Adjusting device for rocket recovery

Abstract

The adjusting device comprises a plurality of damping adjusting assemblies and a rotating assembly, the multiple damping adjusting assemblies are arranged along the periphery of a rocket body, and each damping adjusting assembly comprises a damping mounting plate, a ventilation channel arranged in the height direction of the damping mounting plate in a penetrating mode and a rotating impeller arranged in the ventilation channel; the current damping part is arranged between the rotating impeller and the damping mounting plate, and the damping mounting plate rotates to be opened and closed in the radial direction of the rocket body through the rotating assembly; when the rocket is in a landing state, the damping mounting plate rotates to a vertical folding state, and the ventilation channel is horizontally arranged; when the rocket is in a vibration reduction state, the ventilation channel rotates till vertical wind penetrates through the damping mounting plate, the rotating impeller rotates under the action of the vertical wind, and the current damping component generates eddy current damping. The invention has the advantages of light weight, low energy consumption and the like while ensuring safe and stable landing of the rocket.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket recovery vibration reduction, and particularly relates to an adjustment device for rocket recovery. Background Art

[0002] Rocket recovery technology refers to the technology of recovering the whole or part of a rocket after launch and reusing it, which can greatly reduce the cost of rocket launch and space exploration. During the rocket recovery process, the adjustment and control of the rocket's attitude, speed, position, etc. are directly related to whether the rocket can be recovered stably and safely. The main ways to recover rockets are: gliding recovery, parachute recovery, and air recovery. Among them, gliding recovery requires a space shuttle to glide and land on a runway, but its construction and maintenance costs are too high; parachute recovery is only suitable for medium and small rockets and is not easy to control the landing point; air recovery is to first let a parachute help the rocket decelerate, and then use a helicopter to lift the rocket in the air, which requires the pilot to have excellent driving skills and is still not applicable to the recovery of large rockets.

[0003] To solve the above technical problems, the existing method is to adopt a landing leg type vertical recovery scheme. This recovery method requires the rocket to strictly reach the landing platform in a vertical attitude, zero lateral speed, and zero vertical speed, and it requires the rocket to have excellent buffering ability when landing. The existing vertical recovery scheme mainly adjusts the rocket flight attitude by generating a reaction force through jet thrust. It needs to consume a large amount of fuel to thrust the rocket to reduce the rocket speed within a short time, and the rocket body needs to be equipped with a landing bracket for a smooth landing. These all increase the weight of the recoverable rocket itself. And there are certain requirements for the overall mass when launching a rocket. At this time, only the payload capacity can be sacrificed to offset the increased mass, which makes the payload capacity of the vertical recovery launch vehicle and the mass of the additional devices added for the purpose of being able to return a pair of contradictory points. The rocket has a large load, high energy consumption, and high cost, and cannot meet the requirements of rocket lightweight, high reliability, and environmental adaptability. More than 90% of the first-stage rocket recovery failures occur in the landing section, thus restricting the safe and reliable implementation of the landing leg type vertical recovery scheme. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and provide an adjustment device for rocket recovery that is lightweight and low-energy-consuming while ensuring the safe and stable landing of the rocket.

[0005] To solve the above technical problems, the technical solution proposed by the present invention is as follows:

[0006] An adjustment device for rocket recovery, comprising a plurality of damping adjustment components and a rotating component. The plurality of damping adjustment components are arranged along the outer periphery of the rocket body. The damping adjustment component includes a damping mounting plate, a ventilation channel penetrating through the damping mounting plate in the height direction, a rotating impeller arranged in the ventilation channel, and a current damping component arranged between the rotating impeller and the damping mounting plate. The damping mounting plate rotates and opens and closes along the radial direction of the rocket body through the rotating component; when the rocket is in the landing state, the damping mounting plate rotates to the vertical folding state, and the ventilation channel is horizontally arranged; when the rocket is in the vibration damping state, the ventilation channel rotates to the vertical wind passing through the damping mounting plate, the rotating impeller rotates under the action of the vertical wind, and the current damping component generates eddy current damping.

[0007] As a further improvement of the above technical solution:

[0008] The current damping component includes a plurality of energy-consuming permanent magnets, a conductor plate and a conductor back plate arranged in an overlapping manner. The plurality of energy-consuming permanent magnets are installed on the rotating impeller through a magnet mounting plate to rotate with the rotating impeller; the conductor plate is arranged opposite to the energy-consuming permanent magnets, and the conductor back plate and the conductor plate are arranged on the damping mounting plate.

