CN211336491U

CN211336491U - Multi-stage landing buffering energy-absorbing device

Info

Publication number: CN211336491U
Application number: CN201922028203.2U
Authority: CN
Inventors: 张�荣; 李松岩; 罗昌杰; 于文泽; 钟波
Original assignee: Shenzhen Cansinga Technology Co ltd
Current assignee: Shenzhen Cansinga Technology Co ltd
Priority date: 2019-11-21
Filing date: 2019-11-21
Publication date: 2020-08-25
Anticipated expiration: 2029-11-21

Abstract

The utility model provides a multistage landing buffering energy-absorbing device, including tertiary energy-absorbing mechanism, first order energy-absorbing mechanism includes first shell and the elastic energy-absorbing unit of holding in first shell inner chamber, second level energy-absorbing mechanism is elastic cement buffer, second level energy-absorbing mechanism includes relative distribution's first end and second end, first end is spacing in first shell and supports the top with elastic energy-absorbing unit, tertiary energy-absorbing mechanism includes second shell and holding the plasticity energy-absorbing unit in the second shell inner chamber, the second end is spacing in the second shell and supports the top with plasticity energy-absorbing unit. The utility model discloses a first order energy-absorbing mechanism provides the buffering energy-absorbing of conventional operating mode, provides the buffering energy-absorbing of unconventional urgent operating mode through second level energy-absorbing mechanism, provides the buffering energy-absorbing of unconventional urgent operating mode through third level energy-absorbing mechanism to it is difficult to satisfy the technical problem that aircraft such as carrier rocket, aircraft reply complicated landing operating mode requirement to have solved landing buffering energy-absorbing device effectively.

Description

Multi-stage landing buffering energy-absorbing device

Technical Field

The utility model belongs to the technical field of spacecraft soft landing auxiliary device, more specifically say, relate to a multistage landing buffering energy-absorbing device.

Background

At present, a landing buffering energy absorption device applied to the field of aerospace generally adopts a single elastic energy consumption or plastic energy consumption mode to assist aircrafts such as a carrier rocket, an airplane and the like to realize soft landing, wherein elastic energy consumption generally adopts elastic energy absorption units which can be restored by rubber, springs and the like, a common load curve of the elastic energy absorption units is a nonlinear parabola, the elastic energy absorption units can rebound after load relief, buffering energy absorption is carried out by converting impact energy into frictional heat energy consumption, but the energy absorption is relatively small, the compression ratio is limited, and the landing buffering energy absorption device is generally suitable for low-level energy impact occasions; the plastic energy consumption generally adopts unrecoverable plastic energy absorption units such as honeycombs and crushing pipes, the plastic energy absorption units have strong bearing capacity and high compression rate, impact energy is converted into metal plastic deformation energy for buffering and energy absorption, and the energy absorption is large but cannot be reused. And because the uncertainty of various parameters such as impact speed, attitude, wind speed and the like of the aircraft is large when the aircraft lands, the landing buffering energy-absorbing device particularly applied to the carrier rocket is influenced by the various parameters and also ablated by rocket tail flames, and even if the landing buffering energy-absorbing device is protected by a heat-proof heat-insulating material, the aircraft still needs to be baked at the high temperature of about 150 ℃, so that the existing landing buffering energy-absorbing device is difficult to meet the requirement of the aircraft such as the carrier rocket, the airplane and the like on complex landing working conditions.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a multistage landing buffering energy-absorbing device, including but not limited to solving landing buffering energy-absorbing device and being difficult to satisfy the technical problem that aircraft such as carrier rocket, aircraft reply complicated landing operating mode requirement.

In order to achieve the above object, the utility model provides a multistage landing buffering energy-absorbing device, include:

the first-stage energy absorption mechanism comprises a first shell and an elastic energy absorption unit accommodated in the inner cavity of the first shell;

the second-stage energy absorption mechanism is an elastic cement buffer and comprises a first end and a second end which are oppositely distributed, and the first end is limited in the first shell and abuts against the elastic energy absorption unit; and

the third-stage energy absorption mechanism comprises a second shell and a plastic energy absorption unit accommodated in the inner cavity of the second shell, and the second end is limited in the second shell and abuts against the plastic energy absorption unit;

the triggering force of the first-stage energy absorption mechanism is smaller than that of the second-stage energy absorption mechanism, and the triggering force of the second-stage energy absorption mechanism is smaller than that of the third-stage energy absorption mechanism.

