CN202947849U - Vibration testing clamp of instrument cabin of lunch vehicle - Google Patents
Vibration testing clamp of instrument cabin of lunch vehicle Download PDFInfo
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- CN202947849U CN202947849U CN 201220546208 CN201220546208U CN202947849U CN 202947849 U CN202947849 U CN 202947849U CN 201220546208 CN201220546208 CN 201220546208 CN 201220546208 U CN201220546208 U CN 201220546208U CN 202947849 U CN202947849 U CN 202947849U
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Abstract
The utility model relates to a vibration testing clamp of an instrument cabin of a lunch vehicle. The vibration testing clamp comprises an annular upper end face, a square lower end face and a lateral wall for connecting the upper end face and the lower end face; wherein the a round is formed on the lower end face of the lateral wall; a plurality of bolt holes are arranged on the upper end face and the lower end face; a plurality of reinforcing ribs for connecting the upper end face and the lower end face are evenly arranged on the lateral wall along the circumferential direction; the outer diameter of the upper end face is 2.5m to 3.5m; the thickness of the lateral wall is 20mm; the proportional relation of the thickness of the lateral wall, the thickness of the upper end face and the lower end face and the thickness of the reinforcing ribs is 1:2:2; the proportion of the height of the testing clamp to the outer diameter of the upper end face is smaller than or equal to 1:5, and the proportion of the height of the testing clamp to the diameter of the round formed on the lower end face of the lateral wall is smaller than 1:3. The first-order inherent frequency of the clamp is improved to higher than 100Hz, so that testing requirements can be met. The vibration testing clamp can bear CZ-series large vibration tests and has certain generality.
Description
Technical field
The utility model relates to a kind of carrier rocket instrument room vibration test fixture, particularly relates to more than a kind of natural frequency brings up to 100Hz, satisfies the carrier rocket instrument room vibration test fixture of testing requirements.
Background technology
Test fixture is a ring important in vibration test, and its design, manufacturing, installation are related to the quality of test.
The motion parts of shaking table comprises moving-coil and table top, uniform many threaded holes on table top, by screw, vibration tong is fixed on table top, test specimen is connected on fixture, so the major function of fixture is: connect or fixedly the vibration parameters such as test specimen, transmission power or acceleration, keep the test specimen direction of vibration.
Because it is the transition piece of a connection, be again a force transferring part, the quality of jig Design directly affects test effect.Must understand as the connecting device jig Design
1, the position, hole on product, vibration table and the size of bolt hole;
2, the general assembly (TW) that can bear of vibration table surface maximum;
3, the normal thrust of shaking table;
4, the pretightning force of product, vibration table and fixture attachment screw.
As force transferring part also should satisfy lightweight, rigidity is large, the high requirement of frequency, also requires its single order response frequency higher than the single order response frequency of large-scale experiment spare more than three times for large-scale jig.
Testpieces is the carrier rocket instrument room, and its diameter is very large, is about 3.1 meters left and right.The instrument bulkhead is columnar structured, in instrument room, instrument and equipment is installed on bulkhead, the vibration that they are subject to when rocket takes off is through bulkhead input, so the vibration condition in whole cabin is input to instrument room lower end frame by shaking table, fixture in the vibration test of simulated flight environment.
The known large-scale jig of diameter more than 3 meters props up under state admittedly in the bottom surface at present, first order resonance frequency is all lower than 100Hz, and the vibration test frequency range of large-scale cabin section is generally 5Hz-100Hz, obviously the large-scale jig first order resonance frequency before is difficult to guarantee that (vertical fundamental frequency of large-scale experiment spare has more present 20Hz-40Hz) to the requirement more than three times higher than the single order response frequency of large-scale experiment spare of its single order response frequency in the test frequency band.Therefore needing badly provides more than a kind of natural frequency brings up to 100Hz, satisfies the carrier rocket instrument room vibration test fixture of testing requirements.
Summary of the invention
The technical problems to be solved in the utility model is to provide more than a kind of natural frequency brings up to 100Hz, satisfies the carrier rocket instrument room vibration test fixture of testing requirements.
For solving the problems of the technologies described above, a kind of carrier rocket instrument room of the utility model vibration test fixture comprises the upper surface of annular, square lower surface, and the sidewall that connects the upper and lower end face; Sidewall forms circular on the lower surface; Be equipped with some bolts hole on upper surface and lower surface; On sidewall, the edge circumferentially evenly is provided with the reinforcement that several connect the upper and lower end face; The external diameter of upper surface is 2.5 meters～3.5 meters; Sidewall thickness is greater than 20mm; The proportionate relationship of sidewall thickness, upper and lower end face thickness and Rib Thickness is about 1:2:2; The ratio of the height of test fixture and upper surface external diameter is less than 1:5, with the ratio of sidewall conglobate diameter of shape on the lower surface less than 1:3.