[0009] The magnet mounting plate is provided with a first connection hole for ensuring the connection of the ventilation channel, and an air passing gap communicating with the ventilation channel is left between the magnet mounting plate and the damping mounting plate; the conductor plate and the conductor back plate are provided with a second connection hole for ensuring the connection of the ventilation channel.

[0010] The plurality of energy-consuming permanent magnets are arranged at intervals along the circumference of the magnet mounting plate, and the first connection hole is arranged between adjacent energy-consuming permanent magnets.

[0011] The ventilation channel includes a small-diameter ventilation hole, an equal-diameter through section and a large-diameter ventilation hole which are connected in sequence from top to bottom. The small-diameter ventilation hole and the large-diameter ventilation hole are arranged on the damping mounting plate, and the rotating impeller is installed in the equal-diameter through section through an impeller support seat.

[0012] The diameter of the equal-diameter through section is equal to that of the large-diameter ventilation hole, the blades of the rotating impeller are arranged towards the large-diameter ventilation hole, and the current damping component is arranged at one end of the rotating impeller close to the small-diameter ventilation hole.

[0013] The top plate of the damping mounting plate protrudes with a damping installation space, and the current damping part is arranged in the damping installation space.

[0014] The eddy current damping components are at least two, and at least two eddy current damping components are arranged in an array on the damping mounting plate; the number of the ventilation channels and the rotating impellers is the same as the number of the eddy current damping components, and they are arranged in one-to-one correspondence.

[0015] It further includes a frame-shaped mounting bracket fixed to the rocket body. There are four sets of the damping adjustment components, and the four sets of the damping adjustment components are rotatably mounted on the four sides of the frame-shaped mounting bracket through the rotating components.

[0016] When the rocket is in a vibration damping state, the damping mounting plate rotates to a horizontal arrangement through the rotating component, and the ventilation channel is arranged parallel to the direction of the vertical wind.

[0017] Compared with the prior art, the advantages of the present invention are as follows:

[0018] For the first time in the field of rocket recovery vibration damping, the present invention creatively adopts the combination of the vertical wind during the vertical movement of the rocket and the rotating impeller, combined with the principle of eddy current damping, and uses the method of rotating and switching the ventilation channel to adjust the working state of the damping adjustment component. While simplifying the damping structure and lightweight, it realizes the high-damping vibration damping characteristics during rocket recovery, ensuring the smooth recovery and landing of the rocket. At the same time, the present invention replaces the method of using fuel to provide counter-thrust for vibration damping, avoiding the problems of large consumption of fuel energy and heavy load, improving the energy utilization efficiency, realizing the lightweight requirement during the vertical recovery of the rocket, and effectively improving the carrying capacity of the rocket. Specifically:

[0019] The present invention arranges a plurality of damping adjustment components in the circumferential direction of the rocket body. The damping adjustment component includes a damping mounting plate, a ventilation channel, a rotating impeller and a current damping component. The ventilation channel is arranged through in the height direction of the damping mounting plate. The rotating impeller is arranged in the ventilation channel, and the current damping component is arranged between the rotating impeller and the damping mounting plate, which makes the adjustment device simple in structure, small in occupied space, low in cost, and convenient for installation and disassembly.

[0020] At the same time, the damping mounting plate rotates and opens and closes along the radial direction of the rocket body through the rotating component. When the rocket is in the descending state during the recovery process, the damping mounting plate rotates to a vertical folded state, and the ventilation channel is horizontally arranged. At this time, the vertical wind cannot penetrate the damping mounting plate, and the rotating impeller will not rotate, so that the damping adjustment component does not work and does not affect the normal descending speed of the rocket, so as to reduce the burden on the rocket.

[0021] During the shock absorption state of the rocket's soft landing during the rocket recovery process, the ventilation channel rotates to the vertical wind through damping mounting plate to form an air diversion channel. At this time, the wind provides aerodynamic drag. At the same time, the rotating impeller rotates under the action of the vertical wind. At this time, the current damping component generates eddy current damping. The rotating impeller continuously vibrates under the action of the vertical wind, thereby generating continuous eddy current damping. Through the dual buffering effects of aerodynamic drag and electromagnetic damping force, sufficient damping force is provided for the rocket's soft landing, thereby effectively buffering the landing impact and suppressing the rocket's vibration, achieving the safe and stable soft landing of the rocket. At the same time, it enables the rocket body to maintain a stable attitude during the recovery process, effectively avoiding dangerous situations such as tilting and rolling caused by too fast a descent speed or uneven force, significantly improving the success rate and safety of rocket recovery.

