A vibration damping device for electrical components near a rocket separation explosive bolt

Abstract

The application provides a device for damping the vibration of an electrical component near an explosion bolt for separating a rocket, comprising: a first damping mechanism having a connecting surface for connecting with a rocket body; the first damping mechanism further has two connecting ends distributed along a first direction; the first direction is parallel to the connecting surface; two groups of second damping mechanisms, each of which is connected with a connecting end; the second damping mechanism extends along the first direction; and a mounting member installed between the two groups of second damping mechanisms and having a mounting surface for mounting the electrical component. The impact force generated by the explosion of the explosion bolt first acts on the rocket body, and the impact force acting on the electrical component after the double damping mechanisms are superimposed and damped is greatly reduced, so that the electrical component is protected from being damaged by the high impact force generated by the explosion of the explosion bolt during the separation of the rocket stage, i.e. the stability and reliability of the electrical component are ensured, thereby facilitating the successful completion of the rocket launch task.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket separation, in particular to a vibration reduction device for electrical components near a rocket separation explosive bolt. BACKGROUND

[0002] The separation of the stage section of a carrier rocket is generally achieved by using explosive bolts. Explosive bolts are mostly used for multi-point connection of the separation surface. In some application scenarios, electrical components are installed inside the separated rocket body. These electrical components still need to work after the separation explosion is completed. However, a great impact force is generated when the explosive bolt explodes. Most of the impact force is directly applied to the rocket body, which greatly affects the performance and reliability of the electrical components inside the separated rocket body. In particular, the electrical components close to the explosive bolt are easily damaged and fail under the great impact, which eventually leads to the failure of the corresponding instructions during the rocket launch process, resulting in the failure of the launch task to achieve the expected effect. Therefore, the present application provides a vibration reduction device for electrical components near a rocket separation explosive bolt. SUMMARY

[0003] The purpose of the present application is to provide a vibration reduction device for electrical components near a rocket separation explosive bolt to solve the above problems.

[0004] The present application provides a vibration reduction device for electrical components near a rocket separation explosive bolt, comprising:

[0005] A first damping mechanism having a connecting surface for connecting with a rocket body; the first damping mechanism further has two connecting ends distributed along a first direction; the first direction is parallel to the connecting surface;

[0006] Two groups of second damping mechanisms, each of the two groups of second damping mechanisms being connected with a connecting end; the second damping mechanism extends along the first direction;

[0007] A mounting member mounted between the two groups of second damping mechanisms, having a mounting surface for mounting electrical components.

[0008] According to the technical scheme provided by some embodiments of the present application, the first damping mechanism includes an upper plate spring and a lower plate spring distributed along a second direction; the second direction is perpendicular to the connecting surface; a first mounting space is formed between the upper plate spring and the lower plate spring; a first elastic member extending along the second direction is arranged in the first mounting space.

[0009] According to the technical scheme provided in some embodiments of the present application, the upper plate spring and the lower plate spring have the same structure, each including a first flat section, a transition section arranged at both ends of the first flat section, and a second flat section arranged at one end of the transition section away from the first flat section; the two second flat sections of the upper plate spring and the lower plate spring correspondingly abut against each other and jointly form the connecting end.

[0010] According to the technical scheme provided in some embodiments of the present application, the first elastic member is sleeved on the first connecting bolt; the first connecting bolt penetrates the upper plate spring, the lower plate spring and the rocket body in sequence and is screwed with the first connecting nut.

[0011] According to the technical scheme provided in some embodiments of the present application, each group of the second damping mechanism includes at least two damping components distributed along a third direction; the third direction is perpendicular to the first direction and perpendicular to the second direction.

[0012] According to the technical scheme provided in some embodiments of the present application, the damping component includes a connecting part connected with the connecting end; the connecting part is provided with a first mounting groove; an elastic part is arranged in the first mounting groove; the elastic part has a second mounting groove for accommodating an end portion of the mounting part.

[0013] According to the technical scheme provided in some embodiments of the present application, the connecting part includes a sleeve; one end of the sleeve extends outward to form a ring-shaped stopper; the other end of the sleeve is detachably connected with a blocking plate; the blocking plate and the stopper jointly form the first mounting groove in a ring shape; the sleeve is sleeved on a second connecting bolt; the second connecting bolt penetrates the sleeve, the blocking plate, the upper plate spring and the lower plate spring in sequence and is screwed with a second connecting nut.

