CN115352639A - Distribution bearing triggerable buffering energy-absorbing airplane cabin luggage rack structure - Google Patents

Abstract

A distribution bearing triggerable buffer energy-absorbing airplane cabin luggage rack structure is characterized in that a bottom cavity area of a luggage rack box body is filled with a honeycomb structure for absorbing energy, an air bag system is installed in the cavity area of the luggage rack box body, and the luggage rack box body is connected with the upper part of a cabin through a buffer energy-absorbing connecting device; when the plane has accidents such as falling and collision, firstly, the honeycomb structure filled in the cavity area at the bottom of the luggage rack box body can realize first-step energy absorption; then the buffer energy-absorbing connecting device starts to play a role to realize the energy absorption of the second step; when the sensor detects a damage signal, the safety air bag component starts to work, the safety air bag is rapidly expanded and unfolded to realize the third step of energy absorption, the safety air bag is rapidly expanded and unfolded to play a role in buffering, and secondary damage to passengers due to the fact that the luggage rack falls off is avoided; the problem of traditional luggage rack can't play the performance of buffering energy absorption not enough under the high-speed impact effect is solved, can effectively reduce the biggest impact load and play the effect of energy-absorbing protection.

Description

Distribution bearing triggerable type buffering energy-absorbing airplane cabin luggage rack structure

Technical Field

The invention relates to the technical field of civil aviation transporters, in particular to a distribution bearing triggerable buffer energy-absorbing airplane cabin luggage rack structure.

Background

With the rapid development of civil aviation industry, a new design concept of 'safety, economy, comfort and environmental protection' is continuously embodied on a large-scale passenger plane, an accidental crash accident is possible to happen to the civil aviation passenger plane in the process of executing a flight task, the civil aviation regulation airworthiness standard puts a certain requirement on the airworthiness of the plane, and the safety is taken as the most basic attribute and requirement of the plane and must be sufficiently emphasized. When the aircraft crashed by accident, the aircraft usually has high speed, and the luggage rack is located above the top of the head of the passenger in the passenger cabin, and under the action of great impact, the heavy object can probably damage the whole luggage rack after the connection structure of the existing luggage rack, so that the secondary injury is caused to the passenger. Take boeing 737NG as an example, traditional aircraft luggage rack uses phenolic resin glass fiber panel and paper honeycomb combined material panel to make and forms, the surface is spread and is spread a layer of white tydran film, from the material with structural buffering energy-absorbing when not considering high-speed impact, and be ordinary rigid connection with the connection structure of fuselage, fix to the fuselage through the connecting rod, the structure is comparatively simple, do not consider that the aircraft luggage rack is invalid in destruction under the high-speed impact, unable buffering dissipation energy, it leads to luggage rack to drop and causes bigger injury to the passenger to take place the fracture very probably. Consequently, for guaranteeing passenger's personal safety, wholly have under the prerequisite of certain anti crash characteristic at aircraft cabin section, aircraft luggage rack structure need possess the effect of buffering energy-absorbing, reduces the risk of luggage rack structure destruction to reduce unexpected casualties to a certain extent.

For a long time, many scholars at home and abroad carry out a series of intensive researches on energy-absorbing materials and structures to avoid serious damage of the structures in accidents such as automobile collision, emergency landing of aircrafts and the like and simultaneously reduce the injuries of drivers, pilots, passengers and the like. The traditional buffering energy-absorbing material is mainly metal, absorbs energy through structural failure or plastic deformation, wherein a tubular structure is widely applied to an energy-absorbing device and comprises a round pipe, a square pipe, a conical pipe which is formed along the axial direction, a windowing pipe, a polygonal thin-wall pipe and the like, and the most widely used metal thin-wall round pipe has good mechanical property and special geometric mode. Besides the buckling deformation of the metal thin-wall pipe, the expanding deformation and the metal cutting of the metal structure can also play a role in buffering and energy absorption. Wherein, the expanding deformation absorbs the impact energy through plastic deformation and friction heating; the metal cutting buffer converts impact energy into metal cutting energy, so that the purpose of energy absorption is achieved. The existing buffering energy-absorbing device mostly absorbs energy by the crushing deformation of materials, such as a multilayer metal grid structure, a metal honeycomb, metal foam, a negative Poisson ratio structure and the like, and meanwhile, a metal thin-wall member is widely applied to buffering energy absorption.