[0022] At the same time, when the rocket is in the shock absorption state, the damping mounting plate unfolds smoothly from the folded state, which greatly increases the windward area of the rocket body, increases the air resistance, and is equivalent to opening a "deceleration parachute" for the falling rocket, achieving the purpose of effectively controlling the rocket's descent speed. Brief Description of the Drawings

[0023] In the following, the present invention will be described in more detail based on embodiments and with reference to the drawings. Among them:

[0024] Figure 1 is a three-dimensional structure diagram of the adjustment device for rocket recovery of the present invention (rocket shock absorption state);

[0025] Figure 2 is a three-dimensional structure diagram of the adjustment device for rocket recovery of the present invention (rocket landing state);

[0026] Figure 3 is a three-dimensional structure schematic diagram of the damping adjustment component of the present invention;

[0027] Figure 4 is a main sectional view of the damping adjustment component of the present invention;

[0028] Figure 5 is a schematic diagram of the positional relationship between the impeller support seat and the magnet mounting plate of the present invention.

[0029] Each reference numeral in the figure represents:

[0030] 1. Rocket body; 2. Damping adjustment component; 21. Damping mounting plate; 211. Damping installation space; 22. Ventilation channel; 221. Small-diameter ventilation hole; 222. Equal-diameter through-section; 223. Large-diameter ventilation hole; 23. Rotating impeller; 24. Energy-consuming magnet; 25. Conductor plate; 26. Conductor back plate; 27. Magnet mounting plate; 271. First connection hole; 28. Impeller support seat; 29. Second connection hole; 3. Rotating component; 31. Rotating connection shaft; 4. Frame-shaped mounting rack; 5. Air passing gap. Detailed implementation mode

[0031] The present invention will be further described in detail below in conjunction with the accompanying drawings of the specification and specific embodiments, but the protection scope of the present invention is not limited thereby.

[0032] As Figures 1 to 5 shown, the adjustment device for rocket recovery in this embodiment includes a plurality of damping adjustment components 2 and a rotating component 3. The plurality of damping adjustment components 2 are arranged along the outer periphery of the rocket body 1. The damping adjustment component 2 includes a damping mounting plate 21, a ventilation channel 22, a rotating impeller 23, and a current damping component. Among them, the ventilation channel 22 is arranged through in the height direction of the damping mounting plate 21. The rotating impeller 23 is arranged in the ventilation channel 22, and the current damping component is arranged between the rotating impeller 23 and the damping mounting plate 21, which makes the adjustment device simple in structure, small in occupied space, low in cost, and convenient for installation and disassembly.

[0033] At the same time, the damping mounting plate 21 rotates and opens and closes along the radial direction of the rocket body 1 through the rotating component 3. When the rocket is in the landing state during the recovery process, the damping mounting plate 21 rotates to the vertical folding state, and the ventilation channel 22 is horizontally arranged. At this time, the vertical wind cannot penetrate the damping mounting plate 21, and the rotating impeller 23 will not rotate, so that the damping adjustment component 2 does not work and does not affect the normal landing speed of the rocket, so as to reduce the burden on the rocket.

[0034] During the shock absorption state when the rocket is about to make a soft landing during the rocket recovery process, the ventilation channel 22 rotates to allow the vertical wind to penetrate the damping mounting plate 21 to form an air diversion channel. At this time, the wind force provides aerodynamic resistance; at the same time, when the rotating impeller 23 rotates under the action of the vertical wind, at this time, the current damping component generates eddy current damping, and the rotating impeller 23 continuously vibrates under the action of the vertical wind, thereby generating continuous eddy current damping. Through the dual buffering effects of aerodynamic resistance and electromagnetic damping force, sufficient damping force is provided for the rocket to make a soft landing, so as to effectively buffer the landing impact and suppress the vibration of the rocket, and realize the safe and stable soft landing of the rocket. At the same time, it enables the rocket body 1 to maintain a stable attitude during the recovery process, effectively avoiding dangerous situations such as tilting and rolling caused by too fast a descent speed or uneven force, and significantly improving the success rate and safety of rocket recovery.

