CN213364180U - Fixture device for missile radar front cabin section vibration experiment - Google Patents
Fixture device for missile radar front cabin section vibration experiment Download PDFInfo
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- CN213364180U CN213364180U CN202022316478.9U CN202022316478U CN213364180U CN 213364180 U CN213364180 U CN 213364180U CN 202022316478 U CN202022316478 U CN 202022316478U CN 213364180 U CN213364180 U CN 213364180U
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- adapter
- vertical wall
- cabin section
- front cabin
- radar front
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Abstract
The utility model discloses a clamp device for missile radar front cabin section vibration experiment, which is characterized by comprising a base vertical wall integrated piece and an adapter, wherein the base vertical wall integrated piece is connected with the adapter, and the adapter is connected with a test product; the base vertical wall integrated piece is of an L-shaped structure formed by a base plane, a vertical wall and wall plates at two ends, the base plane is arranged on the vibration platform, and the vertical wall is arranged on the base plane and connected with the wall plates at two sides; one end of the adapter is a cuboid and is connected with the vertical wall through a bolt, and the other end of the adapter is a cylindrical boss and is connected with a product through a bolt. The utility model has the characteristics of can reliably be connected with shaking table and product, the quality is suitable, both guaranteed that the shaking table can normally work, reduced the influence to the product again.
Description
Technical Field
The utility model relates to a guided missile radar front deck section is anchor clamps device for vibration experiments belongs to mechanical design and anchor clamps technical field.
Background
The aerospace product is inevitably influenced by a vibration environment in the using and transporting processes, in order to check the environmental adaptability of the product, a relevant vibration test needs to be carried out before the product leaves a factory so as to improve the reliability of the product, and the reasonable design of the clamp which accords with the vibration test condition is the key for ensuring the test quality.
The vibration clamp has the advantages that mechanical energy of the vibration table is transmitted to a test piece without distortion, and a set of vibration clamp with reasonable design can ensure convenient and reliable connection between the test piece and the vibration table, has good transmission characteristics and avoids under-test and over-test of the test piece.
Disclosure of Invention
The to-be-solved technical problem of the utility model is: how to provide a guided missile radar front deck section vibration test fixture, make it guarantee convenient and reliable connection, possess better transfer characteristic again.
In order to solve the technical problem, the technical scheme of the utility model is to provide a clamp device for missile radar front cabin section vibration experiment, which is characterized by comprising a base vertical wall integrated piece and an adapter, wherein the base vertical wall integrated piece is connected with the adapter, and the adapter is connected with a test product; the base vertical wall integrated piece is of an L-shaped structure formed by a base plane, a vertical wall and wall plates at two ends, the base plane is arranged on the vibration platform, and the vertical wall is arranged on the base plane and connected with the wall plates at two sides; one end of the adapter is a cuboid and is connected with the vertical wall through a bolt, and the other end of the adapter is a cylindrical boss and is connected with a product through a bolt.
Preferably, the base plane is provided with a plurality of mounting holes, the mounting holes are distributed in a multi-ring shape in the center of the base plane, and the periphery of the center is distributed at equal intervals.
Preferably, both ends of the inner side of the vertical wall are respectively supported by a flush wall plate with a certain thickness to form an L-shaped structure, and a plurality of reinforcing ribs are arranged on the outer side of the vertical wall for supporting.
Preferably, the stand wall inboard be equipped with the adapter be connected a cuboid recess of matching, correspond with the cuboid end of adapter the stand wall on distribute according to the inner circle annular, peripheral equidistant distribution is equipped with the stand wall through-hole.
Preferably, adapter one end be the cuboid, be equipped with the screw hole at its terminal surface, the other end of adapter is the cylinder boss, is equipped with cylinder boss screw hole on the face of cylinder, the angular circle such as screw hole distributes.
Preferably, the natural frequency of the fixture device is 3-5 times of the natural frequency of the product, and the transfer factor of the frequency response function is approximately equal to 1, so that resonance is avoided, and good transfer characteristics are ensured.
The beneficial effects of the utility model reside in that:
1. the tool clamp device can be reliably connected with the vibrating table and a product, has proper quality, not only ensures the normal work of the vibrating table, but also reduces the influence on the product;
2. the tool clamp device can be used for carrying out vibration tool tests on products, when the products are tested for multiple times, the whole tool clamp does not need to be replaced, and only the adapter needs to be replaced, so that the test efficiency and the clamp utilization rate can be improved;
3. the tool clamp device is simple in structure, easy to use, convenient to test and low in cost.
Drawings
FIG. 1 is a schematic view of the structure of the components of the clamping device of the present invention,
fig. 2 is an installation schematic diagram of the fixture device of the present invention.
