Miniature missile-borne accelerometer damping device

Abstract

The utility model provides a miniature missile-borne accelerometer damping device, and relates to the technical field of damping. A vibration reduction unit of the device comprises a vibration reduction assembly, a supporting piece and a locking piece. The vibration reduction assemblies are arranged on the two sides of the mounting piece, and the vibration reduction assemblies can generate axial compression deformation with the length direction of the supporting piece as the axis direction; one end of the supporting piece penetrates through the mounting through hole and the damping assembly to be connected with the locking piece; and when the locking piece and the supporting piece are in a connected state, the damping assembly is in an axial compression state. Local vibration reduction can be carried out on the missile-borne accelerometer, the overall vibration reduction effect of the missile-borne accelerometer can be achieved by combining all the vibration reduction units for use, and therefore acceleration measurement errors caused by the external vibration impact effect are avoided. Moreover, the device is simple in structural arrangement, each vibration reduction unit is small in size, and the problems of large occupied space, high manufacturing cost and maintenance cost and acceleration measurement error of a traditional inertial measurement device can be effectively solved.

Description

Technical Field

[0001] This specification relates to the field of vibration reduction technology, and more specifically, to a vibration reduction device for a miniature missile-borne accelerometer. Background Technology

[0002] Inertial measurement products (INS) offer advantages over satellite navigation products, including higher measurement accuracy, better concealment, and less interference from external environmental conditions, leading to their increasingly widespread use in both military and civilian sectors. However, with societal development demands, the operating environments for INS are becoming increasingly harsh, their dimensions smaller, and their measurement accuracy higher. High-precision INS typically use quartz flexible accelerometers to measure linear acceleration. In harsh operating environments, these INS will experience impact and vibration, leading to vibration rectification errors. Currently, there are no mature error compensation algorithms to compensate for these errors, and external vibration and impact conditions may even exceed the accelerometer's tolerance, causing it to fail. To meet societal demands and improve the product's environmental adaptability, vibration reduction measures are necessary for INS.

[0003] Currently, most inertial measurement products adopt external whole-machine vibration reduction measures. The vibration dampers used for whole-machine vibration reduction are large in size, the fixing screws are separate from the vibration damper, and special vibration damper mounting brackets are required. This leads to the current inertial measurement products having disadvantages such as complex vibration reduction design, large space requirements, high cost, and vibration dampers being exposed to the external environment and prone to aging, resulting in short maintenance cycles. At the same time, due to the large size of the vibration damper itself, it will deform when there is external vibration and impact, bringing additional motion to the inertial measurement product, and thus measurement errors due to vibration damper deformation. Utility Model Content

[0004] The purpose of this specification is to provide a vibration reduction device for a miniature missile-borne accelerometer, which can solve the problem of large measurement errors caused by existing whole-machine vibration reduction measures.

[0005] The embodiments described in this specification are implemented as follows:

[0006] A vibration damping device for a miniature missile-borne accelerometer is disclosed. The missile-borne accelerometer is mounted on a mounting frame with multiple mounting components. The vibration damping device includes multiple damping units, each corresponding to a mounting component of the mounting frame. Each damping unit includes a damping component, a support component, and a locking component. Each mounting component has a through-hole with its channel direction aligned with the installation direction of the missile-borne accelerometer. The damping component is located on both sides of the mounting component along the channel direction of the through-hole. One end of the support component passes through the through-hole and connects to the damping component and the locking component. When the locking component and the support component are connected, the damping component is under axial compression with the length direction of the support component as its axis.

[0007] The embodiments described in this specification have at least the following advantages or beneficial effects:

[0008] Compared with existing technologies, this miniature missile-borne accelerometer vibration damping device, through the coordinated action of locking components, damping components, and support components, can locally dampen the missile-borne accelerometer. The combined use of these damping units achieves overall vibration damping of the missile-borne accelerometer, thus avoiding acceleration measurement errors caused by external vibrations and impacts. Furthermore, the device has a simple structure and small damping units, effectively solving the problems of large space occupation, high manufacturing and maintenance costs, and acceleration measurement errors (caused by deformation of traditional dampers under external vibrations and impacts) inherent in traditional inertial measurement devices. Attached Figure Description

[0009] To more clearly illustrate the technical solutions of the embodiments of this specification, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this specification and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0010] Figure 1 This is a structural schematic diagram of the vibration damping device for the miniature missile-borne accelerometer provided in this specification;

[0011] Figure 2 This is a structural schematic diagram of the vibration damping assembly provided in this manual.