Reinforcement and upper and lower end face cohesive position all are provided with knuckle, and the diameter of knuckle is more than or equal to 10mm.
The quantity of reinforcement is 12～20.
The quantity of reinforcement is 16.
The upper surface external diameter is 3.2 meters, and the length of side of lower surface is 2.06 meters.
The utility model takes full advantage of the design feature of the test condition input face of vibration table surface and testpieces, use finite element analysis software, by abundant prerun, the calculating to aspects such as model frequency, antidumping moment, bolt tension, shearing stress, designed the vibration test fixture that is applicable to carrier rocket instrument room and similar structures testpieces (as: Upper Stage of rocket).
The utility model by analyzing reinforcement, each spot size, attachment screw reasonable layout, control, increases the rigidity of fixture in the situation that do not gain in weight, and more than the fixture first natural frequency is brought up to 100Hz, makes it to satisfy testing requirements.
The utility model satisfies the vibration test requirement fully, simultaneously, can accept CZ serial large-scale vibration test, and certain versatility is arranged.On the basis of this fixture face, the larger sized weld jig of transferring also can be completed the vibration test of other products.
Description of drawings
Fig. 1 is the schematic diagram of carrier rocket instrument room vibration test fixture provided by the utility model.
Embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail.
The utility model will be applicable to 30 tons of shaking tables.Because double star radome fairing quality weighs 7.5 tons, 4.2 meters of centers of gravity are largest domestic weight separate unit vibration tests.For guaranteeing to test smooth enforcement, to the very high requirement of design proposition of fixture.
The frequency range 5-100Hz of double star radome fairing vibration test identifies that the magnitude of level is peak accelerator 0.8g.Comprise the upper surface of annular, square lower surface, and the sidewall that connects the upper and lower end face; Sidewall forms circular on the lower surface; Be equipped with some bolts hole on upper surface and lower surface; On sidewall, the edge circumferentially evenly is provided with the reinforcement that several connect the upper and lower end face; The external diameter of upper surface is 2.5 meters～3.5 meters; Sidewall thickness is greater than 20mm; The proportionate relationship of sidewall thickness, upper and lower end face thickness and Rib Thickness is about 1:2:2; The ratio of the height of test fixture and upper surface external diameter is less than 1:5, with the ratio of sidewall conglobate diameter of shape on the lower surface less than 1:3.Preferred upper surface external diameter is 3.2 meters, and the length of side of lower surface is 2.06 meters.The quantity of reinforcement is 12～20, preferred 16.Reinforcement and upper and lower end face cohesive position all are provided with knuckle, and the diameter of knuckle is more than or equal to 10mm.
Be connected the aspect with shaking table, in order to increase coupling stiffness, strengthen fixture bottom surface connection area and attachment screw quantity and reach 52.
The utility model is not in the situation that general assembly (TW) increases, and the fixture bottom surface is entirely admittedly propped up the state fundamental frequency and significantly brought up to 145Hz.The upsetting moment that vibration table surface can bear is 6.25E5N*m.Greater than the maximum upsetting moment of test, but more approaching, so will monitor in test in the situation that barycenter place peak accelerator response enlargement factor is no more than 2 times, test can be carried out safely.
No. 45 steel of the material selection of bolt, material parameter is as follows: elastic modulus E=200GPa, Poisson's Ratio μ=0.3, density p=7800kg/m
3Diameter of bolt M20,52 of quantity distribute according to 30 tons of slide unit table top installation dimensions.
It is 306MPa that the bolt of fixture connects the maximum Mise stress that bears, less than the tensile strength 600MPa of M20 performance rate 6.8 grade bolts.Can adopt performance rate more than 8.8 grades in test, tensile strength is greater than the bolt of 800MPa.
The bolt of fixture connects the maximum shear stress 151MPa that bears, less than the shear resistance of 6.8 grade bolts.
Except weight, damping is also a factor of fixture selection on making, and larger damping can reduce the input and output ratio of fixture, reduces the amplification of fixture on resonant frequency.Also to consider in addition the factors such as difficulty or ease of price and processing, so, the material that our aluminium is made as fixture.
The damping ratio that the casting fixture is applicable to complicated and large-scale testpieces and foundry goods is larger, and this also is conducive to reduce the amplification of fixture on resonant frequency, so production method adopts casting.
Claims (5)
1. carrier rocket instrument room vibration test fixture is characterized in that: comprise the upper surface of annular, square lower surface, and the sidewall that connects the upper and lower end face; Sidewall forms circular on the lower surface; Be equipped with some bolts hole on described upper surface and lower surface; On sidewall, the edge circumferentially evenly is provided with the reinforcement that several connect the upper and lower end face; The external diameter of upper surface is 2.5 meters～3.5 meters; Sidewall thickness is greater than 20mm; The proportionate relationship of sidewall thickness, upper and lower end face thickness and Rib Thickness is about 1:2:2; The ratio of the height of described test fixture and upper surface external diameter is less than 1:5, with the ratio of sidewall conglobate diameter of shape on the lower surface less than 1:3.