Detailed Description
In order to make the invention more comprehensible, preferred embodiments are described in detail below with reference to the accompanying drawings.
As shown in fig. 1 and 2, the clamp device for the missile radar front cabin section vibration experiment is characterized by comprising a base vertical wall integrated piece and an adapter 3, wherein the base vertical wall integrated piece is connected with the adapter 3, and the adapter 3 is connected with a test product; the base vertical wall integrated piece is of an L-shaped structure formed by a base plane 1, a vertical wall 2 and wall plates at two ends, the base plane 1 is arranged on the vibration platform, and the vertical wall 2 is arranged on the base plane 1 and connected with the wall plates at two sides; one end of the adapter 3 is a cuboid and is connected with the vertical wall 2 through a bolt, the other end of the adapter is a cylindrical boss and is connected with a product through a bolt, a plurality of mounting holes are arranged on the base plane 1, the mounting holes are distributed in a multi-ring shape in the center of the base plane, and the periphery of the center is distributed at equal intervals; the inboard both ends of founding wall 2 support with the neat high wallboard of certain thickness respectively, constitute L type structure to be equipped with a plurality of strengthening ribs 4 in the outside of founding wall 2 and be used for supporting, found 2 inboards of wall and be equipped with and be connected a cuboid recess that matches with adapter 3, correspond with the cuboid end of body of adapter 3 found wall 2 on distribute according to the inner circle annular, peripheral equidistant distribution is equipped with founds wall through-hole 6, 3 one end of adapter be the cuboid, be equipped with screw hole 8 at its terminal surface, the other end of adapter (3) is the cylinder boss, is equipped with cylinder boss screw hole 7 on the face of cylinder, angular circumference such as screw hole distributes.
Claims (6)
1. The clamp device for the missile radar front cabin section vibration experiment is characterized by comprising a base vertical wall integrated piece and an adapter (3), wherein the base vertical wall integrated piece is connected with the adapter (3), and the adapter (3) is connected with a test product; the base vertical wall integrated piece is of an L-shaped structure formed by a base plane (1), a vertical wall (2) and wall plates at two ends, the base plane (1) is arranged on the vibration platform, and the vertical wall (2) is arranged on the base plane (1) and connected with the wall plates at two sides; one end of the adapter (3) is a cuboid and is connected with the vertical wall (2) through a bolt, and the other end of the adapter is a cylindrical boss and is connected with a product through a bolt.
2. The clamp device for the missile radar front cabin section vibration experiment as recited in claim 1, wherein a plurality of mounting holes are arranged on the base plane (1), the mounting holes are distributed in a multi-ring shape at the center of the base plane, and the periphery of the center is distributed at equal intervals.
3. The missile radar front cabin section vibration experiment fixture device as claimed in claim 1, wherein both ends of the inner side of the vertical wall (2) are respectively supported by a height-aligning wall plate with a certain thickness to form an L-shaped structure, and a plurality of reinforcing ribs (4) are arranged on the outer side of the vertical wall (2) for supporting.
4. The clamp device for the missile radar front cabin section vibration experiment as claimed in claim 1, wherein the inner side of the vertical wall (2) is provided with a cuboid groove which is connected and matched with the adapter (3) and corresponds to the cuboid end of the adapter (3), the vertical wall (2) is annularly distributed according to an inner ring, and vertical wall through holes (6) are distributed on the periphery at equal intervals.
5. The clamp device for the missile radar front cabin section vibration experiment as claimed in claim 1, wherein one end of the adapter (3) is a cuboid, a threaded hole (8) is formed in the end face of the adapter, the other end of the adapter (3) is a cylindrical boss, a cylindrical boss threaded hole (7) is formed in the cylindrical face, and the threaded holes are distributed in an equiangular and circumferential mode.
6. The clamp device for the missile radar front cabin section vibration experiment as claimed in claim 1, wherein the natural frequency of the clamp device is 3-5 times of the product natural frequency, and the transfer factor of the frequency response function is approximately equal to 1, so that resonance is avoided, and good transfer characteristics are ensured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022316478.9U CN213364180U (en) | 2020-10-16 | 2020-10-16 | Fixture device for missile radar front cabin section vibration experiment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022316478.9U CN213364180U (en) | 2020-10-16 | 2020-10-16 | Fixture device for missile radar front cabin section vibration experiment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213364180U true CN213364180U (en) | 2021-06-04 |
Family
ID=76130979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022316478.9U Active CN213364180U (en) | 2020-10-16 | 2020-10-16 | Fixture device for missile radar front cabin section vibration experiment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213364180U (en) |
-
2020
- 2020-10-16 CN CN202022316478.9U patent/CN213364180U/en active Active
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