CN220960633U - Stability verification test device for transmitting platform - Google Patents
Stability verification test device for transmitting platform Download PDFInfo
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- CN220960633U CN220960633U CN202322627227.6U CN202322627227U CN220960633U CN 220960633 U CN220960633 U CN 220960633U CN 202322627227 U CN202322627227 U CN 202322627227U CN 220960633 U CN220960633 U CN 220960633U
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- pulley
- wire rope
- seat
- fixed
- verification test
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- 238000012360 testing method Methods 0.000 title claims abstract description 20
- 238000012795 verification Methods 0.000 title claims abstract description 15
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 17
- 239000010959 steel Substances 0.000 claims abstract description 17
- 239000004568 cement Substances 0.000 claims abstract description 6
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000011161 development Methods 0.000 abstract description 5
- 238000004088 simulation Methods 0.000 abstract description 2
- 125000003003 spiro group Chemical group 0.000 abstract description 2
- 238000013112 stability test Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model provides a launch platform stability verification test device, sets up in the positive side of ground launching frame, including connecting seat, be used for spiro union simulation missile product rings screw, stand, crossbeam, pulley seat, pulley, wire rope and weight, wherein, the stand is fixed on cement ground, and the crossbeam is fixed on the stand, and the pulley seat is fixed on the crossbeam, and the pulley is connected with the pulley seat, and the pulley can smoothly rotate in the pulley seat; one end of the steel wire rope is connected with a lifting ring screw, the lifting ring screw is connected with a connecting seat in a threaded manner, the connecting seat is fixedly connected with a ground launching frame, the other end of the steel wire rope penetrates through a pulley to be connected with weights with different weight levels, and different weights are changed to obtain different weights so as to simulate pulling forces under different limit working conditions and verify the stability of a launching platform; has the advantages of short development period and low development cost.
Description
Technical Field
The utility model relates to the technical field of stability verification test devices, in particular to a stability verification test device for a transmitting platform.
Background
In the development process of the missile ground launching platform, whether the launching platform is tilted or not needs to be verified under the working condition of limiting tension, and whether a launching frame can fix a test item of a locking product or not under the impact of secondary locking force of a launching device, so that the launching platform is stable and reliable in the missile launching process and does not tilt, and the rigidity and the strength of a launching frame locking mechanism meet the requirements. In the past, the test is carried out in a hydraulic laboratory, a special fixture clamp is required to be designed, and when the test is carried out, the required tensile force is given on a hydraulic table, and the tensile force is acted on a transmitting platform through a fixture to complete the stability verification test; the test coordination period is long, the tooling design time is long, and the cost is high.
Disclosure of utility model
The technical problem solved by the utility model is to provide a stability verification test device for a transmitting platform, so as to solve the problems in the background technology.
The technical problems solved by the utility model are realized by adopting the following technical scheme:
The utility model provides a launch platform stability verification test device, sets up in the positive side of ground launching frame, including connecting seat, be used for spiro union simulation missile product rings screw, stand, crossbeam, pulley seat, pulley, wire rope and weight, wherein, the stand is fixed on cement ground, and the crossbeam is fixed on the stand, and the pulley seat is fixed on the crossbeam, and the pulley is connected with the pulley seat, and the pulley can smoothly rotate in the pulley seat; one end of the steel wire rope is connected with the lifting ring screw, the lifting ring screw is connected with the connecting seat in a threaded manner, the connecting seat is fixedly connected with the ground launching frame, the other end of the steel wire rope penetrates through the pulley to be connected with weights with different weight levels, and different weights are changed to obtain different weights so as to simulate pulling forces under different limit working conditions and verify the stability of the launching platform.
According to the utility model, when verifying whether the launching frame can fix and lock the missile product under the impact of the secondary locking force of the launching device, the simulated missile product is hung on the launching device, then the simulated missile product and the simulated missile product are hung on the ground launching frame together, the flying ring screw is screwed on the simulated missile product, different weights are changed to obtain different weights, so that the pulling force under the impact of the secondary locking force of different launching devices is simulated, and the reliability of the ground launching frame to fix and lock the product is verified.
In the utility model, the stand column is provided with the support, and the cross beam is fixedly connected with the support through the bolt.
In the utility model, the bottom of the upright post is provided with a reinforcing plate for supporting the upright post.
In the utility model, the beam is provided with a bolt hole for installing the pulley seat.
In the utility model, a hook for hanging weights is arranged on the steel wire rope.
In the present utility model, the pulley is a fixed pulley.
Advantageous effects
1) The utility model can convert the horizontal pulling force under the required limit working condition into gravity, and realizes the direction conversion through the fixed pulley on the stability test device, and has simple implementation and convenient operation;
2) The test site is small in limit, and only anchor bolts are needed to be drilled on a proper cement site and used for fixing the stability test device beside the emission platform;
3) According to the utility model, by replacing weights with different weight levels, the tension under different working conditions can be obtained, so that the stability of the launching platform required by different working conditions is verified, and the reliability of a locking product is fixed by the launching frame under the impact of secondary locking forces of different launching devices;
4) The utility model has the advantages of short development period and low development cost.
Drawings
FIG. 1 is a schematic view of an installation of a preferred embodiment of the present utility model.
FIG. 2 is a cross-sectional view taken at A-A in FIG. 1.
FIG. 3 is a schematic illustration of a connection of a fixed lock simulated missile product in accordance with the preferred embodiment of the present utility model.
Description of the embodiments
The utility model is further described with reference to the following detailed drawings in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the implementation of the utility model easy to understand.