Currently, there are some component structures in the fields of airplanes and automobiles, etc., which consider the buffer and energy absorption in case of high-speed collision in unexpected situations, such as the lower floor structure of the passenger cabin of an airplane. The corrugated beam and the corrugated plate structure have good buffering and energy-absorbing characteristics, absorb a large amount of energy through continuous crushing deformation, replace a lower web plate of a cargo compartment floor with a lightening hole, absorb impact energy and reduce initial load, and are already applied to a bottom plate of a helicopter cabin as a buffering and energy-absorbing part. The design of the traditional aircraft luggage rack structure follows the design principles of safety, comfort and maintainability on the premise of meeting the airworthiness requirement and the overall design requirement of the aircraft. For a typical structure form of a luggage rack, a composite material panel of a metal material and a honeycomb sandwich structure is generally used for a main-stream airplane cabin luggage rack structure in the market, and a decorative film is paved or a decorative paint layer is sprayed on the surface of the composite material panel to meet the requirement of the appearance effect of a cabin; the connection form considers the maintenance requirement, the shock absorption and noise reduction requirement and the installation design compensation, and rigid rod pieces are adopted for connection so as to transmit and bear the load of the aircraft in the course direction, the lateral direction and the vertical direction.

The invention patent with publication number CN109850157A discloses a multifunctional airplane luggage rack, which improves the structure of the luggage rack, is provided with a terminal display, controls the opening of a luggage rack lock through a bar code recognizer, ensures the boarding order, improves the boarding efficiency, and increases the escape probability of passengers in emergency situations, but does not consider the buffering and energy absorption requirements of the luggage rack under the unexpected situations of falling and collision of the airplane and the like; the invention patent with publication number CN108367810A discloses an overhead luggage rack for an airplane, which has a latch mechanism to fix the movable part of the luggage rack, and a lifting spring is provided to facilitate closing the luggage rack, but the invention also lacks a structural design for buffering and energy absorption; other related inventions mainly include improvement of convenience and safety in use when the cover of the luggage rack is opened by increasing the volume of the luggage rack through design, and do not consider energy absorption for buffering under high-speed impact. At present, the structure of the luggage rack only considers the requirements of material flame retardance, structural strength and other functionalities, and no clear solution is given to the structure of the conventional airplane luggage rack for the requirements of buffering and energy absorption under high-speed impact.

In conclusion, the existing mainstream airplane luggage rack structure is generally made of a composite material of a metal material and a honeycomb sandwich structure, only the requirements of structure weight reduction, material flame retardance and structural strength are considered, the requirement of buffering and energy absorption under high-speed impact is not considered, and the luggage rack structure does not have a good energy absorption effect and has certain limitation. For the connection form of the luggage rack and the airplane body, the airplane can be subjected to course, lateral and vertical loads in the flying process, the loads of the luggage rack are different in different postures, the traditional airplane luggage rack adopts a rigid connection structure which is good in maintainability and simple in structure and easy to replace, and the connection structure can be subjected to great loads when the airplane is accidentally crashed and is a key component for buffering and absorbing energy. Because the rod piece is mainly pulled when the aircraft luggage rack is connected with the passenger cabin section of the fuselage, and the existing buffering energy-absorbing device or structure generally generates crushing deformation through buffering energy-absorbing materials so as to realize energy absorption, most of the devices are used for the compression process of direct collision, for example, the impact damage of an anti-collision beam during the collision of an automobile, the energy-absorbing deformation generated during the high-speed collision of the lower structure of the floor of the aircraft cabin, and the like, the situation can not be applied to the structure of the aircraft luggage rack, and the volume of the rod-shaped connecting structure is smaller, most of the existing buffering energy-absorbing devices are unreasonable, the energy-absorbing efficiency is lower, the using condition and the limitation are obvious, the buffering energy-absorbing device which can be used for the connecting structure of the aircraft luggage rack and the fuselage also rarely appears and has no triggering device, and therefore, a novel connecting device with the buffering energy-absorbing effect is required to be designed. Meanwhile, the existing aircraft luggage rack structure does not consider secondary damage to passengers when the luggage rack falls off in the design process, and a corresponding safety protection system is lacked.

