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

Abstract

The present application relates to a kind of big buffering capacity arrow body vertical damping buffer mechanism in small space, belong to the field of reusable launch vehicle;The vertical damping buffer mechanism includes unfolding piece, locking piece, connecting piece, buffer device, landing piece and unlocking piece, with light quality, easy operation, easy replacement by ingenious structure design, can effectively improve mechanism installation, replacement, maintenance efficiency, reduce processing cost, and the vertical damping buffer mechanism is locked in the tail section inside arrow body in rocket ascent segment, not protruding from the outside of arrow body, without additional setting device such as pneumatic cover, without occupying the external space of arrow body, maintain the aerodynamic shape of arrow body, the internal space of arrow body occupied when retracted is also smaller;And preferably adopt layered crush buffering method can reduce structure size under the premise of guaranteeing bearing and buffering performance.

Description

Technical Field

[0001] This invention relates to a landing mechanism buffer mechanism for launch vehicles, specifically a vertical vibration reduction buffer mechanism for rocket bodies with high buffering capacity in a small space, belonging to the field of reusable launch vehicle technology. Background Technology

[0002] As a crucial element for the vertical recovery of launch vehicles, the landing mechanism's cushioning structure and performance directly impact the success or failure of the vertical recovery mission. Currently, vertical recovery of launch vehicles generally employs a folding-leg landing cushioning mechanism, with two typical design schemes. One is a hydraulically based cushioning system, typically a multi-section rod-type landing leg mechanism. The hydraulic cushioning mechanism is located inside the final section of the multi-section rod or used as a separate support rod. This type occupies a significant amount of internal or external space within the launch vehicle and is quite heavy. The other type is based on metal crushing mechanisms such as aluminum honeycomb, also integrated inside the final section of the multi-section rod-type landing leg mechanism or used as a separate support rod. This type also requires a large amount of internal or external space within the launch vehicle, and the processing cost of aluminum honeycomb is relatively high. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the above-mentioned shortcomings of the prior art and provide a vertical vibration damping buffer mechanism for rocket bodies with large buffering capacity in a small space. This buffer mechanism has the characteristics of small size, large buffering capacity, light weight, easy to deploy and retract, easy to replace, and low cost. It can be applied to the wide-range landing buffering conditions of aerospace launch vehicles and solves the problems of large size, heavy weight, and difficult maintenance and replacement of vertical vibration damping buffer mechanisms for launch vehicles.

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

[0005] A vertical vibration damping and buffering mechanism for an arrow body with high buffering capacity in a small space includes:

[0006] The unfolding component is located on the upper surface of the connecting component and is connected to the arrow body, allowing the vertical vibration damping and buffering mechanism to rotate around the unfolding component.

[0007] The locking element is located on the side wall of the connector and engages with the locking groove of the arrow body to achieve a locked position.

[0008] The connector connects to the first-stage buffer assembly of the buffer device and is used to bear the load when the rocket body lands.

[0009] A buffer device for shock absorption during rocket landing includes n-stage buffer components arranged in sequence, with a connecting plate between adjacent buffer components, where n is a positive integer and n≥2;

[0010] The landing component, connected to the nth-stage buffer assembly of the buffer device, is used to support and bear the load of the rocket body and the vertical vibration damping buffer mechanism during the landing and buffering process.

[0011] The unlocking component, located on the landing component, is used for locking and unlocking the connection between the vertical vibration damping mechanism and the rocket body.

[0012] In the above-mentioned vertical vibration damping and buffering mechanism for a rocket body with large buffer capacity in a small space, the locking component is a pin structure, which cooperates with the claw assembly set inside the locking groove of the rocket body to achieve positioning and locking.

[0013] In the aforementioned vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space, one of the two adjacent buffer components of the buffer device is a cylindrical structure with a first strip groove running from top to bottom at intervals along the annular outer wall. The cross-section of the first strip groove is rectangular, and multiple sets of through holes are opened on the cylindrical outer wall. The other buffer component is a cylindrical structure with multiple second strip grooves running from top to bottom along the annular outer wall. The cross-section of the second strip groove is triangular, and multiple sets of through holes are opened on the cylindrical outer wall.

