Rocket stand-alone vibration reduction device, carrier rocket and rocket stand-alone vibration reduction method
By setting a rocket single-machine vibration damping device with vibration damping pads and limit pads between the rocket stand and the support, the problems of complex vibration damping structure design and low production efficiency in the prior art are solved, and efficient and flexible vibration damping effects are achieved.
Patent Information
- Application Number
- CN202311239772.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-09-25
- Publication Date
- 2025-02-25
AI Technical Summary
The existing rocket single-machine vibration-absorbing structure design is usually a special design, requiring processing of multiple size structures, resulting in low production efficiency, long cycles and high costs.
A rocket single-machine vibration damping device is designed, including a connector, a first vibration damping assembly and a second vibration damping assembly. By providing a vibration damping pad between the single-machine and the bracket, flexible contact and vibration damping effect are achieved, and stability is improved through the limit pad.
It achieves better vibration damping effect, simplifies the design and production process, reduces costs, improves production efficiency, and facilitates subsequent adjustment and optimization of vibration damping structure.
Smart Images
Figure CN119508426A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of single rocket vibration reduction, and in particular to a single rocket vibration reduction device, a launch vehicle and a single rocket vibration reduction method. Background Art
[0002] During the launch process of the launch vehicle, engine operation, structural separation, aerodynamic effects, etc. will produce a complex and harsh vibration environment, which is transmitted to the single equipment on the rocket through the rocket body structure, causing the electrical single equipment on the rocket to undergo a complex and harsh mechanical environment. In order to improve its working environment and improve product performance, it is necessary to reduce the original mechanical environmental conditions. Adopting a vibration-reducing connection structure is an effective post-processing measure.
[0003] At present, the design of vibration reduction structure is generally based on a certain single equipment. By designing a special vibration reduction structure, it is used to reduce vibration according to the test results. The vibration reduction structure is generally a special structure, and in the design process, it is necessary to process structures of various sizes and perform optimization work, which not only greatly reduces the production efficiency, but also has a long design and production cycle and high cost.
[0004] Therefore, there is an urgent need for a single-unit rocket vibration reduction device, a launch vehicle, and a single-unit rocket vibration reduction method to solve the above problems. Summary of the invention
[0005] Based on the above, the purpose of the present invention is to provide a rocket stand-alone vibration reduction device, a launch vehicle and a rocket stand-alone vibration reduction method, which have better vibration reduction effect and are convenient for subsequent adjustment and optimization, so that the launch vehicle has higher reliability in use.
[0006] To achieve the above object, the present invention adopts the following technical solutions:
[0007] A single rocket vibration reduction device, wherein the single rocket is mounted on the rocket bulkhead through a bracket, and wherein the single rocket vibration reduction device comprises:
[0008] A connecting piece, wherein a first connecting hole is formed on the single machine, and the connecting piece passes through the first connecting hole and is detachably connected to the bracket;
[0009] A first vibration damping assembly, comprising at least one first axial vibration damping pad, the first axial vibration damping pad being sleeved on the outer periphery of the connecting member and being arranged between the unit and the bracket, and / or the first vibration damping assembly comprising a first lateral vibration damping pad sleeved on the outer periphery of the connecting member, the first lateral vibration damping pad being in contact with a side of the unit close to the bracket and at least partially extending into the first connecting hole;
[0010] The second vibration damping assembly includes a second lateral vibration damping pad and a first limiting pad which are sleeved on the outer periphery of the connecting rod. The second lateral vibration damping pad is arranged on a side of the single machine away from the bracket and at least partially extends into the first mounting hole. The first limiting pad is pressed against a side of the second lateral vibration damping pad away from the single machine, and a first retaining edge is arranged on the outer periphery of the first limiting pad extending toward the direction of the single machine.
[0011] As a preferred solution of a single-unit vibration reduction device for a rocket, the second vibration reduction assembly further includes:
[0012] The second axial vibration damping pad is arranged between the second lateral vibration damping pad and the first limiting pad, and the first retaining edge is arranged around the second axial vibration damping pad.
[0013] As a preferred solution of a rocket stand-alone vibration reduction device, the rocket stand-alone vibration reduction device further includes:
[0014] The third vibration damping assembly includes a third lateral vibration damping pad and a second limiting pad which are sleeved on the outer periphery of the connecting member, a second connecting hole is opened on the bracket, the connecting member passes through the second connecting hole, the third lateral vibration damping pad is arranged on the side of the bracket away from the single machine and at least partially extends into the second connecting hole, the second limiting pad is pressed against the side of the third lateral vibration damping pad away from the bracket, and a second retaining edge is arranged on the outer periphery of the second limiting pad extending toward the bracket.
