CN109489925A - A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test - Google Patents
A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test Download PDFInfo
- Publication number
- CN109489925A CN109489925A CN201710817557.8A CN201710817557A CN109489925A CN 109489925 A CN109489925 A CN 109489925A CN 201710817557 A CN201710817557 A CN 201710817557A CN 109489925 A CN109489925 A CN 109489925A
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- China
- Prior art keywords
- vibration test
- overhang
- ball screw
- guided missile
- transverse acceleration
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention relates to a kind of devices of guided missile transverse acceleration in reduction firing mount combination vibration test, including erecting by overhang (1), outer adjutage (2) and locking device (3), two erectings by overhang (1) are T-shaped structure, outer adjutage (2) is L-shaped structure, fixes a locking device (3) on the outer extended segment of each outer adjutage (2).The device of the invention can be installed in conjunction with the valve distance of different erecting by overhang flexible choice different locations and the spiro rod length of different length, can satisfy the firing mount combination vibration test of different erectings by overhang, save the experimentation cost of vibration test.
Description
Technical field
The invention belongs to vibration test fields, and in particular to guided missile laterally accelerates in a kind of reduction firing mount combination vibration test
The device of degree.
Background technique
Vibration test is a big event in environmental test, can be used to find in product design and production process
Defect improves the purpose of the vibration resistance environment capacity of product to reach improvement product design.
Test indoor simulation guided missile passes through the vibration test for leading the guided missile for the truth that hair frame is suspended on aircraft at present, is
It effectively examines guided missile and leads the most effective mode of hair frame vibration resistance ability.The mode of vibration due to only fix 2 sling points of guided missile,
It carries out that biggish transverse acceleration can be generated when vibration test.And existing missile vibration test requirements document, it is horizontal in any frequency
It should be no more than 0.45 times (or 0.2 times of acceleration spectral density) for testing axial upper acceleration to the acceleration of vibration.
Summary of the invention
The purpose of the present invention is: inventing this vibration test grip device is in order in progress guided missile firing mount combination vibration test
When, reduce influence of the transverse acceleration of guided missile test part to test, improves the validity of test driving axial vibration.
In view of the above problem of the prior art, according to one aspect of the present disclosure, the present invention uses following technology
Scheme:
A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test, including erecting by overhang (1), outer extension
Arm (2) and locking device (3)；
Wherein, two erectings by overhang (1) are T-shaped structure, and top is connect by fixing bolt with vibration test fixture, two
The top both ends of testpieces are axially hung by erecting by overhang respectively in erecting by overhang (1) bottom；
Outer adjutage (2) is L-shaped structure, and the lower part two sides of each erecting by overhang (1), which are bolted outside two, to be extended
Arm (2)；
A locking device (3) is fixed on the outer extended segment of each outer adjutage (2), locking device (3) includes bulb spiral shell
Bar (4), valve (5) and stop bit nut (6), ball screw (4) periphery have screw thread, and ball screw (4) is screwed into each outer extension
Threaded hole on the outer extended segment of arm (2), ball screw (4) bottom connect valve (5), are bonded at the top of valve (5) and testpieces,
Realize that the cross spacing of testpieces, stop bit nut (6) realize the stop bit of ball screw (4), prevent ball screw in vibration test
(4) it loosens.
It is characterized in that, the device is made of 30CrMnSiA material.
It is characterized in that, outer adjutage (2) the upper screwed hole position of adjustment, to adjust the position of valve (5), and passes through adjusting
The angle of valve (5), guarantee are contacted with various sizes of testpieces surface.
The utility model has the advantages that
The device of the invention, in conjunction with the valve distance and different length of different erecting by overhang flexible choice different locations
Spiro rod length installed, can satisfy different erectings by overhang firing mount combination vibration test, saved the examination of vibration test
Test cost.
Detailed description of the invention
The part combination part front view of the fixed lifting lug of Fig. 1.
Fig. 2 locking device schematic diagram.
Specific embodiment
The present invention is described in further detail below with reference to embodiment, embodiments of the present invention are not limited thereto.
The device of guided missile transverse acceleration in a kind of reduction firing mount combination vibration test of the invention, including erecting by overhang
(1), outer adjutage (2) and locking device (3), as shown in Figure 1.
Two erectings by overhang (1) are T-shaped structure, and top is connect by fixing bolt with vibration test fixture, two hangings
The top both ends of testpieces are axially hung by erecting by overhang respectively in device (1) bottom.
Outer adjutage (2) is L-shaped structure, and the lower part two sides of each erecting by overhang (1), which are bolted outside two, to be extended
Arm (2).
As shown in Fig. 2, fixing a locking device (3), locking device (3) on the outer extended segment of each outer adjutage (2)
Including ball screw (4), valve (5) and stop bit nut (6), ball screw (4) periphery has screw thread, and ball screw (4) is screwed into
Threaded hole on the outer extended segment of each outer adjutage (2), ball screw (4) bottom connect valve (5), valve (5) and test
Fitting at the top of part realizes that the cross spacing of testpieces, stop bit nut (6) realize the stop bit of ball screw (4), prevent vibration test
Middle ball screw (4) loosens.