Optionally, the second housing includes a second shell and a second end cap, and the second end cap is covered on one end of the second shell.

Optionally, the elastic energy absorbing unit comprises:

a plurality of thermoplastic polyester elastomers arranged coaxially at intervals; and

at least two separation blocking pieces are respectively arranged between two adjacent thermoplastic polyester elastomers.

Optionally, the baffle plate is a metal plate.

Optionally, the plastic energy absorbing unit is a metal honeycomb material piece.

Optionally, the second stage energy absorbing mechanism comprises:

a first cylinder having a closed end that is one of the first end and the second end;

the opening end of the second cylinder body extends into the opening end of the first cylinder body and is limited in the inner cavity of the first cylinder body, the closed end of the second cylinder body is the other one of the first end and the second end, and the inner cavity of the second cylinder body is filled with elastic cement gum;

the third end cover is covered on the opening end of the second cylinder body in a sealing manner; and

and the piston part of the piston rod is accommodated in the inner cavity of the second cylinder body and is close to the third end cover, and the rod part of the piston rod penetrates through the third end cover to be fixedly connected with the inner wall of the first cylinder body.

Optionally, the cross-sectional area of the first end and the cross-sectional area of the second end are respectively greater than the cross-sectional area of the body of the first cylinder, a first mounting hole is formed in one end of the first housing, a second mounting hole is formed in one end of the second housing, and the outer contour shape of the first mounting hole and the outer contour shape of the second mounting hole are matched with the outer contour shape of the body of the first cylinder.

Optionally, be equipped with first current-limiting structure on the third end cover, first current-limiting structure is used for supplying the elasticity daub pours into and restricts the elasticity daub flows out the inner chamber of second cylinder body, be equipped with second current-limiting structure in the piston portion, second current-limiting structure is used for supplying the elasticity daub flows into from being close to one side of third end cover is kept away from one side of third end cover.

Optionally, the first flow restriction structure comprises:

the first accommodating groove is concavely arranged on the inner end face of the third end cover;

the first through hole penetrates through the outer end face of the third end cover and is communicated with the first accommodating groove;

the first steel ball is accommodated in the first accommodating groove and can seal the first through hole; and

the first hollow stud is arranged on the notch of the first accommodating groove in a rotating mode so as to limit the first steel ball from falling out of the first accommodating groove;

the second current limiting structure includes:

the second accommodating groove is concavely arranged on the end face, far away from the third end cover, of the piston part;

the second through hole penetrates through the end face, facing the third end cover, of the piston part and is communicated with the second accommodating groove;

the second steel ball is accommodated in the second accommodating groove and can seal the second through hole; and

and the second hollow stud is spirally arranged on the notch of the second accommodating groove to limit the second steel ball from falling out of the second accommodating groove.

Optionally, be equipped with spacing flange on the inner wall of first cylinder body, the spacing groove has been seted up on the outer wall of second cylinder body, the spacing groove is followed the open end of second cylinder body to the blind end of second cylinder body extends, spacing flange stretches into it is spacing to form in the spacing groove.

The utility model provides a multistage landing buffering energy-absorbing device's beneficial effect lies in: the three-stage energy absorption mechanism is adopted, the first-stage energy absorption mechanism provides buffering energy absorption under the conventional working condition to ensure the soft landing of the aircraft, the second-stage energy absorption mechanism provides buffering energy absorption under the unconventional non-emergency working condition to ensure the stable landing of the aircraft, and the third-stage energy absorption mechanism provides buffering energy absorption under the unconventional emergency working condition to ensure the safe landing of the aircraft, so that the technical problem that a landing buffering energy absorption device cannot meet the requirement of the aircraft such as a carrier rocket, an airplane and the like on the complex landing working condition is effectively solved, and the landing safety and success rate of the aircraft are improved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the embodiments or the prior art descriptions will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive labor.

