Vertical vibration damping and buffering mechanism for rocket body with large buffering capacity in small space

Abstract

The invention relates to a vertical damping and buffering mechanism for a rocket body with large buffering capacity in a small space, and belongs to the technical field of carrier rocket reuse. The vertical vibration reduction buffering mechanism comprises an unfolding piece, a locking piece, a connecting piece, a buffering device, a landing piece and an unlocking piece, and through the ingenious structural design, the vertical vibration reduction buffering mechanism is light in weight, easy to operate and replace, capable of effectively improving mechanism installation, replacement and maintenance efficiency, capable of reducing machining cost and high in reliability. The vertical vibration reduction buffer mechanism is overturned, locked and stored in the tail section of the rocket body at the rising section of the rocket and does not protrude out of the rocket body, devices such as a pneumatic cover do not need to be additionally arranged, the external space of the rocket body is not occupied, the pneumatic appearance of the rocket body is maintained, and the occupied internal space of the rocket body is small when the vertical vibration reduction buffer mechanism is stored; and a layered crushing buffering method is preferably adopted, so that the structure size can be reduced on the premise of ensuring the bearing and buffering performance.

Description

Technical Field

[0001] The invention relates to a buffer mechanism of a landing mechanism of a carrier rocket, in particular to a vertical vibration reduction buffer mechanism of a rocket body with a large buffering capacity in a small space, and belongs to the technical field of carrier rocket reuse. Background Art

[0002] As the key to the vertical recovery of launch vehicles, the landing mechanism buffer structure and performance will directly affect the success or failure of the vertical recovery mission. At present, the vertical recovery of launch vehicles generally adopts the recovery scheme of the folding leg landing buffer mechanism, and there are usually two designs for its buffer mechanism. One is a hydraulic-based buffer form, usually a multi-section rod landing leg mechanism. The hydraulic buffer mechanism is placed inside the last section of the multi-section rod or used alone as a supporting auxiliary rod. It occupies a large space inside or outside the rocket body and has a large weight. The other is a buffer form based on metal crushing such as aluminum honeycomb, which is also integrated into the last section of the multi-section rod landing leg mechanism or used alone as a supporting auxiliary rod. It also needs to occupy a large space inside or outside the rocket body, and the processing cost of aluminum honeycomb is relatively high. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the above-mentioned deficiencies of the prior art and provide a vertical vibration reduction and buffering mechanism for a rocket body with a large buffering capacity in a small space. The buffering mechanism has the characteristics of small size, large buffering capacity, light weight, easy retraction, easy replacement and low cost. It can be used for the wide-range landing buffering conditions of a space vehicle and solves the problems of large size, heavy weight and difficult maintenance and replacement of the vertical vibration reduction and buffering mechanism of a carrier rocket.

[0004] The above-mentioned purpose of the present invention is mainly achieved through the following technical solutions:

[0005] A vertical vibration reduction and buffering mechanism for an arrow body with a large buffering capacity in a small space, comprising:

[0006] The unfolding member is arranged on the upper surface of the connecting member and connected to the arrow body, so that the vertical vibration reduction and buffering mechanism can rotate around the unfolding member;

[0007] A locking piece, which is arranged on the side wall of the connecting piece and cooperates with the locking groove of the arrow body to complete the locking in place;

[0008] A connecting piece connected to the first-stage buffer assembly of the buffer device and used for bearing during the landing buffering of the rocket body;

[0009] A buffer device, used for vibration reduction and buffering when the rocket body lands, comprises n-stage buffer components arranged in sequence, and a connecting plate is provided between two adjacent stages of buffer components, wherein n is a positive integer, and n≥2;

[0010] The landing piece is connected to the nth-level buffer assembly of the buffer device and is used to support and carry the rocket body and the vertical vibration damping buffer mechanism during the landing and buffering process of the rocket body;

[0011] The unlocking member is arranged on the landing member and is used for locking and unlocking the connection between the vertical vibration damping and buffering mechanism and the rocket body.

[0012] In the above-mentioned arrow body vertical vibration damping and buffering mechanism with large buffering capacity in a small space, the locking member is a pin structure, which cooperates with the claw assembly arranged inside the arrow body locking groove to achieve locking in place.