Referring to a stability verification test device of a transmitting platform in fig. 1-3, a ground transmitting frame 2 is installed on a transmitting platform 1, and a stability test device 3 is arranged on the right side of the ground transmitting frame 2; verifying whether the launching platform 1 is overturned or not through the stability test device 3, and whether the launching frame can fix a locking product or not under the impact of the secondary locking force of the launching device; the stability test device 3 comprises a connecting seat 4, a lifting screw 5, a stand column 6, a support 7, a beam 8, a pulley seat 9, a pulley 10, a steel wire rope 11, weights 12 and anchor bolts 13, wherein the stand column 6 is fixedly connected to the cement floor through the anchor bolts 13, the beam 8 is fixedly connected with the stand column 6 through bolts, the pulley seat 9 is fixedly connected with the beam 8 through bolts, the pulley 10 is connected with the pulley seat 9 through bolts, and the pulley 10 can smoothly rotate in the pulley seat 9; one end of a steel wire rope 11 is connected with a lifting screw 5, the lifting screw 5 is in threaded connection with a connecting seat 4, the connecting seat 4 is fixedly connected with a ground launching frame 2 through screws, the other end of the steel wire rope 11 penetrates through a pulley 10 to be connected with weights 12 with different weight levels, and different weights are replaced to obtain different weights so as to simulate tensile forces under different limit working conditions and verify the stability of the launching platform 1.
In this embodiment, when verifying that the launching frame can fix and lock the missile product under the impact of the secondary locking force of the launching device, the simulated missile product 14 is hung on the launching device 15, then the simulated missile product 14 and the simulated missile product are hung on the ground launching frame 2 together, the flying ring screw 5 is screwed on the simulated missile product 14, and different weights are replaced to obtain different weights so as to simulate the pulling force under the impact of the secondary locking force of different launching devices, so that the reliability of fixing and locking the product by the ground launching frame 2 is verified.
In this embodiment, the stand 6 is provided with a support 7, and the cross beam 8 is fixedly connected with the support 7 by bolts.
In this embodiment, the bottom of the upright 6 is provided with a reinforcing plate for supporting the upright 6.
In the present embodiment, bolt holes for mounting the pulley holders 9 are provided on the cross beam 8.
In this embodiment, a hook is provided on the wire rope 11 for hanging the weight 12.
In this embodiment, the following is specifically implemented:
1) Selecting a proper cement field, and drilling four anchor bolts 13 on the ground, wherein the depth is not less than 120mm;
2) Hoisting the stability test device 3 to the foundation bolts 13, and connecting and fastening;
3) Weights with different weights (1 ton, 1.25 ton and 1.5 ton) are sequentially added at the grounding end of the steel wire rope 11, and the steel wire rope 11 passes through the pulley 10;
4) The launching platform 1 is opened to a proper position beside the stability test device 3, and the launching platform 1 is at least 4 meters away from the stability test device 3;
5) Landing legs of the launching platform 1 are dropped to level;
6) The weight is lifted by a forklift, and the other end of the steel wire rope 11 is fixed on a lifting screw 5 on the ground launching frame 2;
7) Slowly descending the forklift, stopping descending after the weight is suspended in the air, suspending the weight for a certain time, and observing whether the supporting legs of the launching platform 1 are suspended or not so as to verify whether the launching platform 1 is tilted or not;
8) Hanging a simulated missile product 14;
9) Weights with different weights (0.25 ton and 0.5 ton) are sequentially added at the grounding end of the steel wire rope 11, and the steel wire rope 11 passes through the pulley 10;
10 A forklift or a hydraulic trailer is used for supporting the weight; the other end of the steel wire rope 11 is fixed on the simulated missile product 14;
11 Slowly lowering the forklift or the hydraulic trailer, stopping lowering after the weight is suspended in the air, suspending the weight for a certain time, and observing whether the ground launching frame 2 can fix and lock the simulated missile product 14.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made without departing from the spirit and scope of the utility model, which is defined in the appended claims. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (6)
1. The launching platform stability verification test device is arranged on the positive side of a ground launching frame and comprises a connecting seat, a lifting screw for being in threaded connection with a simulated missile product, a stand column, a beam, a pulley seat, a pulley, a steel wire rope and weights, and is characterized in that the stand column is fixed on a cement ground, the beam is fixed on the stand column, the pulley seat is fixed on the beam, and the pulley is connected with the pulley seat; one end of the steel wire rope is connected with the lifting ring screw, the lifting ring screw is connected with the connecting seat in a threaded manner, the connecting seat is fixed on the ground launching frame, and the other end of the steel wire rope penetrates through the pulley and is connected with weights with different weight levels.
2. The launch platform stability verification test apparatus of claim 1, wherein the stand is provided with a support, and the cross beam is fixedly connected to the support by bolts.
3. The launch platform stability verification test apparatus of claim 1, wherein the column bottom is provided with a reinforcing plate for supporting the column.
4. The launch pad stability verification test apparatus of claim 1, wherein the cross beam is provided with bolt holes for mounting the pulley mount.
5. The launch pad stability verification test apparatus of claim 1, wherein a hanger for hanging weights is provided on the wire rope.
6. The launch pad stability verification test apparatus of claim 1, wherein the pulley is a fixed pulley.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322627227.6U CN220960633U (en) | 2023-09-27 | 2023-09-27 | Stability verification test device for transmitting platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322627227.6U CN220960633U (en) | 2023-09-27 | 2023-09-27 | Stability verification test device for transmitting platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220960633U true CN220960633U (en) | 2024-05-14 |
Family
ID=91011077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322627227.6U Active CN220960633U (en) | 2023-09-27 | 2023-09-27 | Stability verification test device for transmitting platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220960633U (en) |
-
2023
- 2023-09-27 CN CN202322627227.6U patent/CN220960633U/en active Active
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