Disclosure of Invention

In order to overcome the defects in the prior art, the invention aims to provide a distribution-bearing triggerable buffering energy-absorbing airplane cabin luggage rack structure, which adopts a plurality of buffering modes that the distribution-bearing triggerable buffering mode is adopted, energy absorption is realized by converting impact load borne by the structure into compression deformation of materials and metal cutting, the problem that the traditional luggage rack cannot play a role in buffering and absorbing energy under the action of high-speed impact is solved, the maximum impact load can be effectively reduced, and the function of energy absorption protection is played.

In order to achieve the purpose, the technical scheme of the invention is as follows:

the utility model provides a distribution bears formula buffering energy-absorbing aircraft cabin luggage rack structure that can trigger, includes luggage rack box 4, and the regional packing of bottom cavity of luggage rack box 4 has honeycomb 6 that is used for the energy-absorbing, and the regional installation air bag system of cavity of luggage rack box 4, and luggage rack box 4 is connected with 1 upper portion in cabin through buffering energy-absorbing connecting device 5.

The buffering and energy-absorbing connecting device 5 comprises a sleeve 11 and a sleeve rod 12 which are used for connecting the cabin 1 and the luggage rack box body 4, the inner wall of a triggering section of the sleeve 11 is of a variable cross section, the sleeve 11 is connected with the sleeve rod 12 through a screw 15, metal foam 13 is filled in the sleeve 11, a broach 16 and a gasket 14 are installed at the top of the metal foam 13, and the upper part of the gasket 14 is fastened with a nut 18 on the screw 15 through a spring 17.

The screw 15 at the upper part of the nut 18 is also provided with a spring slider triggering mechanism which triggers to absorb energy under the action of great impact and is arranged in the variable cross-section area of the sleeve 11, the spring slider triggering mechanism is composed of a spring frame 19, a triggering spring 20 and a slider 21, grooves are reserved at the bottoms of four cylindrical holes of the spring frame 19 and are used for positioning one end of the triggering spring 20, a rod-shaped structure at the root part of the slider 21 is provided with an annular slit, and the triggering spring 20 is sleeved and arranged on the annular slit.

The cross section of the sliding block 21 is trapezoidal and is matched with the variable cross section of the sleeve 11.

The safety airbag system comprises a sensor 10 bonded on the outer wall of the buffering and energy-absorbing connecting device 5, a safety airbag assembly 8 arranged at the honeycomb structure 6, a slit for ejecting and unfolding an airbag reserved at the bottom of the luggage rack box body 4, and a central electronic control device 7 arranged at the side edge of the luggage rack box body 4; the central electronic control unit 7 is controlled in signal communication with the sensor 10 and the airbag module 8.

The safety air bag assembly 8 comprises a gas generator, an igniter and an air bag, and the central electronic control device 7 is internally provided with a control processing system.

The invention has the beneficial effects that:

1. the bottom of the luggage rack box body 4 of the airplane is filled with the honeycomb structure 6 for buffering and energy absorption, the luggage rack box body has the characteristic of distributed bearing when being connected with the airplane body, and the connecting device has excellent buffering and energy absorption effects.

2. The buffering and energy-absorbing connecting device 5 adopts a compression loop bar structure design, converts the impact load of the structure into the compression and energy absorption of the buffering material, can be widely applied to a pulled rod-shaped structure, and solves the problem that the traditional buffering and energy-absorbing device cannot be applied to the pulled rod-shaped structure.