[0013] In the above-mentioned vertical vibration damping and buffering mechanism of the arrow body with large buffering capacity in a small space, among the two adjacent buffer components of the buffer device, one of the buffer components is a cylindrical structure, and a first strip groove is formed from top to bottom at every interval along the annular outer wall surface, the cross-section of the first strip groove is rectangular, and a plurality of through holes are opened on the cylindrical outer wall surface; the other buffer component is a cylindrical structure, and a plurality of second strip grooves are formed from top to bottom along the annular outer wall surface, the cross-section of the second strip groove is triangular, and a plurality of through holes are opened on the cylindrical outer wall surface.

[0014] In the above-mentioned arrow body vertical vibration damping and buffering mechanism with large buffering capacity in a small space, the multiple groups of through holes in the cylindrical structure of the two buffer components are arranged at intervals along the annular outer wall surface, and the apertures of the through holes gradually increase from top to bottom.

[0015] In the above-mentioned vertical vibration damping and buffering mechanism of the rocket body with large buffering capacity in a small space, the buffer device includes two buffer components. The first buffer component connected to the connecting piece is a cylindrical structure, and a first strip groove penetrating from top to bottom is formed at a certain distance along the annular outer wall surface. The cross-section of the first strip groove is rectangular, and a plurality of groups of through holes are arranged at intervals on the cylindrical outer wall surface, and the aperture of the through hole gradually increases from top to bottom; the second buffer component connected to the landing piece is a cylindrical structure, and a plurality of second strip grooves penetrating from top to bottom are formed along the annular outer wall surface. The cross-section of the second strip groove is triangular, and a plurality of groups of through holes are arranged at intervals on the cylindrical outer wall surface, and the aperture of the through hole gradually increases from top to bottom.

[0016] In the above-mentioned vertical vibration damping and buffering mechanism of the rocket body with large buffering capacity in a small space, the landing part includes a landing disc and a reinforcing rib plate arranged on the landing disc, the reinforcing rib plate is connected to the buffer device, and the unlocking part is installed on the reinforcing rib plate.

[0017] In the above-mentioned arrow body vertical vibration damping and buffering mechanism with large buffering capacity in a small space, the unlocking member is an unlocking support ear with a through hole inside, which cooperates with the axle pin of the arrow body to realize the connection locking and unlocking between the vertical vibration damping and buffering mechanism and the arrow body structure.

[0018] The above-mentioned vertical vibration damping and buffering mechanism for the rocket body with large buffering capacity in a small space also includes a buffer pad that is deployed into place and bonded to the upper surface of the connecting part, so as to achieve a buffering effect between the vertical vibration damping and buffering mechanism and the rocket body structure when deployed into place, thereby reducing the impact of the gravity-driven vertical vibration damping and buffering mechanism on the rocket body structure during the deployment process.

[0019] The above-mentioned vertical vibration damping and buffering mechanism of the rocket body with large buffering capacity in a small space also includes a landing buffer pad, which is bonded to the lower surface of the landing plate of the landing piece and is used to further dampen and buffer the vertical vibration damping and buffering mechanism when it lands.

[0020] In the above-mentioned vertical vibration damping and buffering mechanism of the rocket body with large buffering capacity in a small space, the two adjacent buffering components in the buffering device are screwed together by a connecting plate, the first-stage buffering component is welded or integrally formed with the connecting part, and the nth-stage buffering component is welded or integrally formed with the landing part.

[0021] In the above-mentioned vertical vibration damping and buffering mechanism of the rocket body with large buffering capacity in a small space, the deploying member, locking member, connecting member, buffer device, landing member and unlocking member are all made of metal, including stainless steel or aluminum alloy.

[0022] The method for realizing the above-mentioned vertical vibration reduction and buffering mechanism of the rocket body with large buffering capacity in a small space includes:

[0023] The unlocking piece is matched with the shaft pin of the arrow body by a pin puller to complete the initial locking;

[0024] After the rocket body lands, the buffer device absorbs the landing impact energy through layered crushing to achieve buffering;

[0025] Upon receiving the unlocking command, the pin puller completes the pin pulling action, and the shaft pin is pulled out from the unlocking member, completing the unlocking;

[0026] The vertical vibration damping and buffering mechanism is deployed by its own gravity;

[0027] The locking piece is matched with the locking groove on the arrow body to achieve locking in place.