[0035] At the same time, when the rocket is in the shock absorption state, the damping mounting plate 21 smoothly unfolds from the folded state, which greatly increases the windward area of the rocket body, increases the air resistance, and is equivalent to opening a "deceleration parachute" for the falling rocket, achieving the purpose of effectively controlling the descent speed of the rocket.

[0036] For the first time in the field of rocket recovery vibration damping, the present invention creatively combines the vertical wind during the vertical movement of the rocket with the rotating impeller 23 and incorporates the principle of eddy current damping. By means of the rotating switching of the ventilation channel 22 to adjust the working state of the damping adjustment component 2, while simplifying the damping structure and achieving lightweight, high-damping vibration damping characteristics during rocket recovery are realized, ensuring the smooth recovery and landing of the rocket. At the same time, the present invention replaces the method of using fuel to provide counter-thrust vibration damping, avoiding the problems of large consumption of fuel energy and heavy load, improving the energy utilization efficiency, meeting the lightweight requirement of the rocket during vertical recovery, and effectively enhancing the carrying capacity of the rocket.

[0037] As Figure 4 shown, the current damping component includes a plurality of energy-consuming permanent magnets 24, a conductor plate 25, and a conductor back plate 26. Among them, the plurality of energy-consuming permanent magnets 24 are installed on the rotating impeller 23 through a magnet mounting plate 27 and rotate with the rotating impeller 23; the conductor plate 25 is arranged opposite to the energy-consuming permanent magnets 24, and the conductor back plate 26 and the conductor plate 25 are stacked and arranged on the damping mounting plate 21. Its layout structure is compact and occupies little space. In other embodiments, the energy-consuming permanent magnets 24 and the conductor plate 25 can also be swapped, that is, the conductor plate 25 is arranged on the rotating impeller 23, and the energy-consuming permanent magnets 24 are arranged on the damping mounting plate 21. The energy-consuming permanent magnets 24 can also be permanent magnets made of other materials.

[0038] In this embodiment, when the energy-consuming permanent magnets 24 rotate with the rotating impeller 23, relative movement is generated between the energy-consuming permanent magnets 24 and the conductor plate 25. The conductor plate 25 cuts the magnetic induction lines, generating an eddy current damping force, so that the energy during rocket vibration is finally converted into heat energy generated by eddy current heating, achieving the purpose of energy-consuming vibration damping. At the same time, the rotating impeller 23 continuously vibrates under the action of the vertical wind, thereby generating continuous eddy current damping and realizing the safe and smooth soft landing of the rocket. The conductor back plate 26 can effectively guide and concentrate the magnetic flux, reduce the magnetic resistance and magnetic leakage of the magnetic circuit, and the conductor back plate 26 and the energy-consuming permanent magnets 24 and the conductor plate 25 jointly form a closed magnetic circuit, thereby optimizing the magnetic field distribution and enhancing the magnetic flux density in the area of the conductor plate 25. That is, the conductor back plate 26 enhances the magnetic flux density by improving the concentration of the magnetic flux and reducing the magnetic resistance of the magnetic circuit. The increase in the magnetic flux density makes the generation of eddy current more significant, thereby greatly enhancing the energy-consuming ability of the conductor plate 25 and improving the vibration damping effect.

[0039] Furthermore, the length of the conductor plate 25 is equal to the length of the conductor back plate 26, and the conductor plate 25 and the conductor back plate 26 are overlapped. This further optimizes the electromagnetic performance, reduces energy loss, and has a simple layout structure, ensuring the excellent vibration damping effect of the damper.

[0040] In this embodiment, the conductor plate 25 is a non-ferromagnetic conductor member with high electrical conductivity (such as copper, aluminum, copper alloy, or aluminum alloy, etc.) to increase the intensity of eddy current in the conductor plate 25. The conductor back plate 26 is made of a material with high magnetic permeability to increase the intensity of eddy current in the conductor plate 25.

[0041] In this embodiment, the magnet mounting plate 27 is provided with a first connection hole 271 to ensure the connection of the ventilation channel 22, and the conductor plate 25 and the conductor back plate 26 are provided with a second connection hole 29 to ensure the connection of the ventilation channel 22, so that the vertical wind passes through the damping mounting plate 21, ensuring the damping effect. Preferably, there is an air passing gap 5 between the magnet mounting plate 27 and the damping mounting plate 21, thereby increasing the air passing area, enabling the rotating impeller 23 to rotate at high speed, and further increasing the eddy current damping force of the current damping component.