[0015] As a preferred solution of a single-unit vibration reduction device for a rocket, the third vibration reduction assembly further includes:
[0016] The third axial vibration damping pad is arranged between the third lateral vibration damping pad and the second limiting pad, and the second retaining edge is arranged around the third axial vibration damping pad.
[0017] As a preferred solution of a rocket stand-alone vibration reduction device, the connecting member includes a screw, a threaded hole is provided on the bracket, and the screw passes through the first connecting hole and is threadedly connected to the threaded hole; or
[0018] The connecting member includes a screw and a nut. The screw passes through the first connecting hole and the second connecting hole and is threadedly connected with the nut. The nut abuts against the second limiting pad.
[0019] A launch vehicle comprises a rocket cabin, a single unit, a bracket and the rocket single unit vibration reduction device described in any of the above technical solutions, the bracket is fixed to the cabin wall of the rocket cabin, and the single unit is installed on the bracket through the rocket single unit vibration reduction device.
[0020] A rocket stand-alone vibration reduction method, based on the above-mentioned rocket stand-alone vibration reduction device, comprises the following steps:
[0021] S100: Assembling the connecting member, the first vibration reduction assembly and the second vibration reduction assembly to a target stand-alone machine and a target bracket;
[0022] S200: obtaining the installation frequency of the target stand-alone machine during testing or use, comparing the installation frequency with a preset installation frequency, and increasing or decreasing the first axial vibration damping pad and the first lateral vibration damping pad according to the comparison value.
[0023] As a preferred solution of a single rocket vibration reduction method, the following steps are further included before step S100:
[0024] S001: designing a plurality of groups of vibration damping assemblies, wherein the number of the first axial vibration damping pads and / or the first lateral vibration damping pads in each group of the vibration damping assemblies is different;
[0025] S002: Test the test unit equipped with different vibration reduction combinations to obtain the natural frequency f1 of the test unit, and calculate the comprehensive stiffness coefficient K1 corresponding to each vibration reduction combination based on the natural frequency and the mass m1 of the test unit, where
[0026] S003: Obtain the required comprehensive stiffness coefficient K2 according to the target single machine weight m2 and the preset installation frequency f2, where
[0027] S004: Select the K1 having the smallest difference with the K2, select the vibration reduction combination corresponding to K1, and assemble the vibration reduction combination to the target single machine.
[0028] As a preferred scheme for a rocket single-unit vibration reduction method, in step S002, the test single unit and the vibration reduction combination have n1 connection points. When the vibration reduction combination to be assembled on the target single unit has n2 connection points, the comprehensive stiffness coefficient required for the target single unit is obtained according to calculation.
[0029] As a preferred solution for a single-unit rocket vibration reduction method, in step S004, when the K1 with the smallest difference with the K2 is selected, it is determined whether the difference between the resonant frequency and the excitation frequency of the K1 and the rocket body is within a preset range. If it is within the preset range, the K1 closest to the K2 is selected.
[0030] The beneficial effects of the present invention are:
[0031] The present invention provides a single-unit rocket vibration reduction device, which includes a connecting piece, a first vibration reduction assembly and a second vibration reduction assembly. By arranging the first vibration reduction assembly between the single unit and a bracket, a flexible contact between the single unit and the bracket is achieved to achieve a vibration reduction effect. In addition, a first lateral vibration reduction pad and / or a first axial vibration reduction pad can be selectively arranged between the single unit and the bracket according to the vibration reduction requirements to meet the vibration reduction requirements and improve the vibration reduction effect. At the same time, by arranging the second vibration reduction assembly on the side of the single unit away from the bracket, the vibration reduction effect is further improved. The second lateral vibration reduction pad can effectively reduce the shaking displacement of the connecting piece in the first connecting hole, increase the lateral stiffness, and be limited by the first limiting pad to improve the stability of the connecting piece and the first lateral vibration reduction pad. The rocket stand-alone vibration reduction device has good versatility and can be used in flat-plate connections without designed built-in interfaces. The connection parts can also be processed in advance so that the first vibration reduction component and the second vibration reduction component are embedded in the connection surface. It is easy to adjust the characteristics of the vibration reduction structure, quickly change and optimize the vibration reduction structure, and has a large adjustment range. The number of additional parts is small, and standardized spare parts can be formed according to the size of the connecting parts, which can quickly respond to later vibration reduction needs.
[0032] The present invention also provides a launch vehicle, which includes a rocket cabin, a single unit, a bracket and the above-mentioned rocket single unit vibration reduction device. By assembling the rocket single unit vibration reduction device between the single unit and the bracket, the working environment of the single unit is improved, the probability of damage during vibration is reduced, the service life of the single unit is effectively extended, and the working reliability is improved, thereby improving the use reliability of the launch vehicle.