[0028] Compared with the prior art, the present invention has at least the following beneficial effects:

[0029] (1) The vertical vibration damping and buffering mechanism provided in the embodiment of the present invention includes a buffering device having n-stage buffering components, which is suitable for wide-range landing buffering conditions of a space vehicle, can achieve large buffering capacity with a small volume, and can realize lean buffering design according to requirements.

[0030] (2) The vertical vibration damping and buffering mechanism provided in the embodiment of the present invention includes an unfolding member, a locking member, a connecting member, a buffer device, a landing member and an unlocking member. Through the ingenious structural design, it is light in weight, easy to operate and easy to replace, which can effectively improve the efficiency of mechanism installation, replacement and maintenance and reduce processing costs.

[0031] (3) The vertical vibration reduction and buffering mechanism provided in the embodiment of the present invention is flipped and locked in the tail section of the rocket body during the rocket's ascent phase, and does not protrude from the outside of the rocket body. No additional devices such as an aerodynamic cover are required, and the external space of the rocket body is not occupied. The aerodynamic shape of the rocket body is maintained, and the internal space of the rocket body occupied when folded is also relatively small. In addition, the layered crushing buffering method is preferably used to reduce the structural size while ensuring the load-bearing and buffering performance.

[0032] (4) The vertical vibration damping and buffering mechanism provided in the embodiment of the present invention is driven to flip and unfold by gravity and inertia, and is locked by a locking member when in place, without the need to separately set up a driving energy source and a thrust energy source;

[0033] (5) The vertical vibration damping and buffering mechanism provided in the embodiment of the present invention is locked to the ring frame at the bottom of the tail section after being deployed, and can directly transmit the support reaction force to the rocket body shell section to achieve load-bearing. Therefore, there is no need to set additional joints on the outer wall of the rocket body and to perform local reinforcement inside the shell section. The load-bearing can be achieved directly through the shell section, and there is no need to set joints and additional reinforcement structures on the rocket body structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The vertical vibration damping and buffering mechanism structure in the embodiment of the present invention is shown in FIG. Figure 1 ;

[0035] Figure 2 The vertical vibration damping and buffering mechanism structure in the embodiment of the present invention is shown in FIG. Figure 2 ;

[0036] Figure 3 1 is a diagram of the folded and unfolded states of the vertical vibration damping and buffering mechanism in an embodiment of the present invention. DETAILED DESCRIPTION

[0037] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0038] like Figure 1 , 2 As shown, the present invention takes the buffer device of the vertical vibration damping buffer mechanism including two-stage buffer components as an example for description, and the specific vertical vibration damping buffer mechanism includes an unfolding shaft 1, an unfolding in-position buffer pad 2, an in-position locking pin 3, a connecting cover 4, a buffer component 5, a landing plate 6, a landing buffer pad 7, and an unlocking lug 8, wherein the buffer component 5 includes an upper buffer component 5-1, a flange connecting plate 5-2, and a lower buffer component 5-3. The unfolding shaft 1, the in-position locking pin 3, the connecting cover 4, the buffer component 5, the landing plate 6, and the unlocking lug 8 are all made of metal, such as stainless steel or aluminum alloy.

[0039] Among them, the vertical vibration damping and buffering mechanism is connected to the arrow body through the deployment axis 1, so that the vertical vibration damping and buffering mechanism can rotate around the deployment axis 1. The deployment axis 1 is used to realize the connection between the vertical vibration damping and buffering mechanism as a whole and the arrow body structure, and to realize the folding and unfolding actions of the vertical vibration damping and buffering mechanism.

[0040] The connecting cover 4 is composed of a connecting plate and an annular wall extending along the lower surface of the connecting plate, the deployment shaft 1 is installed on the upper surface of the connecting plate, the deployed buffer pad 2 is also bonded to the upper surface of the connecting plate, and the in-position locking pin 3 is arranged on the annular wall. The deployed buffer pad 2 is used to achieve the buffering effect between the vertical vibration damping buffer mechanism and the arrow body structure when deployed, and reduce the impact of the gravity-driven vertical vibration damping buffer mechanism on the arrow body structure during the deployment process.