3. The buffering and energy-absorbing connecting device 5 is additionally provided with a trigger mechanism so as to ensure that the buffering and energy-absorbing connecting device only plays a role in buffering and energy-absorbing under the condition of high-speed impact and has the same effect as the original connecting structure under the normal load level.

4. The metal foam 13 is filled with a porous material, so that the energy-absorbing material has the advantages of light weight, high specific strength and good buffering and energy-absorbing effects.

5. The metal cutting energy absorption realized by the broach 16 and the metal foam 13 filling two buffering modes are combined, so that the buffering energy absorption effect is further improved.

6. An air bag system is arranged in the luggage rack structure, and the air bag system is popped up to ensure that passengers are prevented from secondary injury when accidental falling and collision occur through detection and intelligent control of a sensor 10.

Drawings

FIG. 1 is a schematic illustration of a passenger cabin segment of an aircraft.

Fig. 2 is a schematic cross-sectional view of an aircraft luggage rack.

Figure 3 is a schematic view of the roof rack with the airbag fully inflated.

FIG. 4 is a schematic view of the structure of the energy-absorbing connection (initial state).

FIG. 5 is a partial schematic view of a structure of a cushioning and energy absorbing attachment.

FIG. 6 is a schematic view of the structure of the energy-absorbing bumper attachment (in a stretched state).

FIG. 7 is an exploded view of the energy absorbing bumper attachment.

Fig. 8 is a cross-sectional schematic view of a spring-slider trigger mechanism.

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings.

A distribution bearing triggerable buffer energy-absorbing airplane cabin luggage rack structure is disclosed, referring to fig. 1, wherein fig. 1 is a schematic diagram of an airplane cabin section and comprises a cabin 1; a floor 2; a seat 3; a luggage rack box 4; referring to fig. 2 and 3, the bottom cavity area of the luggage rack box body 4 is filled with a honeycomb structure 6 for absorbing energy, an airbag system is installed in the cavity area of the luggage rack box body 4, and the luggage rack box body 4 is connected with the upper part of the cabin 1 through a buffering and energy-absorbing connecting device 5. Specifically, riveted circular holes are reserved at two ends of the buffering and energy-absorbing connecting device 5, and the reserved joints on the upper portions of the luggage rack box body 4 and the engine room 1 are connected and fixed through rivets 9.

Referring to fig. 4, 5 and 6, the energy-absorbing buffer connecting device 5 comprises a metal sleeve 11 and a loop bar 12 for connecting the cabin 1 and the luggage rack box 4, and the metal sleeve 11 and the loop bar 12 are main force-bearing structural members, the sleeve 11 is connected with the loop bar 12 through a screw 15, the metal foam 13 is filled in the sleeve 11, a broach 16 and a gasket 14 are mounted on the top of the metal foam 13, and the upper part of the gasket 14 is fastened with a nut 18 on the screw 15 through a spring 17.

In the aircraft cabin section, the luggage rack box body 4 is generally positioned above the passenger seats and is connected with the fuselage cabin section through a distributed layout, and the lower bearing part of the luggage rack box body is filled with a honeycomb structure to enhance the buffering effect of the box body. Through holes for connection are reserved at corresponding positions of the cabin section and the luggage rack of the airplane body, the single cabin section is connected with the luggage rack on one side through three groups of buffering and energy-absorbing devices with different rod lengths, through holes matched with the buffering and energy-absorbing devices are reserved at two ends of a rod structure of each buffering and energy-absorbing connecting device, and the through holes are distributed and connected at equal intervals by rivets.

