Sheet type damper for rocket recovery

Abstract

The invention provides a chip damper for rocket recovery, which comprises a rocket main body, and further comprises a plurality of buffering and damping units and a rotation adjusting assembly, the plurality of buffering and damping units are arranged along the periphery of the rocket main body, and the rotation adjusting assembly is arranged on the periphery of the rocket main body. The buffering vibration reduction unit comprises a damping mounting frame, sheet-shaped elastic conductor pieces and energy consumption magnetic steel which are alternately arranged in the length direction of the damping mounting frame, and a ventilation channel arranged between the sheet-shaped elastic conductor pieces and the energy consumption magnetic steel, and the damping mounting frame is rotatably arranged through the rotation adjusting assembly; when the rocket is in a landing state, the ventilation channel arranged on the damping mounting frame rotates until vertical wind cannot penetrate through the damping mounting frame; when the rocket is in a vibration reduction state, the ventilation channel rotates till vertical wind penetrates through the damping installation frame, the sheet-shaped elastic conductor piece vibrates under the action of the vertical wind, and eddy current damping is generated by the sheet-shaped elastic conductor piece and the energy dissipation magnetic steel. 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 damping, and in particular to a plate damper 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. The main ways of recovering rockets are: gliding recovery, parachute recovery, and air recovery. Among them, gliding recovery requires a space shuttle to land by gliding on a runway, but its construction and maintenance costs are too high; parachute recovery is only suitable for small and medium-sized 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, which requires the rocket to have excellent buffering ability when landing. The existing vertical recovery scheme needs to consume a large amount of fuel to perform a reverse thrust on 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 vertically recovered 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 failures of the first-stage rocket recovery 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 a plate damper for rocket recovery that is lightweight and low-energy-consuming while ensuring the safe and smooth landing of the rocket.

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

[0006] A sheet damper for rocket recovery, comprising a rocket body, further comprising a plurality of buffer and vibration damping units and a rotation adjustment assembly. The plurality of buffer and vibration damping units are arranged along the outer periphery of the rocket body. The buffer and vibration damping unit includes a damping mounting frame, sheet-shaped elastic conductor pieces and energy-consuming permanent magnets arranged alternately along the length direction of the damping mounting frame, and a ventilation channel arranged between the sheet-shaped elastic conductor pieces and the energy-consuming permanent magnets. The damping mounting frame is rotatably arranged through the rotation adjustment assembly; when the rocket is in the landing state, the ventilation channel arranged on the damping mounting frame rotates to a position where the vertical wind cannot penetrate the damping mounting frame; when the rocket is in the vibration damping state, the ventilation channel rotates to a position where the vertical wind penetrates the damping mounting frame, and the sheet-shaped elastic conductor pieces vibrate under the action of the vertical wind and generate eddy current damping with the energy-consuming permanent magnets.

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

[0008] The sheet-shaped elastic conductor piece is a curved sheet-shaped conductor plate, and the ventilation channel overlaps with the curved section of the curved sheet-shaped conductor plate to drive the curved sheet-shaped conductor plate to vibrate when the vertical wind enters.

[0009] The ventilation channel includes an upper ventilation hole, a through section and a lower ventilation hole that are sequentially communicated. The upper ventilation hole and the lower ventilation hole are oppositely arranged on the damping mounting frame, and the through section is parallel to the curved sheet-shaped conductor plate and is arranged to penetrate along the height direction of the damping mounting frame.

[0010] The damping mounting frame is a frame-type damping mounting frame. Magnet mounting plates are arranged at intervals along the length direction of the frame-type damping mounting frame, and the energy-consuming permanent magnets are symmetrically arranged on both sides of the magnet mounting plates; the ventilation channel is located between the magnet mounting plates and the sheet-shaped elastic conductor pieces.

[0011] The curved sheet-shaped conductor plate is an S-shaped conductor plate or a Z-shaped conductor plate, and both ends of the S-shaped conductor plate or the Z-shaped conductor plate are fixedly installed on the frame-type damping mounting frame through connection mounting plates.

[0012] The rotation plane of the damping mounting frame when driven by the rotation adjustment assembly is tangent to the rocket body.

[0013] When the rocket is in the landing state, the damping mounting frame rotates to a vertical arrangement through the rotation adjustment assembly, and the ventilation channel is arranged perpendicular to the direction of the vertical wind; when the rocket is in the vibration damping state, the damping mounting frame rotates to a horizontal arrangement through the rotation adjustment assembly, and the ventilation channel is arranged parallel to the direction of the vertical wind.