Fig. 1 is a schematic structural view of a multi-stage landing buffering energy-absorbing device provided by the present invention;

fig. 2 is a schematic view of a first-stage energy-absorbing state of the multi-stage landing buffering energy-absorbing device provided by the present invention;

fig. 3 is a schematic diagram of a secondary energy absorption state of the multi-stage landing buffering energy-absorbing device provided by the present invention;

fig. 4 is a schematic diagram of a three-stage energy absorption state of the multi-stage landing buffering energy-absorbing device provided by the present invention;

FIG. 5 is a graph showing an energy absorption curve of the multi-stage landing buffering energy absorber of the present invention;

fig. 6 is a schematic partial axial sectional view of a multistage landing buffering energy absorber according to the present invention.

Wherein, in the figures, the respective reference numerals:

1-multistage landing buffering energy-absorbing device, 10-first stage energy-absorbing mechanism, 20-second stage energy-absorbing mechanism, 30-third stage energy-absorbing mechanism, 11-first shell, 12-elastic energy-absorbing unit, 21-first end, 22-second end, 23-first cylinder, 24-second cylinder, 25-third end cover, 26-piston rod, 31-second shell, 32-plastic energy-absorbing unit, 110-first mounting hole, 111-first shell, 112-first end cover, 120-thermoplastic polyester elastomer, 310-second mounting hole, 311-second shell, 312-second end cover, 230-limiting flange, 241-throttling gap, 242-limiting groove, 250-first current-limiting structure, 251-first containing groove, 252-first through hole, 253-first steel ball, 261-piston part, 262-rod part, 2610-second current-limiting structure, 2611-second through hole, containing groove 2612-second through hole, 2613-second steel ball, F1-second-stage trigger force, F2-third-stage trigger force, S1-first-stage energy absorption stroke, S2-second-stage energy absorption stroke and S3-third-stage energy absorption stroke.

Detailed Description

In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to illustrate the present invention in further detail. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

It should be noted that: when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly or indirectly connected to the other element. When a component is referred to as being "electrically connected" to another component, it can be electrically connected by conductors, or can be electrically connected by radios, or can be connected by various other means capable of carrying electrical signals. The terms "upper", "lower", "left", "right", and the like, indicate orientations or positional relationships based on those shown in the drawings, are merely for convenience of description, and do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and operate, and thus are not to be construed as limiting the patent, and the specific meanings of the above terms will be understood by those skilled in the art according to specific situations. The terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features. The term "plurality" means two or more unless specifically limited otherwise.

It is right now that the utility model provides a multistage landing buffering energy-absorbing device explains.

Referring to fig. 1 to 4, the multi-stage landing buffering energy-absorbing device 1 includes a first-stage energy-absorbing mechanism 10, a second-stage energy-absorbing mechanism 20 and a third-stage energy-absorbing mechanism 30, wherein the trigger force of the first-stage energy-absorbing mechanism 10 is smaller than the trigger force F1 of the second-stage energy-absorbing mechanism 20, and the trigger force F1 of the second-stage energy-absorbing mechanism 20 is smaller than the trigger force F2 of the third-stage energy-absorbing mechanism 30; specifically, the first-stage energy absorption mechanism 10 comprises a first shell 11 and an elastic energy absorption unit 12, wherein the elastic energy absorption unit 12 is accommodated in an inner cavity of the first shell 11; the second-stage energy absorption mechanism 20 is an elastic cement buffer, the second-stage energy absorption mechanism 20 comprises a first end 21 and a second end 22 which are distributed oppositely, the first end 21 is limited in the first shell 11, namely the first end 21 is accommodated in an inner cavity of the first shell 11 and can move along the axial extension direction of the first shell 11, and meanwhile, the first end 21 abuts against the elastic energy absorption unit 12; the third-stage energy absorption mechanism 30 includes a second shell 31 and a plastic energy absorption unit 32, the plastic energy absorption unit 32 is accommodated in an inner cavity of the second shell 31, and the second end 22 is limited in the second shell 31, that is, the second end 22 is accommodated in the inner cavity of the second shell 31 and can move along the axial extension direction of the second shell 31, and meanwhile, the second end 22 abuts against the plastic energy absorption unit 12.

It is understood that the first stage energy absorbing mechanism 10, the second stage energy absorbing mechanism 20 and the third stage energy absorbing mechanism 30 are coaxial; the cross-sectional outer contour of the first end 21 is matched with the cross-sectional inner contour of the first shell 11, the first end 21 is in clearance fit with the first shell 11, the cross-sectional outer contour of the second end 22 is matched with the cross-sectional inner contour of the second shell 31, and the second end 22 is in clearance fit with the second shell 31; the elastic daub buffer is a viscous buffer which is commercially available and takes elastic daub formed by adding flame retardant, anti-compression agent, lubricant, anti-aging agent and the like into silicon macromolecular compound as an energy absorbing element, and the elastic daub has the characteristic of not changing the basic form at the temperature of between 50 ℃ below zero and 250 ℃.