[0042] Furthermore, a plurality of energy-consuming magnets 24 are arranged at intervals along the circumference of the magnet mounting plate 27, and the first connection hole 271 is provided between adjacent energy-consuming magnets 24. While ensuring the eddy current damping, the layout is compact and occupies a small space. The number of energy-consuming magnets 24 provided can be adjusted according to the required damping force magnitude, such as being set to three, four, etc.

[0043] As Figure 4 shown, furthermore, the ventilation channel 22 includes a small-diameter ventilation hole 221, an equal-diameter through section 222, and a large-diameter ventilation hole 223. Among them, the small-diameter ventilation hole 221 is provided on the top plate of the damping mounting plate 21, the large-diameter ventilation hole 223 is provided on the bottom plate of the damping mounting plate 21, the equal-diameter through section 222 is provided through the height of the damping mounting plate 21, and the rotating impeller 23 is installed in the equal-diameter through section 222 through an impeller support seat 28. This further enables the vertical wind to pass through the inside of the damping mounting plate 21 uniformly and effectively, realizing the effective rotation of the rotating impeller 23.

[0044] In the rocket damping state, when the damping mounting plate 21 rotates to the position where the vertical wind passes through the damping mounting plate 21, the vertical wind will enter the rotating impeller 23 in the equal-diameter through section 222 from the large-diameter ventilation hole 223 at the bottom plate of the damping mounting plate 21. At this time, it drives the rotating impeller 23 to rotate, thereby enabling the current damping component to generate an eddy current damping force. At the same time, the vertical wind is discharged through the small-diameter ventilation hole 221 at the top plate of the damping mounting plate 21, ensuring the reliable and effective movement of the damping adjustment assembly 2 and the damping effect, and the structure is simple and compact.

[0045] Even further, the diameter of the equal-diameter through section 222 is equal to that of the large-diameter ventilation hole 223, the blades of the rotating impeller 23 are arranged facing the large-diameter ventilation hole 223, and the current damping component is arranged at one end of the rotating impeller 23 close to the small-diameter ventilation hole 221. This enables more vertical wind to enter the rotating impeller 23, thereby further improving the damping and vibration reduction effect of the current damping component by increasing the rotation speed of the rotating impeller 23.

[0046] Preferably, a damping mounting space 211 is convexly provided on the top plate of the damping mounting plate 21, and the current damping component is arranged in the damping mounting space 211 to ensure the compact layout of the components in the damping mounting plate 21, and its structure is simple and the occupied space is small.

[0047] In this embodiment, there are two eddy current damping components, and the two eddy current damping components are arranged along the length direction of the damping mounting plate 21; the number of ventilation channels 22 and rotating impellers 23 is the same as the number of eddy current damping components, and they are arranged in one-to-one correspondence. To ensure that the eddy current damping components provide sufficient damping force to the rocket body 1 and ensure the smooth soft landing of the rocket. In other embodiments, the setting data of the eddy current damping components can be adjusted according to the damping force required by the rocket body 1. For example, it can also be set to three, four, etc. Multiple eddy current damping components can be arranged in an array along the length direction or width direction of the damping mounting plate 21.

[0048] In this embodiment, as Figure 1 and Figure 2 shown, the adjustment device for rocket recovery further includes a frame-shaped mounting bracket 4 fixed to the rocket body 1. There are four groups of damping adjustment components 2, and the four groups of damping adjustment components 2 are rotatably mounted on the four sides of the frame-shaped mounting bracket 4 through the rotating component 3. An installation fitting groove is provided in the middle of the frame-shaped mounting bracket 4, and the installation fitting groove is adapted to the outer surface of the rocket body 1 so that the eddy current damping components can be reliably and effectively installed on the rocket body 1.

[0049] Furthermore, the rotating component 3 includes a rotating connection shaft 31. The rotating connection shaft 31 is installed on the frame-shaped mounting bracket 4, and the damping mounting plate 21 is rotatably connected to the rotating connection shaft 31 and rotates under the drive control of the drive motor to realize the effective switching of different states of different damping adjustment components 2.