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

[0015] In the aforementioned vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity within a small space, the buffering device includes two buffer components. The first buffer component connected to the connecting member is a cylindrical structure with a first strip groove running from top to bottom at intervals along the annular outer wall. The cross-section of the first strip groove is rectangular, and multiple sets of through holes are arranged at intervals on the cylindrical outer wall, with the diameter of the through holes gradually increasing from top to bottom. The second buffer component connected to the landing member is a cylindrical structure with multiple second strip grooves running from top to bottom along the annular outer wall. The cross-section of the second strip groove is triangular, and multiple sets of through holes are arranged at intervals on the cylindrical outer wall, with the diameter of the through holes gradually increasing from top to bottom.

[0016] In the aforementioned vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity within a small space, the landing component includes a landing disk and a reinforcing rib plate disposed on the landing disk. The reinforcing rib plate is connected to the buffer device, and the unlocking component is installed on the reinforcing rib plate.

[0017] In the aforementioned vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity within a small space, the unlocking component is an unlocking lug with a through hole inside, which cooperates with the shaft pin of the rocket body to realize the connection, locking and unlocking between the vertical vibration damping and buffering mechanism and the rocket body structure.

[0018] The aforementioned 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 position and is bonded to the upper surface of the connector. This pad provides a buffering effect between the vertical vibration damping and buffering mechanism and the rocket body structure when deployed into position, reducing the impact of the gravity-driven vertical vibration damping and buffering mechanism on the rocket body structure during deployment.

[0019] The vertical vibration damping and buffering mechanism for the rocket body with large buffer capacity in the small space also includes a landing buffer pad, which is bonded to the lower surface of the landing disk of the landing component, and is used to further dampen and buffer the vertical vibration damping and buffering mechanism during landing.

[0020] In the above-mentioned vertical vibration damping and buffering mechanism for rocket bodies with large buffering capacity in a small space, adjacent buffer components in the buffer device are connected by connecting plates. The first-level buffer component is welded to the connecting piece or integrally formed, and the nth-level buffer component is welded to the landing piece or integrally formed.

[0021] In the aforementioned vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity within a small space, the deploying component, locking component, connecting component, buffer device, landing component, and unlocking component are all made of metal, including stainless steel or aluminum alloy.

[0022] The method for implementing the above-mentioned vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space includes:

[0023] The initial locking is achieved by engaging the unlocking component with the shaft pin of the arrow body using a pin puller.

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

[0025] Upon receiving the unlocking command, the pin puller completes the pin pulling action, and the pin is pulled out from the unlocking component, thus completing the unlocking process.

[0026] The vertical vibration damping and buffer mechanism deploys under its own gravity.

[0027] The locking mechanism engages with the locking groove on the rocket body to achieve the desired positioning and locking.

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

[0029] (1) The vertical vibration damping buffer mechanism provided in the embodiments of the present invention includes a buffer device with n-level buffer components, which is suitable for the wide-range landing buffer conditions of aerospace launch vehicles, can achieve large buffering capacity with small volume, and can achieve lean design of buffer according to requirements.

[0030] (2) The vertical vibration damping and buffering mechanism provided in the embodiments of the present invention includes an unfolding component, a locking component, a connecting component, a buffer device, a landing component and an unlocking component. Through ingenious structural design, it is lightweight, 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 damping and buffering mechanism provided in this embodiment of the invention flips and locks inside the tail section of the rocket body during the rocket ascent stage, does not protrude outside the rocket body, does not require additional aerodynamic cover or other devices, does not occupy the external space of the rocket body, maintains the aerodynamic shape of the rocket body, and occupies less internal space of the rocket body when retracted; and preferably adopts a layered crushing buffering method to reduce the structural size while ensuring load-bearing and buffering performance.

[0032] (4) The vertical vibration damping and buffering mechanism provided in this embodiment of the invention is driven to flip and unfold by gravity and inertia, and locked by locking parts when in place, without the need to set up driving energy and pushing energy separately.