[0033] The present invention also provides a method for reducing vibration of a single rocket unit. By assembling the connector, the first vibration reduction assembly and the second vibration reduction assembly of the above-mentioned single rocket unit vibration reduction device on the target unit and the target bracket, the first axial vibration reduction pad, the first lateral vibration reduction pad and the second lateral vibration reduction pad can all play a role in reducing vibration and improve the vibration environment of the target unit. In the subsequent test or use process, the installation frequency of the target unit is collected, and the first axial vibration reduction pad and the first lateral vibration reduction pad are increased or decreased according to the collected installation frequency to adjust and optimize the vibration reduction structure and improve the vibration reduction effect. The method for reducing vibration of a single rocket unit can not only reduce vibration of the target unit, but also adjust and optimize the vibration reduction effect in a timely manner. Moreover, since the single rocket unit vibration reduction device has a simple structure and is easy to disassemble and assemble, it is convenient to quickly adjust the vibration reduction structure. BRIEF DESCRIPTION OF THE DRAWINGS
[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.
[0035] Figure 1 is a cross-sectional view of a single rocket vibration reduction device provided by one embodiment of the present invention;
[0036] Figure 2 is a cross-sectional view of a single rocket vibration reduction device provided by another embodiment of the present invention;
[0037] Figure 3 The process of the rocket single machine vibration reduction method provided by the embodiment of the present invention is as follows Figure 1 ;
[0038] Figure 4 The process of the rocket single machine vibration reduction method provided by the embodiment of the present invention is as follows Figure 2 .
[0039] In the figure:
[0040] 1. Single machine; 10. First connecting hole; 2. Bracket; 20. Second connecting hole; 3. Connector; 31. Nut; 4. First vibration damping assembly; 41. First axial vibration damping pad; 42. First lateral vibration damping pad; 5. Second vibration damping assembly; 51. Second lateral vibration damping pad; 52. First limiting pad; 53. Second axial vibration damping pad; 6. Third vibration damping assembly; 61. Third lateral vibration damping pad; 62. Second limiting pad; 63. Third axial vibration damping pad; 7. Spring pad. DETAILED DESCRIPTION
[0041] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.
[0042] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0043] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.
[0044] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.
[0045] During the launch process of the launch vehicle, engine operation, structural separation, aerodynamic effects, etc. will produce a complex and harsh vibration environment, which is transmitted to the single equipment on the rocket through the rocket body structure, causing the electrical single equipment on the rocket to undergo a complex and harsh mechanical environment. In order to improve its working environment and improve product performance, it is necessary to reduce the original mechanical environmental conditions. Adopting a vibration-reducing connection structure is an effective post-processing measure.
[0046] At present, the design of vibration reduction structure is generally based on a certain single equipment. By designing a special vibration reduction structure, it is used to reduce vibration according to the test results. The vibration reduction structure is generally a special structure, and in the design process, it is necessary to process structures of various sizes and perform optimization work, which not only greatly reduces the production efficiency, but also has a long design and production cycle and high cost.
[0047] Based on the above technical problems, this embodiment provides a rocket single-unit vibration reduction device to improve the vibration environment of the single unit 1, such as Figure 1 and Figure 2As shown, the single unit 1 is installed on the rocket's bulkhead through the bracket 2, that is, the bracket 2 is fixed on the rocket's bulkhead, and the single unit 1 is connected to the bracket 2. Specifically, the rocket single unit vibration reduction device includes a connector 3, a first vibration reduction assembly 4 and a second vibration reduction assembly 5. The single unit 1 is provided with a first connection hole 10, and the connector 3 passes through the first connection hole 10 and is detachably connected to the bracket 2. For example, the connector 3 is a screw, and the screw is threadedly connected to the bracket 2, or the connector 3 includes a screw and a nut 31, and the bracket 2 is provided with a second connection hole 20. The screw passes through the first connection hole 10 and the second connection hole 20 and is threadedly connected to the nut 31. The structure is simple and convenient, and it is easy to disassemble and assemble. It should be noted that only a part of the rod of the screw can be provided with an external thread, or the rod can be provided with an external thread, which is specifically set according to actual needs. Of course, the connector 3 can also be other structures, such as a bayonet and a retaining spring. The first vibration damping assembly 4 includes at least one first axial vibration damping pad 41, which is sleeved on the outer periphery of the connecting member 3 and is arranged between the unit 1 and the bracket 2, and / or the first vibration damping assembly 4 includes a first lateral vibration damping pad 42, which abuts against a side of the unit 1 close to the bracket 2 and at least partially extends into the first connecting hole 10, or the first lateral vibration damping pad 42 abuts against a side of the bracket 2 close to the unit 1 and at least partially extends into the second connecting hole 20, or there are two first lateral vibration damping pads 42, one first lateral vibration damping pad 42 partially extends into the first connecting hole 10, and the other first lateral vibration damping pad 42 partially extends into the second connecting hole 20. The first lateral vibration damping pad and the first axial vibration damping pad 41 