[0041] The vertical vibration damping and buffering mechanism completes the locking function in place by cooperating with the locking slot provided on the arrow body through the locking pin 3 in place, and a claw assembly is provided inside the arrow body locking slot to lock the locking pin 3 in place. The locking pin 3 in place is used to realize the locking function between the vertical vibration damping and buffering mechanism and the arrow body structure after being deployed in place.

[0042] The upper buffer assembly 5-1 is welded or integrally formed with the lower surface of the connection plate of the connection cover 4; the upper buffer assembly 5-1 is screwed with the lower buffer assembly 5-3 through the flange connection plate 5-2; the lower buffer assembly 5-3 is welded or integrally formed with the landing plate 6. The connection cover 4 is used to connect the rocket body and the buffer assembly 5 through the deployment shaft 1, and is also used for bearing during landing buffering.

[0043] The upper buffer component 5-1 is a cylindrical structure, and a first strip groove is formed along the annular outer wall at intervals (preferably at equal intervals) and runs from top to bottom. The cross section of the first strip groove is rectangular, and multiple groups of through holes are arranged at intervals on the cylindrical outer wall, and the aperture of the through hole gradually increases from top to bottom. The lower buffer component 5-3 is a cylindrical structure, and multiple second strip grooves are formed along the annular outer wall and run from top to bottom. The cross section of the second strip groove is triangular, and multiple groups of through holes are arranged at intervals on the cylindrical outer wall, and the aperture of the through hole gradually increases from top to bottom. In this embodiment, the height of the upper buffer component 5-1 is greater than that of the lower buffer component 5-3.

[0044] The buffer assembly 5 is used to achieve vibration reduction and buffering when the rocket body lands vertically. The main working principle is as follows:

[0045] 1. The landing impact energy is absorbed by layered crushing of two-stage sheet metal parts with gradient-sized holes to achieve cushioning.

[0046] 2. According to the design requirements such as the weight of the rocket body and the internal space size, the number of sheet metal parts can be increased or decreased, the size of the holes can be changed, or the height and diameter of each level of sheet metal parts can be changed to achieve targeted and precise design of the buffer effect.

[0047] The landing disc 6 is provided with a reinforcing rib plate, which is connected to the lower buffer assembly 5-3 of the buffer device 5, and the unlocking lug 8 is installed on the reinforcing rib plate. The landing disc 6 is used to support and carry the arrow body and the mechanism during the vertical landing and buffering process of the arrow body.

[0048] The landing cushion 7 is bonded to the lower surface of the landing plate 6, and the landing cushion 7 is used to further reduce vibration and buffer the vertical vibration reduction and buffering mechanism when it lands.

[0049] The unlocking lug 8 is provided with a through hole inside, which cooperates with the shaft pin of the arrow body to realize the connection locking and unlocking between the vertical vibration damping and buffering mechanism and the arrow body structure. The main working principle is that the pin puller cooperates with the unlocking lug 8 to complete the initial locking function. After receiving the unlocking instruction, the pin puller completes the pin pulling action, and the shaft pin is pulled out from the unlocking lug 8, releasing the movement restriction of the unlocking lug 8, and releasing the restriction on the rotational freedom of the vertical vibration damping and buffering mechanism around the deployment axis 1, and completing the unlocking.

[0050] The working sequence of the vertical vibration damping and buffering mechanism in the embodiment of the present invention is as follows:

[0051] Initial locking: the unlocking lug 8 is matched with the arrow body by a pin puller to complete the initial locking function.

[0052] After the rocket body lands, the buffer device absorbs the landing impact energy through layered crushing to achieve buffering;

[0053] After receiving the unlocking instruction, the pin puller completes the pin pulling action, and the shaft pin is pulled out from the unlocking lug 8, thereby releasing the movement restriction on the unlocking lug 8 and the restriction on the rotational freedom of the vertical vibration damping and buffering mechanism around the deployment axis 1, and completing the unlocking;

[0054] Unlock and unfold. After unlocking, the vertical vibration damping and buffering mechanism unfolds by its own gravity.

[0055] The locking in place function is achieved by the locking pin 3 cooperating with the locking groove arranged on the arrow body.