Here, the elastic energy-absorbing unit 12 is preferably composed of a plurality of thermoplastic polyester elastomers 120 and at least two barrier ribs (not shown), wherein the thermoplastic polyester elastomer (TPEE)120 has characteristics of high strength, high elasticity, oil resistance, high temperature resistance, radiation resistance, superior dynamic mechanical properties, etc., and has a self-compression ratio of 30% or more, and stable energy-absorbing performance in a range of-40 ℃ to 250 ℃, and the plurality of thermoplastic polyester elastomers 120 are coaxially arranged at intervals, that is, the plurality of thermoplastic polyester elastomers 120 are arranged at intervals along the axial extension direction of the first shell 11, so that an excessive thickness of a single thermoplastic polyester elastomer 120 can be avoided, and the stability of the elastic energy-absorbing unit 12 in axial compression energy-absorbing can be effectively improved; each baffle plate is arranged between two adjacent thermoplastic polyester elastomers 120, namely, the two adjacent thermoplastic polyester elastomers 120 are separated by one baffle plate, and the surface area of the baffle plate is greater than or equal to the cross-sectional area of the thermoplastic polyester elastomer 120, so that the stress uniformity of each thermoplastic polyester elastomer 120 can be improved, the stability of the energy absorption unit 12 in axial compression energy absorption can be further improved, and the two adjacent thermoplastic polyester elastomers 120 can be effectively prevented from rubbing against each other to cause abrasion. Of course, in other embodiments of the present invention, the thermoplastic polyester elastomer 120 may be replaced by rubber or the like, as the case may be and as desired.

The plastic energy absorption unit 32 is preferably a metal honeycomb material, is made by stacking or stretching metal plates, and has the characteristics of good symmetry, stable and reliable structure, stable and orderly compression process, high energy absorption efficiency and the like. In the process of buffering and energy absorption, the plastic energy absorption unit 32 generates plastic deformation along the axial direction, and converts the impact energy into metal plastic deformation energy. Of course, in other embodiments of the present invention, the plastic energy absorbing unit 32 may be formed by expanding, contracting, planing, or other metal deformation.

The working principle of the multi-stage landing buffering energy absorption device 1 is illustrated by taking the example that the device is installed on a carrier rocket: referring to fig. 5, when the carrier rocket normally lands vertically, the first-stage energy absorbing mechanism 10 starts to work when the landing leg contacts the ground, the elastic energy absorbing unit 12 is pushed by the first end 21 to deform in a compression manner along the axial direction of the multi-stage landing buffering energy absorbing device 1, and impact energy is converted into internal energy and heat energy to be consumed through friction between macromolecules of the elastic energy absorbing unit, so that the carrier rocket is softly landed; if the rocket body attitude control is improper or the influence of external environment parameters is large in the process of landing the carrier rocket, when the trigger force reaches a second-stage trigger force F1, the elastic energy absorption unit 12 is compressed to the limit, a first-stage energy absorption stroke S1 is completed, the second-stage energy absorption mechanism 20 starts to work, and the impact energy of the elastic daub piece filled inside is converted into internal energy and heat energy to be consumed, so that the landing attitude of the rocket body is corrected, and the influence of the external environment parameters is eliminated; if the situations of attitude control failure, abnormal landing and the like occur in the landing process of the carrier rocket, when the trigger force reaches the third-stage trigger force F2, the elastic daub reaches the deformation limit, the second-stage energy absorption stroke S2 is completed, in order to further consume the impact energy of the ground, the third-stage energy absorption mechanism 30 starts to work, the plastic energy absorption unit 32 is pushed by the second end 22 to generate crumpling deformation along the axial direction of the multi-stage landing buffering energy absorption device 1, and the impact energy is converted into metal deformation energy to be consumed through self plastic crumpling, so that the emergency landing of the carrier rocket is realized.