Generally, a buffering energy-absorbing material has an excellent energy-absorbing effect when being compressed, so that an impact load applied to a structure needs to be converted into compression of the buffering energy-absorbing material when an accident occurs. In order to play the effect of buffering energy-absorbing, buffering energy-absorbing structural design is on guaranteeing the basis of original connecting rod function, at its inside packing metal foam aluminium, and the impact that simultaneously need receive the aircraft luggage rack converts the compression of buffering energy-absorbing material into, through design sleeve structure, plays the effect of buffering energy-absorbing. The buffering energy-absorbing part adopts a compression loop bar structure design, mainly comprises a fixed bar sleeve, a buffering energy-absorbing material and an inner pull bar, and is additionally provided with a spring triggering mechanism. The buffering and energy-absorbing connecting device adopts an energy-absorbing mode of combining metal broach cutting energy absorption and porous material (foamed aluminum) filled metal sleeve, wherein the metal broach plays a role in energy absorption by cutting the metal thin-wall sleeve, and in order to enhance the capability of buffering and absorbing impact energy, the metal broach is usually made into a form formed by connecting a plurality of structural forms with different sizes in series. When the impact load reaches a set threshold value, relative motion occurs between the metal sleeve and the broaching tool, and the metal broaching tool sequentially cuts the metal sleeve, so that the impact energy is converted into metal cutting energy, and the aim of buffering and energy absorption is fulfilled. The broach type buffering energy absorption effect mainly depends on the material strength of the sleeve, the working tooth number of the broach, the width of the cutting blade and the thickness of the metal cutting layer, and meanwhile, the broach type buffering energy absorption effect needs to be correspondingly improved when being used for an airplane luggage rack connecting structure in consideration of the processing precision, the assembling precision and the axial size.

Referring to fig. 8, a spring slider triggering mechanism which triggers energy absorption under the action of a great impact is further arranged on the screw 15 at the upper part of the nut 18 and is installed in a variable cross-section area of the sleeve 11, the spring slider triggering mechanism is composed of a spring frame 19, a triggering spring 20 and a slider 21, grooves with small radiuses are reserved at the bottoms of four cylindrical holes of the spring frame 19 and are used for positioning one end of the triggering spring 20, a rod-shaped structure at the root of the slider 21 is provided with an annular slit, the triggering spring 20 is installed on the annular slit in a sleeved mode, and the cross section of the slider 21 is trapezoidal and is matched with the variable cross section of the sleeve 11; through the common restraint of four sliders 21 and trigger spring 20, make whole slider mechanism shrink or expand in radial direction, trigger spring 20 has less compression capacity at initial condition, and slider 21 is in the rightmost end (the internal diameter is great) of sleeve 11 internal diameter expansion section, because spring slider trigger mechanism installs the variable cross section region at sleeve 11, and the cross section of slider is trapezoidal, thereby it forces the slider to remove compression spring when receiving the power of screw rod 15, causes whole mechanism radial contraction to move to the less direction in sleeve cross section gradually, plays the effect of triggering.

When the impact is small, the triggering mechanism does not trigger energy absorption, the distance between the loop bar 12 and the sleeve 11 is short, the screw rod 15 is subjected to axial tension to force the spring slider triggering mechanism to move leftwards, a spring 20 in the triggering mechanism and a spring 17 between the nut 18 and the broach 16 are compressed to generate elastic potential energy and continuously dissipate to finally play a role in buffering; when the shock absorber is greatly impacted, the distance between the loop bar 12 and the sleeve 11 is increased, the spring 17 is compressed to the minimum length at the moment, the spring slider trigger mechanism moves to the minimum end of the variable cross section and triggers whole energy absorption, the gasket 14 starts to compress the metal foam 13, the broach 16 starts to cut the sleeve 11, the two modes simultaneously absorb most of energy, and meanwhile, the roughness of the inner wall of the metal sleeve 11 can be increased, so that the slider 21 in the trigger mechanism and the inner wall of the metal sleeve generate larger friction, and the energy absorption effect is further improved.