[0056] The vertical vibration damping and buffering mechanism in the embodiment of the present invention has the following characteristics:

[0057] 1. The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention is suitable for wide-range landing buffering conditions of aerospace vehicles, can achieve large buffering capabilities with a small volume, and can realize lean buffering design according to requirements.

[0058] Implementation principle:

[0059] The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention realizes buffering by means of layered crushing and energy absorption of the metal structure. The ability of absorbing landing impact energy through deformation is relatively strong, and better buffering performance can be achieved.

[0060] The load-bearing performance and buffering characteristics of the vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention can be designed and controlled by adjusting parameters such as the number of sheet metal parts, the diameter of the gradient holes, the height and diameter of each level of sheet metal parts, and the depth of the pleated structure.

[0061] 2. The vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention is light in weight, easy to operate and replace, and can effectively improve the efficiency of installation, replacement and maintenance of the mechanism and reduce processing costs.

[0062] Implementation principle:

[0063] The pleated structure designed in the vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention is similar to a weight-reducing groove, which can achieve weight reduction under the premise of ensuring the bearing performance. In addition, the designed gradient hole can also achieve weight reduction.

[0064] The vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention is unlocked by a pin puller and locked by a spring pin. The above mechanism and corresponding interface are relatively simple, light in weight, and easy to install and operate.

[0065] The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention is connected to the arrow body only through the deployment axis, and is easy to install and replace.

[0066] The pin puller of the vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention can be driven by non-pyrotechnic energy, such as gas drive, electromagnetic, etc., and has the advantages of being reusable, low impact, and detectable.

[0067] 3. The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention does not occupy the external space of the arrow body, maintains the aerodynamic shape of the arrow body, and occupies a relatively small internal space of the arrow body when folded.

[0068] Implementation principle:

[0069] The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention is flipped and locked in the tail section of the rocket body during the rocket's ascent phase, does not protrude from the outside of the rocket body, and does not require additional devices such as an aerodynamic cover.

[0070] The overall structure of the vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention is used for both buffering and bearing, without any other redundant large-size structural design, thus realizing miniaturization of the mechanism.

[0071] The metal structure layered crushing buffering method adopted by the vertical vibration damping buffer mechanism proposed in the embodiment of the present invention can reduce the structure size while ensuring the bearing and buffering performance.

[0072] 4. The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention does not need to be provided with a separate driving energy source and a thrust energy source.

[0073] Implementation principle:

[0074] The vertical vibration reduction and buffering mechanism proposed in the embodiment of the present invention is driven to flip and unfold by gravity and inertia, and is locked by the spring pin principle when in place, without the need to separately set up a driving energy source and a thrust energy source.

[0075] 5. The vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention can directly realize load-bearing through the shell segment, without the need to set joints and additional reinforcement structures on the rocket body structure.

[0076] Implementation principle:

[0077] The vertical vibration damping and buffering mechanism proposed in the embodiment of the present invention is flipped and unfolded and locked to the ring frame at the bottom of the tail section, and can directly transmit the support reaction force to the rocket body shell section to achieve load bearing. Therefore, there is no need to set additional joints on the outer wall of the rocket body and locally strengthen the inside of the shell section.

[0078] The above description is only the best specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

[0079] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A vertical vibration damping and buffering mechanism for a rocket body with large buffering capacity in a small space, characterized in that: include: The unfolding member is arranged on the upper surface of the connecting member and connected to the arrow body, so that the vertical vibration reduction and buffering mechanism can rotate around the unfolding member; A locking piece, which is arranged on the side wall of the connecting piece and cooperates with the locking groove of the arrow body to complete the locking in place; A connecting piece connected to the first-stage buffer assembly of the buffer device and used for bearing during the landing buffering of the rocket body; A buffer device, used for vibration reduction and buffering when the rocket body lands, comprises n-stage buffer components arranged in sequence, and a connecting plate is provided between two adjacent stages of buffer components, wherein n is a positive integer, and n≥2; The landing piece is connected to the nth-level buffer assembly of the buffer device and is used to support and carry the rocket body and the vertical vibration damping buffer mechanism during the landing and buffering process of the rocket body; The unlocking member is arranged on the landing member and is used for locking and unlocking the connection between the vertical vibration damping and buffering mechanism and the rocket body.