[0033] (5) The vertical vibration damping and buffering mechanism provided in this embodiment of the invention is locked at the bottom ring frame of the tail section after being unfolded. It 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 or to carry out local reinforcement inside the shell section. The load bearing can be achieved directly through the shell section without setting joints and additional reinforcement structures on the rocket body structure. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of the vertical vibration damping and buffer mechanism in an embodiment of the present invention. Figure 1 ;

[0035] Figure 2 This is a schematic diagram of the vertical vibration damping and buffer mechanism in an embodiment of the present invention. Figure 2 ;

[0036] Figure 3 The diagram shows the retracted and extended states of the vertical vibration damping and buffering mechanism in an embodiment of the present invention. Detailed Implementation

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

[0038] like Figure 1 , 2 As shown, this invention describes a vertical vibration damping and buffering mechanism with a two-stage buffer assembly as an example. Specifically, the vertical vibration damping and buffering mechanism includes an unfolding shaft 1, an unfolded buffer pad 2, a locking pin 3, a connecting cover 4, a buffer assembly 5, a landing plate 6, a landing buffer pad 7, and an unlocking lug 8. The buffer assembly 5 includes an upper buffer assembly 5-1, a flange connecting plate 5-2, and a lower buffer assembly 5-3. The unfolding shaft 1, the locking pin 3, the connecting cover 4, the buffer assembly 5, the landing plate 6, and the unlocking lug 8 are all made of metal, such as stainless steel or aluminum alloy.

[0039] The vertical vibration damping mechanism is connected to the arrow body via the unfolding shaft 1, allowing the vertical vibration damping mechanism to rotate around the unfolding shaft 1. The unfolding shaft 1 is used to connect the vertical vibration damping mechanism to the arrow body structure and to realize the retraction and unfolding of the vertical vibration damping mechanism.

[0040] The connecting cover 4 consists of a connecting plate and an annular cylindrical wall extending along the lower surface of the connecting plate. The unfolding shaft 1 is mounted on the upper surface of the connecting plate, and the unfolding buffer pad 2 is also adhered to the upper surface of the connecting plate. The positioning locking pin 3 is set on the annular cylindrical wall. The unfolding buffer pad 2 is used to achieve the buffering effect between the vertical vibration damping buffer mechanism and the rocket body structure when unfolded, reducing the impact of the gravity-driven vertical vibration damping buffer mechanism on the rocket body structure during the unfolding process.

[0041] The vertical vibration damping mechanism achieves its locking function by engaging a locking pin 3 with a locking groove on the rocket body. A claw assembly inside the locking groove locks the locking pin 3 in place. The locking pin 3 is used to lock the vertical vibration damping mechanism in place with the rocket body structure.

[0042] The upper buffer assembly 5-1 is welded to or integrally formed with the lower surface of the connecting plate of the connecting cover 4; the upper buffer assembly 5-1 and the lower buffer assembly 5-3 are screwed together by the flange connecting plate 5-2; the lower buffer assembly 5-3 is welded to or integrally formed with the landing disk 6. The connecting cover 4 is used to connect the rocket body and the buffer assembly 5 through the deployment shaft 1, and also serves as a load-bearing device during landing.

[0043] The upper buffer assembly 5-1 has a cylindrical structure with first strip-shaped grooves running from top to bottom at intervals (preferably at equal intervals) along its annular outer wall. The cross-section of the first strip-shaped groove is rectangular, and multiple sets of through holes are arranged at intervals on the cylindrical outer wall, with the diameter of the through holes gradually increasing from top to bottom. The lower buffer assembly 5-3 has a cylindrical structure with multiple second strip-shaped grooves running from top to bottom along its annular outer wall. The cross-section of the second strip-shaped groove is triangular, and multiple sets of through holes are arranged at intervals on the cylindrical outer wall, with the diameter of the through holes gradually increasing from top to bottom. In this embodiment, the height of the upper buffer assembly 5-1 is greater than that of the lower buffer assembly 5-3.

[0044] Buffer component 5 is used to reduce vibration and cushion the rocket body during vertical landing. Its main working principle is as follows:

[0045] 1. The landing impact energy is absorbed by a two-stage crushing method using two-stage sheet metal parts with holes of gradient size, thus achieving buffering.