[0014] According to the technical scheme provided in some embodiments of the present application, the elastic part includes two rubber pads; the rubber pads are sleeved on the outer wall of the sleeve; one end of each of the two rubber pads close to each other is provided with a mounting gap; the two mounting gaps jointly form the second mounting groove.

[0015] According to the technical scheme provided in some embodiments of the present application, one end of each of the two rubber pads close to each other is formed with a expansion joint.

[0016] According to the technical scheme provided in some embodiments of the present application, the mounting part includes a first horizontal section, a first vertical section arranged at an end of the first horizontal section, and a second horizontal section arranged at one end of the first vertical section away from the first horizontal section.

[0017] Compared with the prior art, the beneficial effects of this application are as follows: This application adopts a combination of a first vibration damping mechanism and a second vibration damping mechanism. During installation, the connecting surface of the vibration damping device is fixedly connected to the inner wall of the rocket body to be separated. When the explosive bolt explodes, most of the impact force generated will first act on the rocket body, and then be damped by the double vibration damping mechanism, that is, by the superposition of the first and second vibration damping mechanisms. At this time, the impact force acting on the electrical components is greatly reduced, thus protecting the electrical components from damage under the high impact force generated by the explosive bolt explosion during the separation of the rocket stages. This ensures the stability and reliability of the electrical components, thereby contributing to the successful completion of the rocket launch mission. Attached Figure Description

[0018] Figure 1 An isometric view of a vibration damping device for electrical components near the rocket separation and explosion bolts provided in this application embodiment;

[0019] Figure 2 A front view of a vibration damping device for electrical components near the rocket separation explosion bolts provided in an embodiment of this application;

[0020] Figure 3 for Figure 2 Cross-sectional view of AA in the middle;

[0021] Figure 4 This is a schematic diagram of the structure of the mounting component provided in the embodiments of this application.

[0022] The text labels in the image represent:

[0023] 1. First vibration damping mechanism; 101. Upper leaf spring; 102. Lower leaf spring; 103. First elastic element; 104. First connecting bolt; 105. First connecting nut;

[0024] 2. Second vibration damping mechanism; 201. Vibration damping component; 202. Sleeve; 203. Blocking plate; 204. Second connecting bolt; 205. Second connecting nut; 206. Rubber pad; 207. Second mounting groove; 208. Expansion joint;

[0025] 3. Installation components; 301. First horizontal section; 302. First vertical section; 303. Second horizontal section; 4. Rocket body. Detailed Implementation

[0026] To enable those skilled in the art to better understand the technical solution of this application, the application will be described in detail below with reference to the accompanying drawings. The description in this section is only exemplary and explanatory, and should not be used to limit the scope of protection of this application.

[0027] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0028] Please refer to Figures 1 to 3 This embodiment provides a vibration damping device for electrical components near the rocket separation explosion bolts. The vibration damping device is installed on the inner wall of the rocket body 4 to be separated, and includes:

[0029] A first vibration damping mechanism 1 has a connecting surface for connecting with the rocket body 4; the first vibration damping mechanism 1 also has two connecting ends distributed along a first direction; the first direction is parallel to the connecting surface;

[0030] Two sets of second vibration damping mechanisms 2 are respectively connected to the two connecting ends; the second vibration damping mechanisms 2 extend along the first direction;

[0031] Mounting component 3, which is installed between the two sets of the second vibration damping mechanisms 2, has a mounting surface for mounting electrical components.

[0032] The vibration damping device is small in size, with external dimensions within the range of (100x100x100mm); the bottom surface of the first vibration damping mechanism 1 is a connecting surface for connecting to the rocket body 4, the first direction is horizontal, and the two connecting ends are respectively Figure 2 The first vibration damping mechanism 1 is located at both ends; two sets of second vibration damping mechanisms 2 are respectively connected to the left and right ends of the first vibration damping mechanism 1. The mounting component 3 is connected in the middle of the two sets of second vibration damping mechanisms 2 and is located directly above the first vibration damping mechanism 1. Its top surface is its mounting surface and is used to install electrical components.