The utility model provides a multistage landing buffering energy-absorbing device 1, tertiary energy-absorbing mechanism has been adopted, provide the buffering energy-absorbing of conventional operating mode through first order energy-absorbing mechanism 10, ensure the soft landing of aircraft, provide the buffering energy-absorbing of unconventional nonemergency operating mode through second level energy-absorbing mechanism 20, ensure the steady landing of aircraft, provide the buffering energy-absorbing of unconventional urgent operating mode through third level energy-absorbing mechanism 30, ensure the safe landing of aircraft, thereby it is difficult to satisfy the carrier rocket to have solved landing buffering energy-absorbing device effectively, the technical problem that aircraft such as aircraft reply complicated landing operating mode requirement, the security and the success rate of aircraft landing have been promoted.

Optionally, referring to fig. 1, as a specific embodiment of the multi-stage landing buffering energy absorption apparatus provided by the present invention, the second shell 31 includes a second shell 311 and a second end cap 312, wherein the second end cap 312 is covered on one end of the second shell 311. Specifically, second shell 31 includes at least one second end cap 312, second end cap 312 may be capped at an end near second stage energy absorbing mechanism 20 or an end away from second stage energy absorbing mechanism 20, and second end cap 312 is detachably connected to second shell 311 by a thread or a bolt. Therefore, after the aircraft completes emergency landing, the plastic energy absorption unit 32 can be conveniently replaced by opening the second end cover 312, and the multi-stage landing buffering energy absorption device 1 can be reused, so that the operation cost of the aircraft is effectively reduced. It will be appreciated that to facilitate servicing of first stage energy absorption mechanism 10, first shell 11 may include a first shell 111 and a first end cap 112, first end cap 112 capping one end of first shell 111.

Optionally, as the utility model provides a multistage landing buffering energy-absorbing device's a specific implementation way, the aforesaid separates the separation blade and is the sheetmetal, it adopts metal material to make to separate the separation blade promptly, because the surface that separates the separation blade is smooth, can reduce the frictional force between separation blade and the thermoplastic polyester elastomer 120 effectively, the wearing and tearing of thermoplastic polyester elastomer 120 have been reduced, and because metal material has fine heat conductivility, it can lead away the heat energy of thermoplastic polyester elastomer 120 compression deformation conversion fast to separate the separation blade, the energy consumption efficiency of elasticity energy-absorbing unit 12 has been improved.

Alternatively, referring to fig. 1, as a specific embodiment of the multistage landing buffering energy absorption device provided by the present invention, the second stage energy absorption mechanism 20 includes a first cylinder 23, a second cylinder 24, a third end cap 25 and a piston rod 26, wherein, the closed end of the first cylinder 23 is one of the first end 21 and the second end 22, the open end of the second cylinder 24 extends from the open end of the first cylinder 23 and is limited in the inner cavity of the first cylinder 23, the closed end of the second cylinder 24 is the other one of the first end 21 and the second end 22, the inner cavity of the second cylinder 24 is filled with elastic cement, the third end cap 25 is covered on the open end of the second cylinder 24, the piston part 261 of the piston rod 26 is accommodated in the inner cavity of the second cylinder 24, and the piston portion 261 is close to the third end cover 25, the rod portion 262 of the piston rod 26 passes through the third end cover 25 to be tightly connected with the inner wall of the first cylinder 23. Specifically, the closed end of the first cylinder body 23 is detachably connected to the body of the first cylinder body 23, which is beneficial for the second cylinder body 24 to be installed in the first cylinder body 23, the second cylinder body 24 is coaxial with the first cylinder body 23 and is in clearance fit with the first cylinder body 23, the second cylinder body 24 can move along the length extending direction of the first cylinder body 23, one end of the rod part 262 is fastened to the piston part 261 or is integrally formed, the other end of the rod part 262 is fastened to the inner end face of the closed end of the first cylinder body 23, the third end cover 25 is provided with a mounting hole for the rod part 262 to penetrate, a sealing ring is arranged on the hole wall of the mounting hole, so that the elastic daub can be ensured not to flow out from the clearance between the rod part 262 and the mounting hole, in the initial state, the piston part 261 is close to the third end cover 25, and the open end of the. When the axial impact force applied to the second-stage energy absorbing mechanism 20 is equal to or greater than the second-stage triggering force F1, the second cylinder 24 extends into the inner cavity of the first cylinder 23 along the length extending direction of the first cylinder 23, at this time, the closed end of the first cylinder 23 pushes the rod portion 262, the rod portion 262 pushes the piston portion 261 to extrude the elastic daub in the second cylinder 24, the elastic daub is driven to flow through the throttling gap 241 to generate a damping force, and the impact energy is converted into the internal energy and the heat energy of the elastic daub to be consumed.