can absorb vibration and play a vibration damping effect, so that the unit 1 and the unit 1 are in flexible contact, the vibration environment of the unit 1 is improved, and its working reliability is ensured; and the first lateral vibration damping pad 42 can increase the lateral stiffness and achieve a vibration damping effect from multiple directions. The second vibration damping assembly 5 includes a second lateral vibration damping pad 51 and a first limiting pad 52 sleeved on the outer periphery of the connecting rod. The second lateral vibration damping pad 51 is arranged on the side of the single machine 1 away from the bracket 2 and at least partially extends into the first mounting hole. The first limiting pad 52 presses against the side of the second lateral vibration damping pad 51 away from the single machine 1, and the outer periphery of the first limiting pad 52 is provided with a first retaining edge extending toward the direction of the single machine 1. Among them, a step surface is formed on the outer periphery of the connecting member 3, and the first limiting pad 52 abuts between the step surface and the second lateral vibration damping pad 51, that is, the step surface plays a limiting role. Exemplarily, when the connecting member 3 includes a screw, the screw head and the rod form the step surface. The vibration damping effect is further increased by the second lateral vibration damping pad 51, which can effectively reduce the shaking displacement of the connecting member 3 in the first connecting hole 10, increase the lateral stiffness, and limit the first limiting pad 52 to improve the stability of the connecting member 3 and the first lateral vibration damping pad 42.The rocket stand-alone vibration reduction device has good versatility and can be used in flat-plate connections without designed built-in interfaces. The connection parts can also be processed in advance so that the first vibration reduction assembly 4 and the second vibration reduction assembly 5 are embedded in the connection surface. The number of first axial vibration reduction pads 41 can be adjusted according to demand, which is convenient for adjusting the characteristics of the vibration reduction structure, quickly changing and optimizing the vibration reduction structure, and has a large adjustment range. The number of additional parts is small, and standardized spare parts can be formed according to the size of the connector 3, which can quickly respond to later vibration reduction needs.
[0048] More specifically, the second vibration damping assembly 5 also includes a second axial vibration damping pad 53, which is arranged between the second lateral vibration damping pad 51 and the first limiting pad 52, and the first rib is arranged around the second axial vibration damping pad 53. By setting the second axial vibration damping pad 53, the axial vibration damping effect can be increased, and the adjustable range of vibration damping can be larger. That is, the second axial vibration damping pad 53 can be increased or decreased according to demand, and the number of the second axial vibration damping pads 53 can be adjusted to ensure the best vibration damping effect. At the same time, the first rib on the first limiting pad 52 can prevent the second axial vibration damping pad 53 from excessively expanding laterally and affecting the axial vibration damping effect and service life.
[0049] Preferably, a spring washer 7 is further provided between the screw head and the first limiting washer 52. After the screw is tightened, the spring washer 7 exerts an upward force on the screw head to prevent the screw from loosening.
[0050] like Figure 2 As shown, when a second connecting hole 20 is opened on the bracket 2, the connecting member 3 passes through the second connecting hole 20. In order to further improve the vibration reduction effect and expand the adjustable range of vibration reduction, the rocket single-unit vibration reduction device also includes a third vibration reduction assembly 6. The third vibration reduction assembly 6 includes a third lateral vibration reduction pad 61 and a second limiting pad 62 which are sleeved on the outer periphery of the connecting member 3. The third lateral vibration reduction pad 61 is arranged on the side of the bracket 2 away from the single unit 1 and at least partially extends into the second connecting hole 20. The second limiting pad 62 is pressed against the side of the third lateral vibration reduction pad 61 away from the bracket 2, and a second retaining edge is provided on the outer periphery of the second limiting pad 62 extending toward the bracket 2. By setting the third lateral vibration damping pad 61, a good limiting effect is played on the connecting member 3, and the lateral stiffness is increased, which can effectively increase the lateral vibration damping effect; at the same time, the second limiting pad 62 is used for limiting, which further improves the stability of the connecting member 3 and the third lateral vibration damping pad 61, and the second limiting pad 62 can limit the third lateral vibration damping pad 61 from excessive lateral expansion and affecting the service life. In this embodiment, when the connecting member 3 includes a screw and a nut 31, the second limiting pad 62 abuts between the nut 31 and the third lateral vibration damping pad 61, or a step surface is provided on the outer periphery of the connecting member 3, and the second limiting pad 62 abuts between the third lateral vibration damping pad 61 and the step surface.
[0051] Specifically, the third damping assembly 6 further includes a third axial damping pad 63. The third axial damping pad 63 is disposed between the third lateral damping pad 61 and the second limiting pad 62, and the second rib surrounds the third axial damping pad 63. By providing the third axial damping pad 63, the axial damping effect can be increased, and the adjustable range of damping is relatively large. That is, the third axial damping pad 63 can be increased or decreased and the number of the third axial damping pads 63 can be adjusted according to requirements to ensure the best damping effect. At the same time, the second rib on the second limiting pad 62 can prevent the third axial damping pad 63 from expanding laterally excessively and affecting the axial damping effect and service life.