[0050] In this embodiment, when the rocket is in the vibration damping state, the damping mounting plate 21 rotates to a horizontal arrangement through the rotating component 3, and the ventilation channel 22 is arranged parallel to the direction of the vertical wind. At this time, the damping mounting plate 21 is fully unfolded, so that the vertical wind can enter the ventilation channel 22 more fully to drive the rotating impeller 23 and make the current damping component produce a better damping effect; at the same time, the windward area of the rocket body is further increased, and the descending speed of the rocket is further controlled. In other embodiments, as long as the angle of the damping mounting plate 21 in the rocket vibration damping state ensures that the vertical wind penetrates the ventilation channel 22, the structure should be within the protection scope of the present invention.

[0051] Although the present invention has been described with reference to the preferred embodiments, various modifications thereof can be made and components thereof can be replaced with equivalents without departing from the scope of the present invention. In particular, as long as there is no structural conflict, the technical features mentioned in each embodiment can be combined in any way. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. An adjustment device for rocket recovery, characterized in that, It includes a plurality of damping adjustment components and a rotating component. The plurality of damping adjustment components are arranged along the outer circumference of the rocket body. The damping adjustment component includes a damping mounting plate, a ventilation channel penetrating through the damping mounting plate in the height direction, a rotating impeller arranged in the ventilation channel, and a current damping component arranged between the rotating impeller and the damping mounting plate. The damping mounting plate rotates and opens and closes along the radial direction of the rocket body through the rotating component; when the rocket is in the landing state, the damping mounting plate rotates to the vertical folding state, and the ventilation channel is horizontally arranged; when the rocket is in the vibration damping state, the ventilation channel rotates to the vertical wind passing through the damping mounting plate, the rotating impeller rotates under the action of the vertical wind, and the current damping component generates eddy current damping.

2. The adjusting device for rocket recovery according to claim 1, characterized in that, The current damping component includes a plurality of energy-consuming permanent magnets, a conductor plate and a conductor back plate arranged in an overlapping manner. The plurality of energy-consuming permanent magnets are installed on the rotating impeller through a magnet mounting plate to rotate with the rotating impeller; The conductor plate is arranged opposite to the energy-consuming permanent magnets, and the conductor back plate and the conductor plate are arranged on the damping mounting plate.

3. The adjusting device for rocket recovery according to claim 2, characterized in that, The magnet mounting plate is provided with a first connection hole for ensuring the connection of the ventilation channel, and an air passing gap communicating with the ventilation channel is left between the magnet mounting plate and the damping mounting plate; the conductor plate and the conductor back plate are provided with a second connection hole for ensuring the connection of the ventilation channel.

4. The adjusting device for rocket recovery according to claim 3, characterized in that, The plurality of energy-consuming permanent magnets are arranged at intervals along the circumference of the magnet mounting plate, and the first connection hole is arranged between adjacent energy-consuming permanent magnets.

5. The adjusting device for rocket recovery according to any one of claims 1 to 4, characterized in that, The ventilation channel includes a small-diameter ventilation hole, an equal-diameter through section and a large-diameter ventilation hole that are connected in sequence from top to bottom. The small-diameter ventilation hole and the large-diameter ventilation hole are arranged on the damping mounting plate, and the rotating impeller is installed in the equal-diameter through section through an impeller support seat.

6. The adjusting device for rocket recovery according to claim 5, wherein, The diameter of the equal-diameter through section is equal to that of the large-diameter ventilation hole. The blades of the rotating impeller are arranged towards the large-diameter ventilation hole, and the current damping component is arranged at one end of the rotating impeller close to the small-diameter ventilation hole.

7. The adjusting device for rocket recovery according to claim 6, characterized in that, The top plate of the damping mounting plate protrudes with a damping mounting space, and the current damping part is arranged in the damping mounting space.

8. The adjusting device for rocket recovery according to any one of claims 1 to 4, characterized in that, The eddy current damping components are at least two, and at least two eddy current damping components are arranged in an array on the damping mounting plate; the number of the ventilation channels and the rotating impellers is the same as the number of the eddy current damping components, and they are arranged in one-to-one correspondence.

9. The adjusting device for rocket recovery according to any one of claims 1 to 4, characterized in that, It further includes a frame-shaped mounting bracket fixed to the rocket body. There are four groups of damping adjustment components, and the four groups of damping adjustment components are rotatably mounted on the four sides of the frame-shaped mounting bracket through the rotating component.

10. The adjusting device for rocket recovery according to any one of claims 1 to 4, characterized in that, When the rocket is in the vibration damping state, the damping mounting plate rotates to the horizontal arrangement through the rotating component, and the ventilation channel is arranged parallel to the direction of the vertical wind.

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