[0012] Icons: 1. Support component; 11. First protrusion; 12. Second protrusion; 2. First damping washer; 21. Abutment part; 22. Through part; 23. First mounting hole; 3. Second damping washer; 31. Second mounting hole; 4. Locking component. Detailed Implementation

[0013] To make the objectives, technical solutions, and advantages of the embodiments in this specification clearer, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this specification, and not all embodiments. Generally, the components of the embodiments of this specification described and shown in the accompanying drawings can be arranged and designed in various different configurations.

[0014] Therefore, the following detailed description of the embodiments provided in the accompanying drawings is not intended to limit the scope of the claimed specification, but merely represents selected embodiments of the specification. All other embodiments obtained by those skilled in the art based on the embodiments in this specification without inventive effort are within the scope of protection of this specification.

[0015] 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.

[0016] In the description of the embodiments in this specification, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings, or the orientation or positional relationships commonly used when the product is in use. These are used only for the convenience of describing this specification and for simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this specification. Furthermore, the terms "first," "second," and "third," etc., are used only for distinguishing descriptions and should not be construed as indicating or implying relative importance.

[0017] Furthermore, the use of terms such as "horizontal," "vertical," and "suspended" does not imply that the component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0018] In the description of the embodiments in this specification, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this specification according to the specific circumstances.

[0019] Please refer to Figures 1 to 2 An embodiment of this specification provides a vibration damping device for a miniature missile-borne accelerometer, wherein a mounting frame is provided at the mounting position of the missile-borne accelerometer, the mounting frame is provided with multiple mounting components, and the miniature missile-borne accelerometer vibration damping device includes multiple vibration damping units, each of which is installed correspondingly to each mounting component of the mounting frame.

[0020] The vibration damping unit includes a vibration damping component, a support 1, and a locking component 4;

[0021] The mounting component has a mounting through hole, and the direction of the mounting through hole is consistent with the mounting direction of the missile-borne accelerometer.

[0022] The vibration damping components are disposed on both sides of the mounting member along the direction of the mounting through hole channel;

[0023] One end of the support member 1 passes through the mounting hole and the vibration damping component is connected to the locking member 4;

[0024] When the locking member 4 and the support member 1 are connected, the vibration damping assembly is in an axial compression state with the length direction of the support member 1 as the axis.

[0025] In this embodiment, a mounting bracket is provided on the mounting side of the aforementioned missile-borne accelerometer, or a mounting bracket is provided on the outer side of the aforementioned missile-borne accelerometer, with the mounting bracket positioned below (with "below" as the mounting location). Figure 1 The upper and lower directions shown are the upper and lower directions proposed in this embodiment. At least four mounting members are provided. The plane where the lower side wall of the mounting member is located is on the same plane as the plane where the lower side wall of the mounting frame is located. All four mounting members are provided with mounting through holes. The hole channel direction of the mounting through holes is the upper and lower direction, so that the end of the support member 1 away from the mounting member can be supported on the mounting surface.

[0026] In this embodiment, each mounting component has a vibration damping unit installed in its mounting hole, and the four vibration damping units are installed at the same height.

[0027] In this embodiment, the support member 1 is in the shape of a shaft.

[0028] In this embodiment, the locking member 4 presses the vibration damping component downward toward the support member 1 according to the preset vibration damping requirements, and the vibration damping component is in an axial compression state at this time.

[0029] As can be seen, the above-mentioned device, through the coordinated action of locking component 4, vibration damping assembly, and support component 1, can locally dampen the missile-borne accelerometer. The combined use of each damping unit achieves overall vibration damping of the missile-borne accelerometer, thereby avoiding acceleration measurement errors caused by external vibration and impact. Furthermore, the device has a simple structure and each damping unit is small in size, effectively solving the problems of large space occupation, high manufacturing and maintenance costs, and acceleration measurement errors (caused by deformation of the traditional damper under external vibration and impact) inherent in traditional inertial measurement devices.

[0030] In this embodiment, the vibration damping component includes a first damping washer 2 and a second damping washer 3;

[0031] The first damping washer 2 has a first mounting hole 23, and the second damping washer 3 has a second mounting hole 31. One end of the support member 1 passes through the first mounting hole 23, the mounting through hole and the second mounting hole 31 in sequence and is connected to the locking member 4.