[0052] In this embodiment, the first lateral damping pad 42, the second lateral damping pad 51, and the third lateral damping pad 61 have the same structure. Taking the first lateral damping pad 42 as an example, the first lateral damping pad 42 includes a body and a convex ring protruding from the body. A through hole is formed in the body opposite to the convex ring. The connecting member 3 can pass through the through hole and the convex ring, and the convex ring can be embedded in the first connection hole 10 or the second connection hole 20. Exemplarily, the inner diameter d1 of the convex ring and the outer diameter d2 of the body, wherein, 3d1 < d2 < 4d1, so that it has a certain stability and load-bearing capacity, and at the same time, the area is not too large to occupy too much installation area; the inner diameter d1 is larger than the diameter of the screw, for example, the difference is 1 mm to 4 mm; so that the convex ring positions the screw and increases the lateral stiffness, and since the convex ring is partially embedded between the screw and the first connection hole 10 or the second connection hole 20, its compression amount is small, so the reserved gap can be slightly smaller; the thickness range of the convex ring is 6 mm to 8 mm, which matches the screw, the first connection hole 10, and the second connection hole 20; the height of the body plus the convex ring is 6 mm to 10 mm, and the convex ring accounts for half of the total height. The convex ring plays a limiting role, separating the screw from the hole wall, achieving the effects of damping and increasing the lateral stiffness.
[0053] In one embodiment, the first axial damping pad 41, the second axial damping pad 53, and the third axial damping pad 63 have the same structure, and are all elastic washers. The inner diameter d3 and the outer diameter d4 of the elastic washer, wherein, 3d3 < d4 < 4d3, so that it needs to have a certain stability and load-bearing capacity, and at the same time, the area is not too large to occupy too much installation area. The inner diameter is 2 mm to 4 mm larger than the diameter of the screw. After compression, the inner diameter of the elastic washer will decrease, and a gap needs to be reserved. The thickness h1 is generally 3 mm to 5 mm. Considering the load-bearing capacity and adjustment gradient comprehensively, the load-bearing capacity is ensured and it is not easily crushed. At the same time, considering the change amount of the structural frequency characteristics after adding a single elastic washer, an appropriate thickness is beneficial to reducing the change amount and improving the smoothness of adjustment.
[0054] In one embodiment, the first limiting pad 52 and the second limiting pad 62 have the same size and structure, and are both made of metal materials with a thickness of 1mm-2mm to ensure the strength of use. For the convenience of description, the first limiting pad 52 and the second limiting pad 62 are both described as limiting pads, and a groove is provided on the limiting pad, and the groove edge of the groove is a retaining edge. The inner diameter of the groove is greater than 1mm to 2mm of the outer diameter of the elastic gasket to accommodate the lateral expansion of the elastic gasket after compression, and to ensure the limiting effect. Preferably, the groove wall and the groove bottom are chamfered, and the free end of the retaining edge is also chamfered to prevent the elastic gasket from being cut during expansion. At the same time, the inner ring diameter of the limiting pad is greater than 1mm to 2mm of the screw diameter, and is less than or equal to the inner diameter of the elastic gasket to ensure the gap between the inner ring and the screw. At the same time, the area of the elastic gasket is covered as much as possible so that it is evenly stressed.
[0055] The rocket single-unit vibration reduction device provided in this embodiment can effectively reduce vibration of the single unit 1, improve the vibration environment of the single unit 1, and ensure its working reliability. And the first axial vibration reduction pad 41, the second axial vibration reduction pad 53, the third axial vibration reduction pad 63, the first lateral vibration reduction pad 42, the second lateral vibration reduction pad 51 and the third lateral vibration reduction pad 61 can all adjust the quantity and position according to the vibration reduction requirements, with high flexibility and good adjustment convenience; at the same time, it is easy to produce as a standard accessory to quickly respond to the later vibration reduction requirements and improve production efficiency. For example, when the screw passes through the first connecting hole 10 and is threadedly connected to the bracket 2, a first lateral vibration reduction pad 42 is arranged between the bracket 2 and the single unit 1, and the convex ring of the first lateral vibration reduction pad 42 extends into the first connecting hole 10, and the screw is also sleeved with a first limiting pad 52, and a second lateral vibration reduction pad 51 is arranged between the single unit 1 and the first limiting pad 52, and the convex ring of the second lateral vibration reduction pad 51 extends into the second connecting hole 20. If the vibration reduction amplitude needs to be increased, one or more first axial vibration reduction pads 41 can be selectively added between the bracket 2 and the single machine 1, or one or more second axial vibration reduction pads 53 can be added between the second lateral vibration reduction pads 51 and the first limiting pads 52. When the screw passes through the first connection hole 10 and the second connection hole 20 and is threadedly connected with the nut 31, the first limiting pad 52 and the second limiting pad 62 are sleeved on the screw, the third lateral vibration reduction pad 61 is padded between the bracket 2 and the second limiting pad 62, and the convex ring of the third lateral vibration reduction pad 61 extends into the second connection, the first axial vibration reduction pad 41 is padded between the single machine 1 and the bracket 2, and the second lateral vibration reduction pad 51 is padded between the single machine 1 and the first limiting pad 52, and the convex ring of the second lateral vibration reduction pad 51 extends into the first connection. If the vibration reduction amplitude needs to be increased, one or more first axial vibration reduction pads 41, first lateral vibration reduction pads 42, one or more second axial vibration reduction pads 53 between the second lateral vibration reduction pads 51 and the first limiting pads 52, or one or more third axial vibration reduction pads 63 between the second limiting pads 62 and the third lateral vibration reduction pads 61 can be selectively added between the bracket 2 and the single unit 1. That is, the single rocket vibration reduction device can combine multiple vibration reduction forms to meet various vibration reduction requirements and improve practicality.