Optionally, please refer to fig. 1, as a specific embodiment of the multi-stage landing buffering energy-absorbing device provided in the present invention, a cross-sectional area of the first end 21 and a cross-sectional area of the second end 22 are respectively greater than a cross-sectional area of the body of the first cylinder 23, meanwhile, a first mounting hole 110 is disposed at one end of the first housing 11, a second mounting hole 310 is disposed at one end of the second housing 31, and an outer contour shape of the first mounting hole 110 and an outer contour shape of the second mounting hole 310 are adapted to an outer contour shape of the body of the first cylinder 23. Specifically, the cross-sectional area of the first end 21 is equal to the cross-sectional area of the second end 22, which is beneficial to design and process the first end 21 and the second end 22, and the aperture of the first mounting hole 110 and the aperture of the second mounting hole 310 are respectively smaller than the width of the first end 21, so that the first end 21 is limited in the inner cavity of the first housing 11, and the second end 22 is limited in the inner cavity of the second housing 31; because the second-stage energy absorption mechanism 20 is provided with the first end 21 and the second end 22 with larger cross-sectional areas, the axial impact force acts on the elastic energy absorption unit 12 and the plastic energy absorption unit 32 more uniformly, and the buffering and energy absorption process of the multi-stage landing buffering and energy absorption device 1 is more stable.

Optionally, please refer to fig. 4, as a specific embodiment of the multi-stage landing buffering energy-absorbing device provided in the present invention, a first flow-limiting structure 250 is disposed on the third end cap 25, the first flow-limiting structure 250 is used for injecting the elastic daub and limiting the flow of the elastic daub out of the inner cavity of the second cylinder 24, meanwhile, a second flow-limiting structure 2610 is disposed on the piston portion 261, and the second flow-limiting structure 2610 is used for allowing the elastic daub to flow into a side away from the third end cap 25 from a side close to the third end cap 25. Specifically, the first flow restriction structure 250 extends through opposite end surfaces of the third end cover 25, and the second flow restriction structure 2610 extends through opposite end surfaces of the piston portion 261 of the piston rod 26. When the elastic mastic is injected into the second cylinder 24 through the first flow restriction structure 250, the elastic mastic may rapidly flow into the inner cavity of the side away from the third end cap 25 through the second flow restriction structure 2610 under the preset pressure, and maintain the piston portion 261 at a position close to the third end cap 25; after the filling of the elastic daub is completed, the first flow limiting structure 250 can limit the outflow of the elastic daub; when axial impact occurs, the second flow-limiting structure 2610 can limit the elastic daub to flow back to the inner cavity near one side of the third end cover 25, so that the elastic daub flows into the inner cavity near one side of the third end cover 25 from the throttling gap 241 under the driving of the piston part 261, and then the throttling damping effect is achieved, and the impact energy is converted into heat energy to be consumed.