[0046] 2. 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 sheet metal part can be changed according to the design requirements such as the weight of the arrow body and the internal space dimensions, so as to achieve a targeted and precise design of the buffer effect.

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

[0048] The landing buffer pad 7 is bonded to the lower surface of the landing disk 6. The landing buffer pad 7 is used to further dampen the vertical vibration damping mechanism during landing.

[0049] The unlocking lug 8 has a through hole inside, which cooperates with the shaft pin of the arrow body to achieve the connection locking and unlocking between the vertical vibration damping buffer 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 command, the pin puller completes the pin pulling action, and the shaft pin is pulled out of the unlocking lug 8, releasing the movement restriction on the unlocking lug 8, releasing the restriction on the rotational degree of freedom of the vertical vibration damping buffer mechanism about the unfolding axis 1, and completing the unlocking.

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

[0051] Initial locking is achieved by engaging the unlocking lug 8 with the arrow body using the pull pin.

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

[0053] Upon receiving the unlocking command, the pin puller completes the pin pulling action, and the pin is pulled out from the unlocking lug 8, thereby releasing the movement restriction on the unlocking lug 8 and the restriction on the degree of freedom of rotation of the vertical vibration damping buffer mechanism around the unfolding shaft 1, thus completing the unlocking.

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

[0055] Position locking is achieved by engaging the position locking pin 3 with the locking groove located on the arrow body.

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

[0057] I. The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention is suitable for the wide-range landing buffering conditions of aerospace launch vehicles. It can achieve a large buffering capacity with a small volume and can achieve a lean design of buffering according to requirements.

[0058] Implementation principle:

[0059] The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention achieves buffering by layering and crushing energy absorption of the metal structure. It has a strong ability to absorb landing impact energy through deformation and can achieve good buffering performance.

[0060] The load-bearing capacity and buffering characteristics of the vertical vibration damping and buffering mechanism proposed in this 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 sheet metal part, and the depth of the pleated structure.

[0061] Second, the vertical vibration damping and buffering mechanism proposed in this embodiment of the invention is lightweight, easy to operate and easy to replace, which can effectively improve the efficiency of installation, replacement and maintenance of the mechanism and reduce processing costs.

[0062] Implementation principle:

[0063] The pleated structure of the vertical vibration damping and buffer mechanism proposed in this embodiment of the invention is similar to a weight-reduction groove, which can reduce weight while ensuring load-bearing performance. In addition, the designed gradient holes can also reduce weight.

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

[0065] The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention is connected to the arrow body only through the unfolding shaft, making installation and replacement convenient.

[0066] The vertical vibration damping and buffer mechanism pin puller proposed in this invention can be driven by non-pyrotechnic energy sources, such as gas drive or electromagnetic, and has the advantages of being reusable, having low impact, and being detectable and measurable.

[0067] Third, the vertical vibration damping and buffering mechanism proposed in this embodiment of the invention does not occupy the external space of the rocket body, maintains the aerodynamic shape of the rocket body, and occupies less internal space of the rocket body when it is retracted.

[0068] Implementation principle:

[0069] The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention flips and locks inside the tail section of the rocket body during the ascent phase, without protruding outside the rocket body, and does not require additional aerodynamic cover or other devices.

[0070] The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention serves both as a buffer and a load-bearing structure, without any other redundant large-size structural designs, thus achieving miniaturization of the mechanism.

[0071] The vertical vibration damping and buffering mechanism proposed in this invention uses a layered crushing and buffering method with a metal structure, which can reduce the structural size while ensuring load-bearing and buffering performance.

[0072] Fourth, the vertical vibration damping and buffering mechanism proposed in the embodiments of the present invention does not require separate drive energy and thrust energy.

[0073] Implementation principle:

[0074] The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention is driven to flip and unfold by gravity and inertia, and locked in place by spring pin principle, without the need for separate driving energy and pushing energy.

[0075] V. The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention can directly achieve load bearing through the shell section, without the need to set joints and additional reinforcing structures on the rocket body structure.