[0056] This embodiment also provides a launch vehicle, which includes a rocket cabin, a single unit 1, a bracket 2 and the above-mentioned rocket single unit vibration reduction device. The bracket 2 is fixed to the wall of the rocket cabin, and the single unit 1 is installed on the bracket 2 through the rocket single unit vibration reduction device. The single unit 1 can be assembled with the bracket 2 through multiple rocket single unit vibration reduction devices. For example, if the single unit 1 and the bracket 2 have four connection points, they are assembled through four rocket single unit vibration reduction devices. By assembling the rocket single unit vibration reduction device between the single unit 1 and the bracket 2, the working environment of the single unit 1 is improved, the probability of damage during vibration is reduced, and its service life can be effectively extended, and the working reliability is improved, thereby improving the reliability of the launch vehicle.
[0057] like Figure 3 and Figure 4 As shown, this embodiment also provides a single rocket vibration reduction method, based on the above-mentioned single rocket vibration reduction device, specifically including the following steps:
[0058] S100: Assemble the connecting member 3, the first vibration damping assembly 4 and the second vibration damping assembly 5 onto the target stand-alone machine 1 and the target bracket 2; if the target bracket 2 is provided with a second connecting hole 20, the connecting member 3 passes through the first connecting hole 10 and the second connecting hole 20, and the third vibration damping assembly 6 needs to be assembled onto the target stand-alone machine 1 and the target bracket 2 to ensure the minimum vibration damping effect.
[0059] S200: During the test or use, the installation frequency of the target unit 1 is obtained, the installation frequency is compared with the preset installation frequency, and the first axial vibration damping pad 41 and the first lateral vibration damping pad 42 are increased or decreased according to the comparison value. For example, if the vibration frequency collected during the test or use is still relatively high, the first axial vibration damping pad 41 and / or the first lateral vibration damping pad 42 are increased. Of course, according to the rocket unit vibration damping device described above, the second axial vibration damping pad 53 and the third axial vibration damping pad 63 can also be increased or decreased, and the adjustment range is relatively large.
[0060] In order to reduce the time for adjusting the vibration reduction, before assembling the single machine 1, a vibration reduction scheme may be designed and reference data may be formed. Specifically, before step S100, the following steps may be included:
[0061] S001: Design multiple groups of vibration damping combinations, wherein the number and position of the first axial vibration damping pads 41 and / or the first lateral vibration damping pads 42 in each group of vibration damping combinations are different, or the number of the second axial vibration damping pads 53 is different, the number of the third axial vibration damping pads 63 is different, etc.;
[0062] S002: Test the test unit equipped with different vibration reduction combinations to obtain the natural frequency f1 of the test unit, and calculate the comprehensive stiffness coefficient K1 corresponding to each vibration reduction combination based on the natural frequency and the mass m1 of the test unit, where A single machine 1 with known mass is selected as a test single machine, and various vibration reduction combinations are respectively assembled into the test single machine, and tests are carried out to obtain the axial natural frequency and lateral natural frequency corresponding to each vibration reduction combination. Then, the axial comprehensive stiffness coefficient and lateral comprehensive stiffness coefficient corresponding to each vibration reduction combination are calculated according to the formula, that is, a database of various vibration reduction combinations can be formed, so that a suitable vibration reduction combination can be quickly selected when assembling the target single machine 1, thereby shortening the time for adjusting the vibration reduction.