Optionally, please refer to fig. 4, as an embodiment of the multi-stage landing buffering energy-absorbing device provided in the present invention, the first current-limiting structure 250 includes a first receiving groove 251, a first through hole 252, a first steel ball 253, and a first hollow stud, the second current-limiting structure 2610 includes a second receiving groove 2611, a second through hole 2612, a second steel ball 2613, and a second hollow stud, wherein the first receiving groove 251 is recessed on an inner end surface of the third end cap 25, the first through hole 252 penetrates through an outer end surface of the third end cap 25 and is communicated with the first receiving groove 251, the first steel ball 253 is received in the first receiving groove 251 and can cover the first through hole 252, and the first hollow stud (not shown) is rotatably disposed on a notch of the first receiving groove 251 to prevent the first steel ball 253 from coming out of the first receiving groove 251; the second receiving groove 2611 is concavely disposed on an end surface of the piston portion 261 facing the third end cap 25, the second through hole 2612 penetrates through the end surface of the piston portion 261 away from the third end cap 25 and is communicated with the second receiving groove 2611, the second steel ball 2613 is received in the second receiving groove 2611 and can cover the second through hole 2612, and a second hollow stud (not shown) is screwed on a notch of the second receiving groove 2611 to prevent the second steel ball 2613 from being disengaged from the second receiving groove 2611. Specifically, a channel formed by the connection of the first receiving groove 251 and the first through hole 252 and a channel formed by the connection of the second receiving groove 2611 and the second through hole 2612 respectively penetrate through the third end cover 25 and the piston portion 261, wherein the width of the first receiving groove 251 is larger than the aperture of the first through hole 252, the width of the second receiving groove 2611 is larger than the aperture of the second through hole 2612, the outer diameter of the first steel ball 253 is matched with the width of the first receiving groove 251, the outer diameter of the second steel ball 2613 is matched with the width of the second receiving groove 2611, an internal thread is arranged at the notch of the first receiving groove 251, the internal thread is in threaded connection with the external thread of the first hollow stud, an internal thread is arranged at the notch of the second receiving groove 2611, the internal thread is in threaded connection with the external thread of the second hollow stud, the first steel ball 253 can move back and forth between the side of the first receiving groove 251, which is connected with the first through hole 252, the second steel ball 2613 can move back and forth between the second hollow stud and the side where the second accommodating groove 2611 is connected with the second through hole 2612, so that the first flow limiting structure 250 and the second flow limiting structure 2610 respectively play a role of a one-way valve.

Optionally, please refer to fig. 1, as a specific embodiment of the multi-stage landing buffering energy-absorbing device provided in the present invention, a limiting flange 230 is disposed on the inner wall of the first cylinder 23, and meanwhile, a limiting groove 242 is disposed on the outer wall of the second cylinder 24, the limiting groove 242 extends from the open end of the second cylinder 24 to the closed end of the second cylinder 24, and the limiting flange 230 extends into the limiting groove 242 to form a limiting position. Specifically, the limiting flange 230 extends circumferentially along the inner wall of the open end of the first cylinder 23, the limiting groove 242 extends circumferentially along the outer wall of the second cylinder 24, and when the multi-stage landing buffering and energy absorbing device 1 is in the initial position, the limiting flange 230 overlaps with a groove wall of the limiting groove 242 on one side close to the open end of the second cylinder 24 to limit the second cylinder 24 in the inner cavity of the first cylinder 23.

The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.

Claims

1. Multistage landing buffering energy-absorbing device, its characterized in that includes:

2. The multi-stage landing cushioning energy absorber device of claim 1, wherein said second outer shell comprises a second shell and a second end cap, said second end cap capping an end of said second shell.

3. The multi-stage landing buffer energy absorber of claim 2, wherein said elastic energy absorber unit comprises:

4. The multi-stage landing cushioning energy absorber of claim 3, wherein said barrier sheet is a metal sheet.

5. The multi-stage landing cushioning energy absorber device of claim 2, wherein said plastic energy absorber unit is a metal honeycomb material.

6. The multi-stage landing cushioning energy absorber device of any of claims 1-5, wherein said second stage energy absorber mechanism comprises:

7. The multi-stage landing buffer energy absorption device according to claim 6, wherein the cross-sectional area of the first end and the cross-sectional area of the second end are respectively larger than the cross-sectional area of the body of the first cylinder, a first mounting hole is formed at one end of the first housing, a second mounting hole is formed at one end of the second housing, and the outer contour shape of the first mounting hole and the outer contour shape of the second mounting hole are matched with the outer contour shape of the body of the first cylinder.

8. The multi-stage landing cushioning energy-absorbing device according to claim 6, wherein a first flow-limiting structure is disposed on said third end cap, said first flow-limiting structure is used for injecting said elastic daub and limiting said elastic daub from flowing out of an inner cavity of said second cylinder, a second flow-limiting structure is disposed on said piston portion, said second flow-limiting structure is used for allowing said elastic daub to flow into a side away from said third end cap from a side close to said third end cap.

9. The multi-stage landing buffer energy absorber of claim 8, wherein said first current limiting structure comprises:

the second current limiting structure includes:

10. The multi-stage landing buffering energy-absorbing device according to claim 6, wherein a limiting flange is provided on an inner wall of the first cylinder, a limiting groove is provided on an outer wall of the second cylinder, the limiting groove extends from an open end of the second cylinder to a closed end of the second cylinder, and the limiting flange extends into the limiting groove to form a limiting.