Considering that the impact load of an aircraft is very large in the case of an accidental crash or an abnormal landing, the breakage or falling of the roof rack structure is likely to occur, and an airbag system is installed in the roof rack structure in order to further protect the safety of passengers. The safety airbag system comprises a sensor 10 bonded on the outer wall of the buffering and energy-absorbing connecting device 5, a safety airbag assembly 8 arranged at the honeycomb structure 6, a slit for ejecting and unfolding an airbag reserved at the bottom of the luggage rack box body 4 and a central electronic control device 7 at the side edge of the luggage rack box body 4; the central electronic control unit 7 is controlled in signal communication with the sensor 10 and the airbag module 8.

The safety air bag component 8 is an existing mature product and comprises a gas generator, an igniter and an air bag, and the central electronic control device 7 contains an algorithm processing system. When the airplane is accidentally crashed or abnormally landed, the air bag system is automatically activated, the displacement sensor attached to the buffering and energy-absorbing connecting device mainly detects the relative position of the sleeve 11 and the loop bar 12, the position information is sent to the central electronic control device 7 through wireless transmission, algorithm processing calculation and comparison judgment are carried out, when the relative position exceeds a set critical value, the buffering and energy-absorbing connecting device achieves the maximum buffering and energy-absorbing effect and is about to be damaged and failed, the central electronic control device 7 is communicated with the air bag assembly 8 and sends out an ignition signal of the air bag, the gas generator starts to work, the igniter detonates the igniter to ensure that the inflator is heated and decomposed to release a large amount of gas to fill the air bag, the air bag pops out from a slit reserved at the bottom of the luggage rack and expands rapidly, and the air bag is completely unfolded to play a buffering role before the luggage rack drops.

The working principle of the invention is as follows:

when the airplane has accidents such as falling and collision, the goods in the inertia luggage rack can generate great impact action on the luggage rack, so that the luggage rack with the buffering and energy-absorbing functions can effectively reduce impact load. Firstly, the honeycomb structure 6 filled in the cavity area at the bottom of the luggage rack box body 4 can realize first-step energy absorption; then the buffering energy-absorbing connecting device 5 starts to play a role, the loop bar 12 is subjected to tensile force and is transmitted to the screw rod 15 to generate displacement, the spring slider trigger mechanism connected with the screw rod 15 also starts to slide, the trigger spring 20 continues to be compressed until the slider 21 moves to a region with a smaller sleeve inner diameter, at the moment, the broach 16 starts to cut the inner wall of the sleeve 11, and meanwhile, the metal foam 13 generates crushing deformation to realize the second-step energy absorption. When the sensor 10 detects a damage signal, the central electronic control device 7 sends an ignition signal, the safety air bag assembly 8 starts to work, and the safety air bag is rapidly expanded and unfolded to realize the third step of energy absorption. The rapid expansion of the safety airbag plays a role in buffering, and the luggage rack is prevented from dropping to cause secondary damage to passengers.

According to the invention, the distribution-bearing triggerable buffering energy-absorbing airplane cabin luggage rack structure is designed, so that the impact load and the personal safety of an airplane in the case of accidental crash or abnormal landing are fully considered, and the buffering energy-absorbing effect of the traditional luggage rack structure is effectively improved. The luggage rack adopts a novel stretchable buffering and energy-absorbing connecting device, and the tensile stress of the structure when the structure is impacted is converted into the compression of a buffering material and the energy absorption of metal cutting through the design of a compression loop bar structure, so that the application scenes of the buffering and energy-absorbing structure are widened, and particularly, a plurality of pulled bar-shaped structures are adopted; meanwhile, a spring slider trigger device is added in the buffering and energy-absorbing connecting structure to ensure the effect of triggering buffering and energy-absorbing under the action of great impact, and the rigid connecting function of the original rod-shaped structure is not influenced under normal conditions; in addition, the metal porous material has the characteristics of low density, stable buffering performance and excellent energy absorption effect, and the energy absorption structure formed by filling the metal sleeve has the advantages of light weight and high specific strength, and can be used in application scenes with strict requirements on structure quality; the design idea of combining two buffering modes of metal porous material filling and metal cutting can obviously improve the buffering and energy-absorbing effect of the whole buffering and energy-absorbing connecting structure and improve the stability of buffering and energy-absorbing simultaneously. The buffering and energy-absorbing connecting device adopts a distributed layout, so that the bearing can be enhanced to a great extent, the acting force can be effectively dispersed when the luggage rack is impacted at a high speed, and the luggage rack is protected from being damaged. The aircraft luggage rack bottom half bears the weight of the buffering effect that the part fills honeycomb structure reinforcing box itself, makes its self structure avoid taking place to destroy, and installation air bag system can protect the passenger to avoid secondary damage under the unexpected condition in luggage rack structure bottom cavity, and when the sensor detected buffering energy-absorbing connection structure's destruction signal, the controller sent the firing signal and made air bag expand the expansion rapidly and expand to play the effect of protection passenger. This luggage rack structure has the effect of multistage buffering energy-absorbing, the regional honeycomb structure that fills of luggage rack bottom cavity realizes first-level energy-absorbing, metal foam conquassation and broach cutting metal sleeve realize the second grade energy-absorbing among the buffering energy-absorbing connection structure, air bag expands rapidly when receiving the destruction signal and expandes and realize the third grade energy-absorbing, can reduce the load that receives when assaulting by a wide margin through multistage buffering energy-absorbing to guarantee passenger's safety.