[0063] S003: Obtain the required comprehensive stiffness coefficient K2 according to the weight m2 of the target single machine 1 and the preset installation frequency f2, where During the actual assembly process, it is necessary to control the installation frequency of the target unit 1 within a suitable range, that is, to have an axial preset installation frequency and a lateral preset installation frequency, and then calculate the required axial comprehensive stiffness coefficient and lateral comprehensive stiffness coefficient corresponding to the target unit 1 through the formula, and then refer to the database obtained in the previous step to compare K2 with each K1 in the database. Exemplarily, the preset installation frequency of the target unit 1 is about 80Hz to 120Hz. It is necessary to avoid the low-frequency part to avoid resonance with the rocket body structure (for example: more than twice the natural frequency of the rocket body), and also to consider avoiding specific excitation frequencies (for example: engine turbo pump rotation frequency), and at the same time as low as possible, so that the energy of the high-frequency part is attenuated as soon as possible to achieve a better vibration reduction effect. At the same time, it is necessary to consider the installation direction and sensitive direction of the unit 1, and design with a certain direction as the main target.
[0064] S004: Select K1 with the smallest difference from K2, and select the vibration reduction combination corresponding to K1, and assemble the vibration reduction combination to the target single machine 1. According to the database, the closest known vibration reduction combination can be quickly obtained, which is convenient for rapid assembly and achieves a better vibration reduction effect. It should be noted that when selecting K1 with the smallest difference from K2, it is determined whether the difference between K1 and the resonant frequency of the rocket body and the excitation frequency (such as the engine turbo pump rotation frequency) is within the preset range. If it is within the preset range, select another K1 that is closest to K2. Among them, the preset range is the design margin. Considering the structural nonlinearity, the difference between the sky and the earth, the unrecognized situation, and the robustness, a certain design margin needs to be maintained; for example, after increasing the excitation magnitude, the single machine 1 can still work normally, and the frequency characteristics can still avoid the engine turbo pump rotation frequency.
[0065] In this embodiment, the stand-alone 1 and the bracket 2 can be connected by multiple connectors 3, that is, there are multiple connection points, such as 4, 5 or 6. When the connection points of the target stand-alone 1 are different from the connection points of the test stand-alone 1, the conversion is performed in the following manner. When the test stand-alone 1 is tested to form a database, the test stand-alone and the vibration reduction combination have n1 connection points. When the vibration reduction combination to be assembled with the target stand-alone 1 has n2 connection points, according to The comprehensive stiffness coefficient required by the target stand-alone machine 1 is calculated. The above method makes the database have better reference and practicality.
[0066] Furthermore, the above steps can quickly determine the applicable vibration reduction combination that is closest to the target single machine 1, and then adjust the vibration reduction effect by increasing or decreasing it during subsequent tests or use. When adjusting the vibration reduction effect, the following situations can be referred to:
[0067] The more the first axial vibration damping pads 41, the second axial vibration damping pads 53, and the third axial vibration damping pads 63 are used, the lower the stiffness and the lower the frequency, and the more obvious the attenuation effect on high-frequency vibration is;
[0068] The larger the mass of the single machine 1 is, the lower the frequency is. Generally, it is necessary to reduce the number of the first axial vibration damping pad 41, the second axial vibration damping pad 53, the third axial vibration damping pad 63 or the first lateral vibration damping pad 42 for matching;
[0069] When the lateral stiffness needs to be increased, a first lateral vibration damping pad 42 may be added;
[0070] If increasing or decreasing the number cannot meet both axial and lateral requirements, you can consider reducing or increasing the outer diameter. Under the same number of layers, the larger the outer diameter, the better the axial stiffness and the better the lateral stiffness. As the outer diameter decreases, the lateral stiffness decreases more than the axial stiffness. Therefore, the axial and lateral frequencies can be matched by adjusting the outer diameter.
[0071] Considering the vibration reduction structure and force characteristics, there are certain differences between the axial and lateral frequencies, which need to be considered comprehensively;
[0072] After determining the basic combination of vibration damping pads, you can also make fine adjustments by adjusting the tightening torque. Tightening can increase rigidity.
[0073] The number of the first axial vibration damping pad 41, the second axial vibration damping pad 53, and the third axial vibration damping pad 63 is controlled within a certain range to avoid excessive number resulting in a higher vibration damping structure and too low lateral stiffness, which causes a larger displacement during low-frequency vibration and is easy to couple with the arrow body structure frequency to cause resonance.
[0074] Through the rocket single-unit vibration reduction device and the rocket single-unit 1 vibration reduction method, the single-unit 1 has a better vibration environment after being assembled on the bracket 2. After vibration reduction, the effective value of random vibration is attenuated by about 45%, which effectively improves the working reliability of the single-unit 1 and reduces the risk of damage to the single-unit 1.