2. a kind of carrier rocket instrument room vibration test fixture according to claim 1, it is characterized in that: described reinforcement and upper and lower end face cohesive position all are provided with knuckle, and the radius of described knuckle is more than or equal to 10mm.
3. a kind of carrier rocket instrument room vibration test fixture according to claim 1, it is characterized in that: the quantity of described reinforcement is 12～20.
4. a kind of carrier rocket instrument room vibration test fixture according to claim 3, it is characterized in that: the quantity of described reinforcement is 16.
5. a kind of carrier rocket instrument room vibration test fixture according to claim 1, it is characterized in that: described upper surface external diameter is 3.2 meters, the length of side of described lower surface is 2.06 meters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220546208 CN202947849U (en) | 2012-10-24 | 2012-10-24 | Vibration testing clamp of instrument cabin of lunch vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220546208 CN202947849U (en) | 2012-10-24 | 2012-10-24 | Vibration testing clamp of instrument cabin of lunch vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202947849U true CN202947849U (en) | 2013-05-22 |
Family
ID=48423545
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220546208 Expired - Lifetime CN202947849U (en) | 2012-10-24 | 2012-10-24 | Vibration testing clamp of instrument cabin of lunch vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202947849U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104048562A (en) * | 2013-09-30 | 2014-09-17 | 中国人民解放军国防科学技术大学 | Whole-missile vertical vibration test protection device |
| CN104266856A (en) * | 2014-09-23 | 2015-01-07 | 北京强度环境研究所 | Method for two-stage fairing-mounted rocket body free boundary implementation and fairing fixed-end boundary implementation in vibration tower |
| CN106289695A (en) * | 2016-09-20 | 2017-01-04 | 天津航天瑞莱科技有限公司 | Horizontal supporting system for the test of large-scale antenna system vibration |
| CN106441767A (en) * | 2016-12-07 | 2017-02-22 | 上海卫星装备研究所 | Ground vibration testing clamp for large spacecraft vibration |
| CN107228747A (en) * | 2017-05-08 | 2017-10-03 | 北京卫星环境工程研究所 | Large vibration table anchorage moment detection device |
| CN108168819A (en) * | 2017-12-21 | 2018-06-15 | 广州广电计量检测股份有限公司 | Vibration test fixture and method, vibration test fixture debugging system and method |
| CN114152153A (en) * | 2021-11-11 | 2022-03-08 | 重庆零壹空间科技集团有限公司 | Rocket body natural frequency test supporting platform |
-
2012
- 2012-10-24 CN CN 201220546208 patent/CN202947849U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104048562A (en) * | 2013-09-30 | 2014-09-17 | 中国人民解放军国防科学技术大学 | Whole-missile vertical vibration test protection device |
| CN104048562B (en) * | 2013-09-30 | 2016-01-20 | 中国人民解放军国防科学技术大学 | A kind of full bullet vertical vibration test safety device |
| CN104266856A (en) * | 2014-09-23 | 2015-01-07 | 北京强度环境研究所 | Method for two-stage fairing-mounted rocket body free boundary implementation and fairing fixed-end boundary implementation in vibration tower |
| CN104266856B (en) * | 2014-09-23 | 2016-08-31 | 北京强度环境研究所 | Two grades of band cover free boundaries and radome fairing built-in boundary implementation in vibration tower |
| CN106289695A (en) * | 2016-09-20 | 2017-01-04 | 天津航天瑞莱科技有限公司 | Horizontal supporting system for the test of large-scale antenna system vibration |
| CN106289695B (en) * | 2016-09-20 | 2019-12-31 | 天津航天瑞莱科技有限公司 | Horizontal supporting system for vibration test of large-scale antenna system |
| CN106441767A (en) * | 2016-12-07 | 2017-02-22 | 上海卫星装备研究所 | Ground vibration testing clamp for large spacecraft vibration |
| CN107228747A (en) * | 2017-05-08 | 2017-10-03 | 北京卫星环境工程研究所 | Large vibration table anchorage moment detection device |
| CN107228747B (en) * | 2017-05-08 | 2019-08-06 | 北京卫星环境工程研究所 | Large vibration table anchorage moment detection device |
| CN108168819A (en) * | 2017-12-21 | 2018-06-15 | 广州广电计量检测股份有限公司 | Vibration test fixture and method, vibration test fixture debugging system and method |
| CN114152153A (en) * | 2021-11-11 | 2022-03-08 | 重庆零壹空间科技集团有限公司 | Rocket body natural frequency test supporting platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130522 |
|
| CX01 | Expiry of patent term |