[0032] In this embodiment, the first damping washer 2 and the second damping washer 3 are capable of elastic compression deformation in the axial direction to achieve the expected vibration reduction effect.

[0033] In detail, the dimensions of the first mounting hole 23 and the second mounting hole 31 are adapted to the outer diameter of the support member 1, that is, the hole wall of the first mounting hole 23 abuts against the outer wall of the support member 1, and the hole wall of the second mounting hole 31 abuts against the outer wall of the support member 1. Through the above arrangement, the vibration reduction effect of the vibration reduction unit can be further improved, and the situation of unstable installation of the support member 1 in the first mounting hole 23 and the second mounting hole 31 can be avoided.

[0034] In addition, in this embodiment, the first damping washer 2 and the second damping washer 3 are independently provided and are respectively provided on both sides of the mounting component, which facilitates the assembly of the vibration damping unit and makes it more convenient.

[0035] In this embodiment, the first damping washer 2 has a through portion 22 and an abutment portion 21 connected to each other. The through portion 22 is fitted into the mounting through hole, and the abutment portion 21 is located on the side of the mounting member away from the locking member 4. Specifically, the through portion 22 can be disposed in the mounting through hole, which can effectively enhance the installation stability of the first damping washer 2 and the mounting member, and the positioning accuracy is higher.

[0036] In this embodiment, one end of the first mounting hole 23 is opened on the side of the abutment portion 21 away from the mounting member, and the other end of the first mounting hole 23 is opened on the side of the through portion 22 close to the mounting member.

[0037] In this embodiment, when installed in the mounting through hole, the plane of the side wall of the through portion 22 near the second damping washer 3 is on the same plane as the plane of the side wall of the mounting member near the second damping washer 3, and the outer side wall of the through portion 22 abuts against the inner side wall of the mounting through hole, which can prevent the first damping washer 2 from tearing during the assembly process.

[0038] In this embodiment, the support member 1 is provided with a first protrusion 11 and a second protrusion 12. The first protrusion 11 can abut against the side of the first damping washer 2 away from the mounting member. The second protrusion 12 can pass through the first mounting hole 23 and be disposed in the second mounting hole 31. The axial height of the second protrusion 12 is less than the axial height of the second damping washer 3.

[0039] In this embodiment, the first protrusion 11 is cylindrical, and its outer diameter is the same as that of the first damping washer 2. The first protrusion 11 can prevent the first damping washer 2 from sliding down toward the support member 1, so as to improve the vibration reduction effect of the first damping washer 2 and the second damping washer 3.

[0040] In this embodiment, the second protrusion 12 can be disposed in the second mounting hole 31 through the first mounting hole 23, and the opening height of the second mounting hole 31 on the side of the second damping washer 3 near the locking member 4 is higher than the setting height of the second protrusion 12 on the side of the locking member 4.

[0041] When the locking member 4 is tightened to compress the first damping washer 2 and the second damping washer 3, the second protrusion 12 can limit the tightening position of the locking member 4, so as to prevent the locking member 4 from being over-tightened and damaging the first damping washer 2 and the second damping washer 3.

[0042] In this embodiment, one end of the support member 1 is connected to the locking member 4 by a thread, and the position of the locking member 4 on the support member 1 can be restricted by the setting position of the second protrusion 12.

[0043] In this embodiment, the locking member 4 is connected to the upper end of the support member 1 by a thread. The number of tightening turns can be determined according to the elastic compression deformation of the first damping washer 2 and the second damping washer 3, so that the installer can adjust the pressure of the locking member 4 on the first damping washer 2 and the second damping washer 3 according to the actual vibration reduction requirements, so as to control the vibration reduction effect.

[0044] In this embodiment, the locking member 4 is a milled flat nut. The side wall of the locking member 4 near the second damping washer 3 is flat, and the side wall of the locking member 4 away from the second damping washer 3 has a milled groove. Specifically, this arrangement facilitates the disassembly and assembly of the vibration damping unit; that is, the first damping washer 2, the second damping washer 3, and the support member 1 can be disassembled simply by loosening the locking member 4 through the milled groove.

[0045] In this embodiment, the end of the support member 1 away from the locking member 4 is provided with a thread to facilitate the connection between the mounting bracket and the mounting position.

[0046] In this embodiment, the locking member 4 and the support member 1 are made of stainless steel, and the first damping washer 2 and the second damping washer 3 are made of nitrile rubber. This configuration allows for better vibration damping effect of the vibration damping unit while also reducing its weight.