[0075] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims
1. A single rocket vibration reduction device, wherein the single rocket is mounted on the rocket bulkhead via a bracket, characterized in that: The rocket single-unit vibration reduction device comprises: A connecting piece, wherein a first connecting hole is formed on the single machine, and the connecting piece passes through the first connecting hole and is detachably connected to the bracket; A first vibration damping assembly, comprising at least one first axial vibration damping pad, the first axial vibration damping pad being sleeved on the outer periphery of the connecting member and being arranged between the unit and the bracket, and / or the first vibration damping assembly comprising a first lateral vibration damping pad sleeved on the outer periphery of the connecting member, the first lateral vibration damping pad being in contact with a side of the unit close to the bracket and at least partially extending into the first connecting hole; The second vibration damping assembly includes a second lateral vibration damping pad and a first limiting pad which are sleeved on the outer periphery of the connecting rod. The second lateral vibration damping pad is arranged on a side of the single machine away from the bracket and at least partially extends into the first connecting hole. The first limiting pad is pressed against a side of the second lateral vibration damping pad away from the single machine, and a first retaining edge is arranged on the outer periphery of the first limiting pad extending toward the direction of the single machine.
2. The rocket stand-alone vibration reduction device according to claim 1, characterized in that: The second vibration reduction assembly also includes: The second axial vibration damping pad is arranged between the second lateral vibration damping pad and the first limiting pad, and the first retaining edge is arranged around the second axial vibration damping pad.
3. The rocket stand-alone vibration reduction device according to claim 1, characterized in that: The rocket stand-alone vibration reduction device also includes: The third vibration damping assembly includes a third lateral vibration damping pad and a second limiting pad which are sleeved on the outer periphery of the connecting member, a second connecting hole is opened on the bracket, the connecting member passes through the second connecting hole, the third lateral vibration damping pad is arranged on the side of the bracket away from the single machine and at least partially extends into the second connecting hole, the second limiting pad is pressed against the side of the third lateral vibration damping pad away from the bracket, and a second retaining edge is arranged on the outer periphery of the second limiting pad extending toward the bracket.
4. The rocket stand-alone vibration reduction device according to claim 3, characterized in that: The third vibration reduction assembly further comprises: The third axial vibration damping pad is arranged between the third lateral vibration damping pad and the second limiting pad, and the second retaining edge is arranged around the third axial vibration damping pad.
5. The rocket stand-alone vibration reduction device according to claim 1 or 3, characterized in that: The connecting member includes a screw, a threaded hole is provided on the bracket, and the screw passes through the first connecting hole and is threadedly connected to the threaded hole; or The connecting member includes a screw and a nut. The screw passes through the first connecting hole and the second connecting hole and is threadedly connected with the nut. The nut abuts against the second limiting pad.
6. A launch vehicle, characterized in that: The launch vehicle includes a rocket cabin, a single unit, a bracket and the rocket single unit vibration reduction device according to any one of claims 1 to 5, the bracket is fixed to the cabin wall of the rocket cabin, and the single unit is installed on the bracket through the rocket single unit vibration reduction device.
7. A method for reducing vibration of a single rocket, based on the single rocket vibration reduction device according to any one of claims 1 to 5, characterized in that: The following steps are involved: S100: Assembling the connecting member, the first vibration reduction assembly and the second vibration reduction assembly to a target stand-alone machine and a target bracket; S200: obtaining the installation frequency of the target stand-alone machine during testing or use, comparing the installation frequency with a preset installation frequency, and increasing or decreasing the first axial vibration damping pad and the first lateral vibration damping pad according to the comparison value.
8. A single rocket vibration reduction method according to claim 7, characterized in that: Before step S100, the method further includes the following steps: S001: designing a plurality of groups of vibration damping assemblies, wherein the number of the first axial vibration damping pads and / or the first lateral vibration damping pads in each group of the vibration damping assemblies is different; S002: Test the test unit equipped with different vibration reduction combinations to obtain the natural frequency f1 of the test unit, and calculate the comprehensive stiffness coefficient K1 corresponding to each vibration reduction combination based on the natural frequency and the mass m1 of the test unit, where S003: Obtain the required comprehensive stiffness coefficient K2 according to the target single machine weight m2 and the preset installation frequency f2, where S004: Select the K1 having the smallest difference with the K2, select the vibration reduction combination corresponding to K1, and assemble the vibration reduction combination to the target single machine.
9. A rocket single-unit vibration reduction method according to claim 8, characterized in that: In step S002, the test unit and the vibration reduction assembly have n1 connection points. When the vibration reduction assembly to be assembled on the target unit has n2 connection points, The comprehensive stiffness coefficient required for the target single machine is calculated.
10. A rocket single-unit vibration reduction method according to claim 8, characterized in that: In step S004, when the K1 with the smallest difference with the K2 is selected, it is determined whether the difference between the resonance frequency and the excitation frequency of the K1 and the rocket body is within a preset range. If so, another K1 closest to the K2 is selected.