[0014] It further includes a frame-shaped mounting bracket. There are four groups of the buffer and shock absorption units, and the four groups of the buffer and shock absorption units are rotatably mounted on the four sides of the frame-shaped mounting bracket through the rotation adjustment assembly. An installation fitting groove adapted to the outer surface of the rocket body is provided in the middle of the frame-shaped mounting bracket.

[0015] The rotation adjustment assembly is mounted on the frame-shaped mounting bracket. The rotation adjustment assembly includes a rotation connecting shaft and a driving motor. The two ends of the rotation connecting shaft are respectively connected to the frame-shaped mounting bracket and the damping mounting bracket, and the damping mounting bracket rotates under the drive of the driving motor.

[0016] The sheet-shaped elastic conductor is a non-ferromagnetic conductor with high electrical conductivity, and the length of the non-ferromagnetic conductor is equal to the length of the energy-consuming permanent magnet.

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

[0018] The present invention solves the problems of large load and limited carrying capacity during the vertical recovery of the rocket through a clever and simple structural design. That is, for the first time in the field of rocket recovery shock absorption, the present invention creatively adopts the principle of combining the vertical wind during the vertical movement of the rocket and eddy current damping. By using the combination of the sheet-shaped elastic conductor and the energy-consuming permanent magnet, and the method of rotating and switching the ventilation channels to adjust the working state of the buffer and shock absorption units, while simplifying the damping structure and reducing the weight, the high-damping shock absorption characteristics during rocket recovery are achieved, ensuring the smooth recovery and landing of the rocket. At the same time, the present invention replaces the method of using fuel to provide reverse thrust for shock absorption, 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 buffer and shock absorption units circumferentially around the rocket body. The buffer and shock absorption unit includes a damping mounting bracket, a sheet-shaped elastic conductor, an energy-consuming permanent magnet and a ventilation channel. The damping mounting bracket and the sheet-shaped elastic conductor are arranged alternately along the length direction of the damping mounting bracket. The ventilation channel is arranged between the sheet-shaped elastic conductor and the energy-consuming permanent magnet. Its sheet-type damper has a simple structure, small occupied space, low cost, and is convenient for installation and disassembly.

[0020] Meanwhile, the damping mounting bracket is rotatably arranged through a rotation adjustment component; during the landing state in the rocket recovery process, the ventilation channel of the damping mounting bracket rotates to a position where the vertical wind cannot penetrate the damping mounting bracket. At this time, the sheet-shaped elastic conductor in the buffer shock absorption unit will not deform and vibrate, so that the buffer shock absorption unit does not work, thus not affecting the normal landing speed of the rocket and reducing the burden on the rocket. During the shock absorption state when the rocket is about to make a soft landing in the rocket recovery process, the ventilation channel rotates to a position where the vertical wind penetrates the damping mounting bracket. The sheet-shaped elastic conductor deforms and vibrates under the action of the vertical wind to cut the magnetic induction lines generated by the energy-consuming magnetic steel, thereby generating eddy current damping. The sheet-shaped elastic conductor continuously vibrates under the action of the vertical wind, thereby generating continuous eddy current damping to provide sufficient damping force for the rocket's soft landing, effectively buffering the landing impact and suppressing the rocket's vibration, and realizing the safe and stable soft landing of the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In the following, the present invention will be described in more detail based on embodiments and with reference to the drawings. Among them:

[0022] Figure 1 is a three-dimensional structural diagram of the sheet-type damper for rocket recovery of the present invention (the side cover plate of the damping mounting bracket is not shown);

[0023] Figure 2 is the front view of the sheet-type damper for rocket recovery of the present invention (rocket landing state);

[0024] Figure 3 is the front view of the sheet-type damper for rocket recovery of the present invention (rocket shock absorption state);

[0025] Figure 4 is a three-dimensional structural diagram of the buffer shock absorption unit of the present invention;

[0026] Figure 5 is the front view of the buffer shock absorption unit of the present invention.

[0027] Each label in the figure represents:

[0028] 1, rocket main body; 2, buffer shock absorption unit; 21, damping mounting bracket; 22, sheet-shaped elastic conductor; 221, connection mounting plate; 23, energy-consuming magnetic steel; 24, ventilation channel; 241, upper ventilation hole; 242, through section; 243, lower ventilation hole; 25, magnetic steel mounting plate; 3, rotation adjustment component; 31, connecting shaft; 4, frame-shaped mounting bracket. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] The present invention will be further described in detail below in conjunction with the specification drawings and specific embodiments, but the protection scope of the present invention is not limited thereby.