Claims (6)

1. The utility model provides a distribution bears triggerable formula buffering energy-absorbing aircraft cabin luggage rack structure, includes luggage rack box (4), its characterized in that, and the regional packing of bottom cavity of luggage rack box (4) has honeycomb (6) that are used for the energy absorption, and the regional installation air bag system of cavity of luggage rack box (4), and luggage rack box (4) are connected with cabin (1) upper portion through buffering energy-absorbing connecting device (5).

2. The distributed load-bearing triggerable energy-absorbing airplane cabin luggage rack structure as claimed in claim 1, wherein the energy-absorbing connecting device (5) comprises a sleeve (11) and a loop bar (12) for connecting the cabin (1) and the luggage rack box body (4), the inner wall of the triggering section of the sleeve (11) is of a variable cross section, the sleeve (11) is connected with the loop bar (12) through a screw (15), metal foam (13) is filled in the sleeve (11), a broach (16) and a gasket (14) are installed at the top of the metal foam (13), and the upper part of the gasket (14) is fastened with a nut (18) on the screw (15) through a spring (17).

3. The passenger cabin luggage rack structure of the triggerable load-bearing cushioning and energy absorbing airplane as claimed in claim 2, wherein a spring slider triggering mechanism for triggering energy absorption under the action of a large impact is further arranged on the screw (15) at the upper part of the nut (18) and is installed in the variable cross-section area of the sleeve (11), the spring slider triggering mechanism is composed of a spring rack (19), a triggering spring (20) and a slider (21), grooves are reserved at the bottoms of four cylindrical holes of the spring rack (19) for positioning one end of the triggering spring (20), the rod-shaped structure at the root of the slider (21) is provided with an annular slit, and the triggering spring (20) is installed on the annular slit in a sleeved mode.

4. A distributed load bearing triggerable amortization energy absorption airplane cabin baggage rack structure according to claim 3, wherein said slider (21) has a trapezoidal cross section adapted to the variable cross section of the sleeve (11).

5. A distributively load-bearing triggerable crash truck structure for aircraft cabins according to claim 1, characterized in that said airbag system comprises sensors (10) glued to the outer walls of the crash truck attachment means (5), airbag modules (8) arranged at the honeycomb structure (6), airbag popping and deploying slits reserved at the bottom of the truck box (4), central electronic control means (7) at the sides of the truck box (4); the central electronic control device (7) is in signal communication control with the sensor (10) and the airbag module (8).

6. The structure of a distributed load-bearing triggerable amortization energy absorption airplane cabin luggage rack as claimed in claim 1, wherein said airbag module (8) comprises a gas generator, an igniter and an airbag, and a control processing system is contained in the central electronic control device (7).

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