[0033] During installation, the connection surface of the vibration damping device is fixedly connected to the inner wall of the rocket body to be separated, and the connection position is located near the explosive bolt. The electrical components to be protected are installed on the mounting surface of the mounting component. When the explosive bolt explodes, most of the impact force will first act on the rocket body, and then be damped by the dual vibration damping mechanism, that is, by the superposition of the first and second vibration damping mechanisms. At this time, the impact force acting on the electrical components is greatly reduced, thus protecting the electrical components from damage under the high impact force generated by the explosive bolt explosion during the separation of the rocket stages. This ensures the stability and reliability of the electrical components, thereby contributing to the successful completion of the rocket launch mission.

[0034] Furthermore, the first damping mechanism 1 includes an upper leaf spring 101 and a lower leaf spring 102 distributed along a second direction; the second direction is perpendicular to the connecting surface; a first mounting space is formed between the upper leaf spring 101 and the lower leaf spring 102; a first elastic member 103 extending along the second direction is provided in the first mounting space.

[0035] Specifically, the second direction is the vertical direction. The upper leaf spring 101 and the lower leaf spring 102 are symmetrically arranged vertically. Both the upper leaf spring 101 and the lower leaf spring 102 are curved structures with one open end. The open end of the upper leaf spring 101 faces downward, and the open end of the lower leaf spring 102 faces upward. The upper leaf spring 101 and the lower leaf spring 102 together enclose a first installation space. A plurality of first elastic elements 103 are provided in the first installation space. In this embodiment, the first elastic element 103 is a spring with a stiffness of 100-1000 N / mm. It is arranged in the vertical direction. In this embodiment, a total of four springs are provided. The four springs are distributed on the four sides of the cuboid structure, which is beneficial to the uniformity of vibration reduction.

[0036] Furthermore, the upper leaf spring 101 and the lower leaf spring 102 have the same structure, each including a first straight section, transition sections disposed at both ends of the first straight section, and a second straight section disposed at the end of the transition section away from the first straight section; the two corresponding second straight sections of the upper leaf spring 101 and the lower leaf spring 102 approach and abut against each other, and together form the connecting end.

[0037] Specifically, the upper leaf spring 101 and the lower leaf spring 102 are both integrally formed components. The first straight section is a rectangular flat plate structure, and the second straight section is also a rectangular flat plate structure. The transition section connects the two rectangular flat plates, and the connection is made with a rounded transition. The two second straight sections on the same side abut against each other in parallel and together form the connection end of the first vibration damping mechanism 1.

[0038] Furthermore, the first elastic element 103 is sleeved on the first connecting bolt 104; the first connecting bolt 104 passes through the upper leaf spring 101, the lower leaf spring 102 and the rocket body 4 in sequence, and is screwed to the first connecting nut 105.

[0039] Specifically, four through holes are provided on the belly of the upper leaf spring 101, i.e., on the first straight section, and four through holes are also provided at corresponding positions on the belly of the lower leaf spring 102, i.e., on the first straight section. Four through holes are also provided at corresponding positions on the rocket body 4. The first connecting bolt 104 passes through three of the corresponding through holes and is threadedly connected to the first connecting nut 105. The above structure facilitates the installation and fixation of the first elastic element 103.

[0040] Furthermore, each group of the second vibration damping mechanism 2 includes at least two vibration damping components 201 distributed along a third direction; the third direction is perpendicular to the first direction and perpendicular to the second direction.

[0041] Specifically, the third direction is parallel to the connecting surface. In this embodiment, each group of the second vibration damping mechanism 2 includes two vibration damping components 201. The two vibration damping components 201 are respectively disposed at the upper ends of the second straight section of the upper leaf spring 101. The four vibration damping components 201 are located on the four sides of the same cuboid structure.

[0042] Furthermore, the vibration damping assembly 201 includes a connecting component connected to the connecting end; the connecting component is provided with a first mounting groove; the first mounting groove is provided with an elastic component; the elastic component has a second mounting groove 207 for accommodating the end of the mounting member 3.

[0043] Specifically, the vibration damping component 201 includes a connecting component and an elastic component. The connecting component is a hollow cylindrical structure, and its side wall is provided with a groove, namely a first mounting groove. The elastic component is installed in the first mounting groove, and a second mounting groove 207 is provided on the side of the elastic component away from the bottom of the first mounting groove. The second mounting groove 207 is used to provide a receiving space for the end of the mounting component 3.