[0030] As Figures 1 to 5As shown, the sheet damper for rocket recovery of this embodiment includes a rocket body 1, a plurality of buffer vibration reduction units 2 and a rotation adjustment assembly 3. Among them, the plurality of buffer vibration reduction units 2 are arranged along the periphery of the rocket body 1, and the buffer vibration reduction unit 2 includes a damping mounting frame 21, a sheet elastic conductor 22, an energy dissipation magnetic steel 23 and a ventilation channel 24. The sheet elastic conductor 22 and the energy dissipation magnetic steel 23 are alternately arranged along the length direction of the damping mounting frame 21, and the ventilation channel 24 is provided between the sheet elastic conductor 22 and the energy dissipation magnetic steel 23. The sheet damper has a simple structure, occupies a small space, has a low cost, and is easy to install and disassemble.

[0031] At the same time, the damping mounting frame 21 is rotatably arranged by rotating the adjustment component 3. When the rocket is in the landing state during the recovery process, the ventilation channel 24 of the damping mounting frame 21 rotates until the vertical wind cannot pass through the damping mounting frame 21. At this time, the sheet elastic conductor 22 in the buffering and vibration reduction unit 2 will not deform and vibrate, so that the buffering and vibration reduction unit 2 does not work, thereby not affecting the normal landing speed of the rocket, so as to reduce the burden on the rocket. When the rocket is in the vibration reduction state of soft landing in the recovery process, the ventilation channel 24 rotates to the vertical wind through the damping mounting frame 21, and the sheet elastic conductor 22 deforms and vibrates under the action of the vertical wind to cut the magnetic flux generated by the energy-consuming magnetic steel 23 to generate eddy current damping. The sheet elastic conductor 22 continues to vibrate under the action of the vertical wind, thereby generating continuous eddy current damping to provide sufficient damping force for the soft landing of the rocket, thereby effectively buffering the landing impact, suppressing the vibration of the rocket, and realizing a safe and smooth soft landing of the rocket.

[0032] It can be seen that the present invention solves the problem of large load and limited carrying capacity during vertical recovery of rockets through ingenious and simple structural design. That is, the present invention is the first in the field of rocket recovery vibration reduction to pioneer the use of the principle of vertical wind combined with eddy current damping during vertical movement of rockets, and utilizes the combination of sheet elastic conductor 22 and energy-consuming magnetic steel 23, as well as the ventilation channel 24 to rotate and switch to adjust the working state of the buffer vibration reduction unit 2. While simplifying the damping structure and reducing weight, it achieves high damping vibration reduction 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 reverse thrust vibration reduction, avoids the problem of large consumption of fuel energy and heavy load, improves energy utilization efficiency, realizes the lightweight requirements of rockets during vertical recovery, and effectively improves the carrying capacity of rockets.

[0033] Furthermore, if Figure 4 and Figure 5As shown, the sheet-shaped elastic conductor 22 is a curved sheet-shaped conductor plate. The ventilation channel 24 overlaps with the curved section of the curved sheet-shaped conductor plate to drive the vibration of the curved sheet-shaped conductor plate when the vertical wind enters, so as to generate relative movement with the energy-consuming magnetic steel 23. At this time, the curved sheet-shaped conductor plate cuts the magnetic induction lines, generating an eddy current damping force, so that the energy during the vibration of the rocket is finally converted into heat energy generated by eddy current heating, achieving the purpose of energy-consuming vibration reduction. In other embodiments, the energy-consuming magnetic steel 23 can also be a permanent magnet made of other materials. While achieving excellent damping and vibration reduction functions, it has a simple structure and a light weight.

[0034] More preferably, the ventilation channel 24 includes an upper ventilation hole 241, a through section 242, and a lower ventilation hole 243 that are sequentially connected. The upper ventilation hole 241 and the lower ventilation hole are relatively arranged on the upper and lower plates of the damping mounting frame 21. The through section 242 is parallel to the curved sheet-shaped conductor plate, and the through section 242 is arranged through along the height direction of the damping mounting frame 21, which further enables the vertical wind to pass through the inside of the damping mounting frame 21 evenly and effectively, realizing the uniform and reliable vibration of the sheet-shaped elastic conductor 22.