2. The vertical vibration damping and buffering mechanism for a rocket body with large buffering capacity in a small space according to claim 1 is characterized in that: The locking piece is a pin structure, which cooperates with a claw assembly arranged inside the arrow body locking groove to achieve locking in place.

3. The vertical vibration damping and buffering mechanism for a rocket body with large buffering capacity in a small space according to claim 1 is characterized in that: Among the two adjacent buffer components of the buffer device, one buffer component is a cylindrical structure, and a first strip groove is formed along the annular outer wall surface at a certain interval from top to bottom, the cross-section of the first strip groove is rectangular, and a plurality of through holes are opened on the cylindrical outer wall surface; the other buffer component is a cylindrical structure, and a plurality of second strip grooves are formed along the annular outer wall surface from top to bottom, the cross-section of the second strip groove is triangular, and a plurality of through holes are opened on the cylindrical outer wall surface.

4. The vertical vibration damping and buffering mechanism for a rocket body with large buffering capacity in a small space according to claim 3 is characterized in that: The multiple groups of through holes of the cylindrical structures of the two buffer components are arranged at intervals along the annular outer wall surface, and the apertures of the through holes gradually increase from top to bottom.

5. The rocket vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 3 is characterized in that: The buffer device includes two buffer components. The first buffer component connected to the connecting piece is a cylindrical structure. A first strip groove is formed along the annular outer wall surface at a certain interval from top to bottom. The cross-section of the first strip groove is rectangular, and a plurality of through holes are arranged at intervals on the cylindrical outer wall surface, and the aperture of the through hole increases gradually from top to bottom. The second buffer component connected to the landing piece is a cylindrical structure. A plurality of second strip grooves are formed along the annular outer wall surface from top to bottom. The cross-section of the second strip groove is triangular, and a plurality of through holes are arranged at intervals on the cylindrical outer wall surface, and the aperture of the through hole increases gradually from top to bottom.

6. The rocket body vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 1 is characterized in that: The landing piece includes a landing disc and a reinforcing rib plate arranged on the landing disc, the reinforcing rib plate is connected to the buffer device, and the unlocking piece is installed on the reinforcing rib plate.

7. The rocket vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 1 is characterized in that: The unlocking piece is an unlocking support ear, which is provided with a through hole inside and cooperates with the shaft pin of the arrow body to realize the connection locking and unlocking between the vertical vibration reduction and buffering mechanism and the arrow body structure.

8. The rocket body vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 1 is characterized in that: It also includes a deployed buffer pad, which is bonded to the upper surface of the connecting piece to achieve a buffering effect between the vertical vibration damping and buffering mechanism and the arrow body structure when deployed, thereby reducing the impact of the gravity-driven vertical vibration damping and buffering mechanism on the arrow body structure during the deployment process.

9. The rocket body vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 1, characterized in that: It also includes a landing cushion, which is bonded to the lower surface of the landing plate of the landing piece and is used to further reduce vibration and buffer the vertical vibration reduction and buffering mechanism when it lands.

10. The rocket body vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 1, characterized in that: Two adjacent buffer components in the buffer device are screwed together via a connecting plate, the first buffer component is welded or integrally formed with the connecting piece, and the nth buffer component is welded or integrally formed with the landing piece.

11. The rocket body vertical vibration damping and buffering mechanism with large buffering capacity in a small space according to claim 1, characterized in that: The unfolding member, locking member, connecting member, buffer device, landing member and unlocking member are all made of metal, including stainless steel or aluminum alloy.

12. The method for realizing the vertical vibration damping and buffering mechanism of a rocket body with large buffering capacity in a small space as claimed in any one of claims 1 to 11, characterized in that: include: The unlocking piece is matched with the shaft pin of the arrow body by a pin puller to complete the initial locking; After the rocket body lands, the buffer device absorbs the landing impact energy through layered crushing to achieve buffering; Upon receiving the unlocking command, the pin puller completes the pin pulling action, and the shaft pin is pulled out from the unlocking member, completing the unlocking; The vertical vibration damping and buffering mechanism is deployed by its own gravity; The locking piece is matched with the locking groove on the arrow body to achieve locking in place.

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