The assembling process of described device are as follows:
Erecting by overhang (1) is fixed by bolts on vibration test fixture；
Testpieces is fixed on erecting by overhang (1) according to the position of lifting lug；
Select suitable position that outer adjutage (2) is fixed by bolts on erecting by overhang (1)；
Locking device (3) is mounted on outer adjutage (2), the position of valve (5) is adjusted, pastes it with testpieces surface
It closes, tightens ball screw.
Stop bit nut (6) are tightened, testpieces is fixed, transverse acceleration when reducing its normal vibration.
Claims (4)
1. a kind of device for reducing guided missile transverse acceleration in firing mount combination vibration test, including erecting by overhang (1), outer adjutage
(2) and locking device (3)；
Wherein, two erectings by overhang (1) are T-shaped structure, and top is connect by fixing bolt with vibration test fixture, two hangings
The top both ends of testpieces are axially hung by erecting by overhang respectively in device (1) bottom；
Outer adjutage (2) is L-shaped structure, and the lower part two sides of each erecting by overhang (1) are bolted two outer adjutages
(2)；
A locking device (3) is fixed on the outer extended segment of each outer adjutage (2).
2. a kind of device for reducing guided missile transverse acceleration in firing mount combination vibration test as described in claim 1, feature
It is, the locking device (3) includes ball screw (4), valve (5) and stop bit nut (6), and ball screw (4) periphery has
Screw thread, ball screw (4) are screwed into the threaded hole on the outer extended segment of each outer adjutage (2), and the connection of ball screw (4) bottom is lived
It is bonded at the top of door (5), valve (5) and testpieces, realizes that the cross spacing of testpieces, stop bit nut (6) realize ball screw (4)
Stop bit, prevent ball screw in vibration test (4) loosen.
3. a kind of device for reducing guided missile transverse acceleration in firing mount combination vibration test as described in claim 1, feature
It is, which is made of 30CrMnSiA material.
4. a kind of device for reducing guided missile transverse acceleration in firing mount combination vibration test as described in claim 1, feature
It is, adjusts outer adjutage (2) upper screwed hole position, to adjust the position of valve (5), and passes through the angle of governor valve (5),
Guarantee is contacted with various sizes of testpieces surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817557.8A CN109489925A (en) | 2017-09-12 | 2017-09-12 | A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817557.8A CN109489925A (en) | 2017-09-12 | 2017-09-12 | A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109489925A true CN109489925A (en) | 2019-03-19 |
Family
ID=65687751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710817557.8A Pending CN109489925A (en) | 2017-09-12 | 2017-09-12 | A kind of device reducing guided missile transverse acceleration in firing mount combination vibration test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109489925A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112229611A (en) * | 2020-08-27 | 2021-01-15 | 芜湖航翼集成设备有限公司 | Aircraft guide rail emitter testing arrangement |
| CN114414250A (en) * | 2021-12-14 | 2022-04-29 | 北京动力机械研究所 | Acceleration test simulation method of lifting lug type mounting structure |
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| JP2004251118A (en) * | 2002-10-31 | 2004-09-09 | Snecma Moteurs | Suspension device for jet engine |
| CN203275054U (en) * | 2013-04-16 | 2013-11-06 | 沈阳兴华航空电器有限责任公司 | General adjustable vibration test installation platform |
| CN106289690A (en) * | 2016-07-29 | 2017-01-04 | 江西洪都航空工业集团有限责任公司 | A kind of vibration test fixture |
| CN106596012A (en) * | 2016-11-25 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Gun carrier combination vibration test fixture |
| CN106768753A (en) * | 2016-11-25 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of circular ring type vibration test fixture |
-
2017
- 2017-09-12 CN CN201710817557.8A patent/CN109489925A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004251118A (en) * | 2002-10-31 | 2004-09-09 | Snecma Moteurs | Suspension device for jet engine |
| CN203275054U (en) * | 2013-04-16 | 2013-11-06 | 沈阳兴华航空电器有限责任公司 | General adjustable vibration test installation platform |
| CN106289690A (en) * | 2016-07-29 | 2017-01-04 | 江西洪都航空工业集团有限责任公司 | A kind of vibration test fixture |
| CN106596012A (en) * | 2016-11-25 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Gun carrier combination vibration test fixture |
| CN106768753A (en) * | 2016-11-25 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of circular ring type vibration test fixture |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112229611A (en) * | 2020-08-27 | 2021-01-15 | 芜湖航翼集成设备有限公司 | Aircraft guide rail emitter testing arrangement |
| CN114414250A (en) * | 2021-12-14 | 2022-04-29 | 北京动力机械研究所 | Acceleration test simulation method of lifting lug type mounting structure |
| CN114414250B (en) * | 2021-12-14 | 2024-04-09 | 北京动力机械研究所 | Acceleration test simulation method for lifting lug type mounting structure |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190319 |
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| RJ01 | Rejection of invention patent application after publication |