[0047] In this embodiment, the working temperature of the above-mentioned nitrile rubber in petroleum-based oil is -50℃ to +100℃.

[0048] In this embodiment, the first damping washer 2 has its axial direction along the hole channel direction of the first mounting hole 23, the axial thickness of the first damping washer 2 is 2.0mm-3.0mm, and the axial compression of the first damping washer 2 is 0.3mm-0.5mm.

[0049] In this embodiment, the second damping washer 3 has its axial direction along the hole channel direction of the second mounting hole 31, the axial thickness of the abutment portion 21 is 2.0mm-3.0mm, and the axial compression of the abutment portion 21 is 0.3mm-0.5mm.

[0050] In this embodiment, the radial compression of the first damping washer 2 and the abutment portion 21 is 0.1 mm.

[0051] In this embodiment, a missile-borne accelerometer with a frequency of 150Hz-1000Hz is used.

[0052] The above are merely preferred embodiments of this specification and are not intended to limit this specification. Various modifications and variations can be made to this specification by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this specification should be included within the scope of protection of this specification.

Claims

1. A vibration damping device for a miniature missile-borne accelerometer, used for a missile-borne accelerometer, wherein a mounting bracket is provided at the mounting position of the missile-borne accelerometer, characterized in that, The mounting frame is provided with multiple mounting components, and the micro missile-borne accelerometer vibration damping device includes multiple vibration damping units, each of which is installed corresponding to a mounting component of the mounting frame. The vibration damping unit includes vibration damping components, support components, and locking components; The mounting component has a mounting through hole, and the direction of the mounting through hole is consistent with the mounting direction of the missile-borne accelerometer. The vibration damping components are disposed on both sides of the mounting member along the hole channel direction of the mounting through hole, and the vibration damping components can undergo axial compression deformation with the length direction of the support member as the axis. One end of the support member passes through the mounting hole and is connected to the vibration damping component and the locking member; When the locking member and the support member are connected, the vibration damping assembly is under axial compression with the length direction of the support member as the axis.

2. The vibration damping device for the miniature missile-borne accelerometer according to claim 1, characterized in that, The vibration damping assembly includes a first damping washer and a second damping washer; The first damping washer has a first mounting hole, the second damping washer has a second mounting hole, and one end of the support member passes through the first mounting hole, the mounting through hole and the second mounting hole in sequence to connect with the locking member.

3. The vibration damping device for the miniature missile-borne accelerometer according to claim 2, characterized in that, The first damping washer has a through portion and an abutment portion that are connected to each other. The through portion is fitted into the mounting through hole, and the abutment portion is located on the side of the mounting member away from the locking member.

4. The vibration damping device for a miniature missile-borne accelerometer according to claim 2 or 3, characterized in that, The support member is provided with a first protrusion and a second protrusion. The first protrusion can abut against the side of the first damping washer away from the mounting member. The second protrusion can pass through the first mounting hole and be disposed in the second mounting hole. The axial height of the second protrusion is less than the axial height of the second damping washer.

5. The vibration damping device for the miniature missile-borne accelerometer according to claim 4, characterized in that, One end of the support member is connected to the locking member by a thread.

6. The vibration damping device for the miniature missile-borne accelerometer according to claim 5, characterized in that, The locking component is a milled flat nut. The side wall of the locking component near the second damping washer is a plane, and the side wall of the locking component away from the second damping washer has a milled groove.

7. The vibration damping device for the miniature missile-borne accelerometer according to claim 2, characterized in that, The locking member and the supporting member are made of stainless steel, and the first damping washer and the second damping washer are made of nitrile rubber.

8. The vibration damping device for the miniature missile-borne accelerometer according to claim 4, characterized in that, The first damping washer has its axial direction along the hole channel direction of the first mounting hole, and its axial thickness is 2.0mm-3.0mm, and its axial compression is 0.3mm-0.5mm.

9. The vibration damping device for the miniature missile-borne accelerometer according to claim 3, characterized in that, The second damping washer has its axial direction along the hole channel direction of the second mounting hole, the axial thickness of the abutment part is 2.0mm-3.0mm, and the axial compression of the abutment part is 0.3mm-0.5mm.

10. The vibration damping device for the miniature missile-borne accelerometer according to claim 1, characterized in that, For use in missile-borne accelerometers with frequencies of 150Hz-1000Hz.

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