[0076] Implementation principle:

[0077] The vertical vibration damping and buffering mechanism proposed in this embodiment of the invention, after being flipped and unfolded, locks into the bottom ring frame of the tail section, which can directly transfer the support reaction force to the rocket shell section to achieve load bearing. Therefore, there is no need to set additional joints on the outer wall of the rocket body or to carry out local reinforcement inside the shell section.

[0078] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the protection scope of the present invention.

[0079] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A vertical vibration damping and buffering mechanism for an arrow body with high buffering capacity in a small space, characterized in that, include: The unfolding component, located on the upper surface of the connecting component, is connected to the arrow body, allowing the vertical vibration damping and buffering mechanism to rotate around the unfolding component. The locking element is located on the side wall of the connector and engages with the locking groove of the arrow body to achieve a locked position. The connector connects to the first-stage buffer assembly of the buffer device and is used to bear the load when the rocket body lands. A buffer device for shock absorption during rocket landing includes n-stage buffer components arranged in sequence, with a connecting plate between adjacent buffer components, where n is a positive integer and n≥2; The landing component, connected to the nth-stage buffer assembly of the buffer device, is used to support and bear the load of the rocket body and the vertical vibration damping buffer mechanism during the landing and buffering process. The unlocking component, located on the landing component, is used for locking and unlocking the connection between the vertical shock absorption mechanism and the rocket body; The vertical vibration damping mechanism flips and locks inside the tail section of the rocket during the ascent phase, without protruding outside the rocket body. The vertical vibration damping mechanism is flipped and unfolded by gravity and inertia. When in position, it is locked to the bottom ring frame of the tail section by locking components and is in a vertical state. No separate drive energy or thrust energy is required.

2. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 1, characterized in that, The locking component is a pin structure, which works with the claw assembly inside the arrow body locking groove to achieve positioning and locking.

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

4. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 3, characterized in that, The cylindrical structures of the two buffer components have multiple sets of through holes arranged at intervals along the annular outer wall, and the diameter of the through holes gradually increases from top to bottom.

5. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 3, characterized in that, The buffer device includes two buffer components. The first buffer component, which is connected to the connector, is a cylindrical structure with a first strip groove running from top to bottom at intervals along the annular outer wall. The cross-section of the first strip groove is rectangular, and multiple sets of through holes are arranged at intervals on the cylindrical outer wall, with the diameter of the through holes gradually increasing from top to bottom. The second buffer component, which is connected to the landing device, is a cylindrical structure with multiple second strip grooves running from top to bottom along the annular outer wall. The cross-section of the second strip groove is triangular, and multiple sets of through holes are arranged at intervals on the cylindrical outer wall, with the diameter of the through holes gradually increasing from top to bottom.

6. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 1, characterized in that, The landing component includes a landing disk and a reinforcing rib plate disposed on the landing disk. The reinforcing rib plate is connected to a buffer device, and an unlocking component is installed on the reinforcing rib plate.

7. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 1, characterized in that, The unlocking component is an unlocking lug 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 buffer mechanism and the arrow body structure.

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

9. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 1, characterized in that, It also includes a landing buffer pad, which is bonded to the lower surface of the landing disk of the landing component to provide further vibration damping and cushioning for the vertical vibration damping mechanism during landing.

10. The vertical vibration damping and buffering mechanism for a rocket body with high buffering capacity in a small space according to claim 1, characterized in that, In the buffer device, adjacent buffer components are connected by connecting plates. The first-level buffer component is welded to the connecting piece or integrally formed, and the nth-level buffer component is welded to the landing piece or integrally formed.

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

12. The method for implementing the vertical vibration damping and buffering mechanism for a small space with large buffering capacity as described in any one of claims 1 to 11, characterized in that, include: The initial locking is achieved by engaging the unlocking component with the shaft pin of the arrow body using a pin puller. Upon receiving the unlocking command, the pin puller completes the pin pulling action, and the pin is pulled out from the unlocking component, thus completing the unlocking process. The vertical vibration damping and buffer mechanism deploys under its own gravity. The locking mechanism engages with the locking groove on the arrow body to achieve positioning and locking. After the rocket lands, the buffer device absorbs the landing impact energy through layered crushing, thus achieving buffering.

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