (24) includes a fixed cylinder (241) that is connected to the guide rail (22) and a truss (242) that is connected between the fixed cylinder (241). The two middle frames (24) are a middle middle frame (2411) and a lower middle frame (2412). The middle middle frame (2411) is installed between the four movable bushings (23) on the guide rail (22), and the other lower middle frame (2412) is installed below the four movable bushings (23) on the guide rail (22).

3. A composite energy-absorbing safety seat for fall protection according to claim 1, characterized in that, The energy-absorbing tie rod group (35) is a buffer energy-absorbing structure composed of multiple tie rod groups evenly distributed on the circumference. The tie rod group includes a thick tie rod (351), a medium tie rod (352), and a thin tie rod (353). During the buffer energy absorption process, the thick tie rod (351) first contacts the first layer panel (324) of the outer cylinder. After absorbing energy, it breaks by contacting the medium tie rod (352) and the second layer panel (323) of the outer cylinder. After absorbing energy, it breaks by contacting the thin tie rod (353) and the third layer panel (322) of the outer cylinder. The energy absorption process of the energy-absorbing tie rod group (35) ends.

4. A composite energy-absorbing safety seat for fall protection according to claim 1, characterized in that, The switch circuit box (43) includes a negative conductor (431), a switch circuit shell (432), a switch circuit hinge (433), a magnet (434), a positive conductor (435), a magnetic chuck (436), and a magnetic stop block (437). The positive conductor (435) and the negative conductor (431) extend from the switch circuit shell (432) and are connected to the electromagnetic energy absorption unit (5). The switch circuit hinge (433) is located inside the switch circuit shell (432) and is connected to the conductor extending from the capacitor power supply (42). The magnetic chuck (436) is connected to the switch circuit hinge (433) and can rotate one-dimensionally around the switch circuit hinge (433). The magnet (434) can attract and fix the magnetic chuck (436) and fix the magnetic chuck (436) under normal operating conditions. The magnetic stop block (437) can fix the magnetic chuck (436) during the impact.

5. A composite energy-absorbing safety seat for fall protection according to claim 4, characterized in that, The trigger rod (44) includes an insulated trigger head (441) and a deformable straight rod (442). The insulated trigger head (441) is in contact with the magnetic pawl (436), and its lower end is connected to the deformable straight rod (442). The insulated trigger head (441) is insulated to prevent accidental activation and avoid the formation of an additional closed circuit. The deformable straight rod (442) is a freely deformable straight rod that can withstand a small tensile force. After completing the triggering task, the deformable straight rod (442) breaks under tensile force and separates from the insulated trigger head (441), without hindering the operation of the rest of the system. The lower end is connected to a guide rod limiter (45). The guide rod limiter (45) includes a limiter fixing surface (451), a limiter plane (452), and a fixing post (453). The limiter fixing surface (451) is installed on the seat body (1) and fixed to the seat body (1). The limiter plane (452) is perpendicular to the limiter fixing surface (451) and is used to support the fixing post (453). The fixing post (453) is located on the limiter plane (452) and contacts the deformable straight rod (442) and is fixed to the deformable straight rod (442).

6. A composite energy-absorbing safety seat for fall protection according to claim 1, characterized in that, The inner cylinder (52) of the electromagnetic energy absorption unit includes an inner cylinder support (521), an upper actuating coil (522), a lower actuating coil (523), and a brake (524). The inner cylinder support (521) is located in the lower cavity of the inner cylinder (52) of the electromagnetic energy absorption unit and is used to fix the upper actuating coil (522) and the lower actuating coil (523). The brake (524) is installed at the bottom of the inner cylinder support (521). The outer cylinder of the electromagnetic energy absorption unit includes an end cap (531), a resistance energy absorption rod (532), an upper spring (533), a central magnetic conductor (534), an excitation coil (535), a lower spring (536), and an inner cylinder bottom surface (537). The end cap (531) is installed on the inner cylinder support (524). On the upper side of the outer cylinder (53) of the energy absorption unit, the inner cylinder (52) of the auxiliary electromagnetic energy absorption unit moves relative to the outer cylinder (53) of the electromagnetic energy absorption unit. The resistive energy absorption rod (532) is installed at a 120° angle inside the outer cylinder (53) of the electromagnetic energy absorption unit, with a total of three rods. One end of the upper spring (533) is installed under the end cap (531), and the other end is suspended. The central magnetic conductor (534) is installed in the middle. A common section is located between the inner cylinder (52) and the outer cylinder (53) of the electromagnetic energy absorption unit. The excitation coil (535) is fixed on the central magnetic conductor (534) and is also within the common section. One end of the lower spring (536) is fixed on the bottom surface (537) of the inner cylinder.

7. A composite energy-absorbing safety seat for fall protection according to claim 1, characterized in that, The aluminum honeycomb bracket (61) includes a bracket mounting surface (611), a bracket reinforcing rib (612), and a bracket bearing surface (613). The bracket mounting surface (611) is fixedly installed with the seat body (1), and the bracket reinforcing rib (612) is obliquely fixed between the bracket mounting surface (611) and the bracket bearing surface (613).

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