[0044] Furthermore, the connecting component includes a sleeve 202; one end of the sleeve 202 extends outward to form a retaining edge, and the other end is detachably connected to a blocking plate 203; the blocking plate 203 and the retaining edge together form the first mounting groove with an annular structure; the sleeve 202 is sleeved on the second connecting bolt 204; the second connecting bolt 204 passes through the sleeve 202, the blocking plate 203, the upper leaf spring 101 and the lower leaf spring 102 in sequence, and is screwed to the second connecting nut 205.

[0045] Specifically, the sleeve 202 includes a hollow cylindrical sleeve body and an annular retaining edge integrally formed at one end of the top of the sleeve body. A plug plate 203 is detachably connected to the end of the sleeve body away from the retaining edge. A threaded hole is opened in the middle of the plug plate 203. An external thread is provided on the outer wall of the sleeve body at the corresponding position. The plug plate 203 is threadedly connected to the sleeve body, which facilitates the installation of the elastic component. The second connecting bolt 204 passes through the internal cavity of the sleeve body, and then passes through the through holes on the second straight section of the upper leaf spring 101 and the lower leaf spring 102 in sequence, and is threadedly connected to the second connecting nut 205. The above structure facilitates the installation of the vibration damping component 201.

[0046] Both the sleeve 202 and the blocking plate 203 are made of aluminum, which is lightweight and helps to reduce the weight of the entire device.

[0047] Furthermore, the elastic component includes two rubber pads 206; the rubber pads 206 are sleeved on the outer wall of the sleeve 202; the two rubber pads 206 are respectively provided with mounting notches at their close ends; the two mounting notches together form the second mounting groove 207.

[0048] Specifically, the rubber has an elastic modulus of 0.6–5 MPa and a damping ratio of 0.2–0.7. The rubber pad 206 has a T-shaped cross-section, including a hollow sleeve portion and an annular limiting portion integrally formed at one end of the sleeve portion. The sleeve portion is fitted onto the outside of the sleeve body. Two rubber pads 206 are arranged opposite each other, and the sleeve portions of the two rubber pads are connected to each other. The two limiting portions are located at the far ends, and the two limiting portions and the two connected sleeve portions together form the second mounting groove 207. The damping ratio of the rubber material is much greater than that of the metal material, and it has good high-frequency vibration isolation performance, making it more suitable for rocket products.

[0049] Furthermore, an expansion joint 208 is formed at one end of the two rubber pads 206 that are close to each other.

[0050] Specifically, an expansion joint 208 is formed between the near ends of the two sleeve portions, and the height of the expansion joint is less than the end thickness of the mounting member 3. By adopting the above structure, the vibration reduction effect of the second vibration damping mechanism 2 can be further enhanced.

[0051] Further, please refer to Figure 4 The mounting component 3 includes a first horizontal section 301, a first vertical section 302 disposed at the end of the first horizontal section 301, and a second horizontal section 303 disposed at the end of the first vertical section 302 away from the first horizontal section 301.

[0052] Specifically, the mounting component 3 is an integrally formed structure made of ordinary steel. The first horizontal section 301 is a rectangular flat plate structure with through holes at its four corners for mounting electrical components. Two second vertical sections 302 are provided at each end of the first horizontal section 301. The two second vertical sections 302 are respectively located at the two ends of the end of the first horizontal section 301. The second vertical section 302 and the second horizontal section 303 are both rectangular flat plate structures. The end of the second horizontal section 303 away from the second vertical section 302 is provided with an annular sleeve section. The sleeve section is fitted onto the outside of the sleeve 202. The connection between the second vertical section 302 and the first horizontal section 301, and between the second vertical section 302 and the second horizontal section 303, are all rounded. The cross-sectional profile of the mounting component 3 is "U" shaped. By adopting the above structure, the stiffness of the mounting component is reduced, which is more conducive to enhancing the vibration reduction effect.

[0053] Furthermore, arc-shaped notches are provided at both ends of the first horizontal segment 301. By adopting the above structure, the stiffness of the first horizontal segment can be reduced, which is beneficial to enhancing the vibration reduction effect.