[0035] As Figure 1 shown, the damping mounting frame 21 is a frame-shaped damping mounting frame 21. The frame-shaped damping mounting frame 21 is provided with magnet mounting plates 25 at intervals along the length direction. The energy-consuming magnetic steels 23 are symmetrically arranged on both sides of the magnet mounting plates 25; the ventilation channel 24 is located between the magnet mounting plates 25 and the sheet-shaped elastic conductor 22. So that the buffer vibration reduction unit 2 has a compact layout and small occupied space while achieving excellent damping and vibration reduction functions.

[0036] In this embodiment, the curved sheet-shaped conductor plate is an S-shaped conductor plate. The two ends of the S-shaped conductor plate are fixedly installed on the frame-shaped damping mounting frame 21 through connection mounting plates 221 to ensure the effective installation of the curved sheet-shaped conductor plate. At the same time, the curved surface of the S-shaped conductor plate can effectively contact the vertical wind, better realizing the vibration control of the rocket body 1. In other embodiments, the curved sheet-shaped conductor plate can also be a Z-shaped conductor plate or other curved surface structures that vibrate when contacting the vertical wind.

[0037] As Figure 2 and Figure 3 shown, the rotation surface of the damping mounting frame 21 when driven by the rotation adjustment assembly 3 is tangent to the rocket body 1, so as to ensure that the buffer vibration reduction unit 2 will not collide with the rocket body 1 when rotating to the rocket landing state and the vibration reduction state, ensuring the normal operation of the buffer vibration reduction unit 2.

[0038] Furthermore, when the rocket is in the landing state, the damping mounting bracket 21 is rotated to a vertical arrangement through the rotation adjustment assembly 3, and the ventilation channel 24 is arranged perpendicular to the direction of the vertical wind. At this time, that is, the ventilation channel 24 is horizontally arranged, and air cannot enter the damping mounting bracket 21 through the opening of the ventilation channel 24. At this time, the buffer and shock absorption unit 2 does not work, so that the buffer and shock absorption unit 2 does not work, thus not affecting the normal landing speed of the rocket and reducing the burden on the rocket.

[0039] When the rocket is in the shock absorption state, the damping mounting bracket 21 is rotated to a horizontal arrangement through the rotation adjustment assembly 3, and the ventilation channel 24 is arranged parallel to the direction of the vertical wind. At this time, that is, the ventilation channel 24 is vertically arranged, and the vertical wind passes through the ventilation channel 24 to penetrate the damping mounting bracket 21. The sheet-shaped elastic conductor 22 deforms and vibrates under the action of the vertical wind to cut the magnetic induction lines generated by the energy-consuming magnetic steel 23, thereby generating eddy current damping. The sheet-shaped elastic conductor 22 continuously vibrates under the action of the vertical wind, thereby generating continuous eddy current damping to achieve the safe and stable soft landing of the rocket. In other embodiments, as long as the angle of the damping mounting bracket 21 in the rocket shock absorption state ensures that the vertical wind enters the ventilation channel 24, the structure should be within the protection scope of the present invention. As long as the angle of the damping mounting bracket 21 in the rocket landing state ensures that the vertical wind does not enter the ventilation channel 24, the structure should be within the protection scope of the present invention.

[0040] Preferably, the damper further includes a frame-shaped mounting bracket 4, and there are four groups of buffer and shock absorption units 2. The four groups of buffer and shock absorption units 2 are rotatably mounted on the four sides of the frame-shaped mounting bracket 4 through the rotation adjustment assembly 3. An installation and fitting groove is provided in the middle of the frame-shaped mounting bracket 4, and the installation and fitting groove is adapted to the outer surface of the rocket body 1, so that the buffer and shock absorption unit 2 can be reliably and effectively mounted on the rocket body 1.

[0041] Furthermore, the rotation adjustment assembly 3 is mounted on the frame-shaped mounting bracket 4. The rotation adjustment assembly 3 includes a rotation connecting shaft 31 and a driving motor. The two ends of the rotation connecting shaft 31 are respectively connected to the frame-shaped mounting bracket 4 and the damping mounting bracket 21. The damping mounting bracket 21 rotates under the drive of the driving motor to ensure the effective rotation of the frame-shaped mounting bracket 4 and realize the effective switching of different states of different buffer and shock absorption units 2.