[0054] The vibration damping device for electrical components near the rocket separation explosive bolts provided in this application is composed of a combination of rubber damping and spring damping. This combination ensures both the rigidity and efficiency of the damping. The rubber pads surround the mounting plate used to install the electrical components on three sides, isolating it from the metal sleeve and isolating vibrations in the axial, lateral, and rotational directions. This vibration damping device for electrical components near the rocket separation explosive bolts is characterized by its small size and extremely high damping efficiency. This allows it to be installed within the limited operating space of the rocket body while significantly reducing the impact force applied to the electrical components, thereby ensuring the stability and reliability of the electrical components and contributing to the successful completion of the rocket launch mission.

[0055] To verify the vibration reduction efficiency of the vibration reduction device provided in this application, a performance test experiment was designed. A simulation model of the vibration reduction device was established in finite element simulation software. An explosive impact acceleration of 6000g was applied to the side of the rocket body away from the vibration reduction device. The simulated impact acceleration of the installation part away from the rocket body after vibration reduction was 50g, which shows that the vibration reduction device of this application has high vibration reduction efficiency.

[0056] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A vibration damping device for electrical components near rocket separation and explosion bolts, characterized in that, include: A first vibration damping mechanism (1) has a connecting surface for connecting with the rocket body (4); the first vibration damping mechanism (1) also has two connecting ends distributed along a first direction; the first direction is parallel to the connecting surface; Two sets of second vibration damping mechanisms (2) are respectively connected to the two connecting ends; the second vibration damping mechanisms (2) extend along the first direction; Mounting component (3), which is installed between the two sets of the second vibration damping mechanisms (2), has a mounting surface for mounting electrical components; The first damping mechanism (1) includes an upper leaf spring (101) and a lower leaf spring (102) distributed along a second direction; the second direction is perpendicular to the connecting surface; a first mounting space is formed between the upper leaf spring (101) and the lower leaf spring (102); a first elastic member (103) extending along the second direction is provided in the first mounting space. The upper leaf spring (101) and the lower leaf spring (102) have the same structure, each including a first straight section, transition sections at both ends of the first straight section, and a second straight section at the end of the transition section away from the first straight section; the two corresponding second straight sections of the upper leaf spring (101) and the lower leaf spring (102) approach and abut against each other, and together form the connecting end.

2. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 1, characterized in that, The first elastic element (103) is sleeved on the first connecting bolt (104); the first connecting bolt (104) passes through the upper leaf spring (101), the lower leaf spring (102) and the rocket body (4) in sequence, and is screwed to the first connecting nut (105).

3. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 1, characterized in that, Each group of the second damping mechanism (2) includes at least two damping components (201) distributed along a third direction; the third direction is perpendicular to the first direction and perpendicular to the second direction.

4. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 3, characterized in that, The vibration damping assembly (201) includes a connecting component connected to the connecting end; the connecting component is provided with a first mounting groove; the first mounting groove is provided with an elastic component; the elastic component has a second mounting groove (207) for accommodating the end of the mounting member (3).

5. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 4, characterized in that, The connecting component includes a sleeve (202); one end of the sleeve (202) extends outward to form a retaining edge, and the other end is detachably connected to a blocking plate (203); the blocking plate (203) and the retaining edge together form the first mounting groove with an annular structure; the sleeve (202) is sleeved on the second connecting bolt (204); the second connecting bolt (204) passes through the sleeve (202), the blocking plate (203), the upper leaf spring (101) and the lower leaf spring (102) in sequence, and is screwed to the second connecting nut (205).

6. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 5, characterized in that, The elastic component includes two rubber pads (206); the rubber pads (206) are fitted onto the outer wall of the sleeve (202); the two rubber pads (206) are respectively provided with installation notches at their close ends; the two installation notches together form the second installation groove (207).

7. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 6, characterized in that, An expansion joint (208) is formed at one end of the two rubber pads (206) that are close to each other.

8. The vibration damping device for electrical components near the rocket separation explosion bolts according to claim 1, characterized in that, The mounting component (3) includes a first horizontal section (301), a first vertical section (302) disposed at the end of the first horizontal section (301), and a second horizontal section (303) disposed at the end of the first vertical section (302) away from the first horizontal section (301).

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