[0042] In this embodiment, the sheet-shaped elastic conductor 22 is a non-ferromagnetic conductor with high electrical conductivity (such as copper, aluminum, copper alloy or aluminum alloy, etc.) to increase the intensity of eddy current in the sheet-shaped elastic conductor 22. At the same time, the length of the non-ferromagnetic conductor is equal to the length of the energy-consuming magnetic steel 23 to better cooperate to generate eddy current damping braking force and achieve the safe and stable landing of the rocket.

[0043] 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. A plate damper for rocket recovery, comprising a rocket body, characterized in that, It also includes a plurality of buffer and vibration damping units and a rotation adjustment assembly. The plurality of buffer and vibration damping units are arranged along the outer periphery of the rocket body. The buffer and vibration damping unit includes a damping mounting frame, sheet-shaped elastic conductor pieces and energy-consuming permanent magnets arranged alternately along the length direction of the damping mounting frame, and a ventilation channel provided between the sheet-shaped elastic conductor pieces and the energy-consuming permanent magnets. The damping mounting frame is rotatably arranged through the rotation adjustment assembly; when the rocket is in the landing state, the ventilation channel provided on the damping mounting frame rotates to a position where the vertical wind cannot penetrate the damping mounting frame; when the rocket is in the vibration damping state, the ventilation channel rotates to a position where the vertical wind penetrates the damping mounting frame, and the sheet-shaped elastic conductor piece vibrates under the action of the vertical wind and generates eddy current damping with the energy-consuming permanent magnets.

2. The chip damper for rocket recovery according to claim 1, wherein The sheet-shaped elastic conductor piece is a curved sheet-shaped conductor plate, and the ventilation channel overlaps with the curved section of the curved sheet-shaped conductor plate to drive the curved sheet-shaped conductor plate to vibrate when the vertical wind enters.

3. The chip damper for rocket recovery according to claim 2, wherein, The ventilation channel includes an upper ventilation hole, a through section and a lower ventilation hole that are sequentially connected. The upper ventilation hole and the lower ventilation hole are oppositely arranged on the damping mounting frame, and the through section is parallel to the curved sheet-shaped conductor plate and is arranged to penetrate along the height direction of the damping mounting frame.

4. The chip damper for rocket recovery according to claim 3, wherein, The damping mounting frame is a frame-type damping mounting frame. The frame-type damping mounting frame is provided with magnet mounting plates at intervals along the length direction, and the energy-consuming permanent magnets are symmetrically arranged on both sides of the magnet mounting plates; the ventilation channel is located between the magnet mounting plate and the sheet-shaped elastic conductor piece.

5. The chip damper for rocket recovery according to any one of claims 2 to 4, characterized in that, The curved sheet-shaped conductor plate is an S-shaped conductor plate or a Z-shaped conductor plate, and both ends of the S-shaped conductor plate or the Z-shaped conductor plate are fixedly installed on the frame-type damping mounting frame through connection mounting plates.

6. The sheet damper for rocket recovery according to any one of claims 1 to 4, characterized in that The rotation plane of the damping mounting frame when driven by the rotation adjustment assembly is tangent to the rocket body.

7. The sheet damper for rocket recovery according to claim 6, wherein When the rocket is in the landing state, the damping mounting frame rotates to a vertical arrangement through the rotation adjustment assembly, and the ventilation channel is arranged perpendicular to the direction of the vertical wind; when the rocket is in the vibration damping state, the damping mounting frame rotates to a horizontal arrangement through the rotation adjustment assembly, and the ventilation channel is arranged parallel to the direction of the vertical wind.

8. The sheet damper for rocket recovery according to any one of claims 1 to 4, characterized in that, It also includes a frame-type mounting frame. There are four groups of the buffer and vibration damping units, and the four groups of buffer and vibration damping units are rotatably mounted on the four sides of the frame-type mounting frame through the rotation adjustment assembly. An installation fitting groove adapted to the outer surface of the rocket body is provided in the middle of the frame-type mounting frame.

9. The chip damper for rocket recovery according to claim 8, characterized in that, The rotation adjustment assembly is mounted on the frame-type mounting frame. The rotation adjustment assembly includes a rotation connecting shaft and a driving motor. The two ends of the rotation connecting shaft are respectively connected to the frame-type mounting frame and the damping mounting frame, and the damping mounting frame rotates under the drive of the driving motor.

10. The chip damper for rocket recovery according to any one of claims 1 to 4, characterized in that, The sheet-shaped elastic conductor piece is a non-ferromagnetic conductor piece with high electrical conductivity, and the length of the non-ferromagnetic conductor piece is equal to the length of the energy-consuming permanent magnet.

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