CN106052992B - The carrier rocket instrument room angular vibration test platform of low cross-linking coupling - Google Patents
The carrier rocket instrument room angular vibration test platform of low cross-linking coupling Download PDFInfo
- Publication number
- CN106052992B CN106052992B CN201610395835.0A CN201610395835A CN106052992B CN 106052992 B CN106052992 B CN 106052992B CN 201610395835 A CN201610395835 A CN 201610395835A CN 106052992 B CN106052992 B CN 106052992B
- Authority
- CN
- China
- Prior art keywords
- shaft
- test platform
- installation pedestal
- pedestal
- rolling bearing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
Abstract
A kind of carrier rocket instrument room angular vibration test platform of low cross-linking coupling, including the big plate of installation, shaft installation pedestal, vibrator installation pedestal, hydraulic vibration exciter, connecting column, hydraulic pressure flexural pivot, shaft fixed pedestal, shaft, rolling bearing, test platform；Wherein, big plate is installed to be fixedly connected with the track on ground, shaft installation pedestal is fixed on vibrator installation pedestal on the big plate of installation, hydraulic vibration exciter is fixedly mounted in vibrator installation pedestal, hydraulic vibration exciter upper end is connected by connecting column with hydraulic pressure flexural pivot, hydraulic pressure flexural pivot is connected with test platform, can be freely rotated；Shaft fixed pedestal bottom end is fixed in shaft installation pedestal, and upper and lower ends fix shaft in such a way that semicircle is to card, and two rolling bearings penetrate shaft, test platform is fallen on entire rolling bearing, after the promotion by hydraulic vibration exciter, rolling bearing is followed together, realize the rotation around axis.
Description
Technical field
The invention belongs to dynamics professional domains, and in particular to the carrier rocket instrument room angular vibration test of low cross-linking coupling
Platform.
Background technology
Carrier rocket carries out gesture stability using strapdown inertial measurement unit, and strapdown inertial measurement unit is mounted on instrument room, Control System Design
When need obtain instrument room state under kinetic characteristics, with it is carried out modeling and COMPENSATION NETWORK DESIGN.Therefore, control system
It needs to obtain and is used to group angle transmission characteristic parameter under instrument room state, carry out attitude stability control design case accordingly.Angle in order to obtain
Transmission characteristic, it is necessary to carry out the attribute testing research under instrument room state, obtain the characteristic ginseng of instrument room and used group mounting bracket
Number.
When early stage carries out carrier rocket instrument room angular vibration test, is loaded, passed through using low frequency six degree of freedom platform
The mode of controller Phase synchronization control realizes the excitation of table top angular oscillation, while measuring input and response, by data identification come
Obtain angle transmission characteristic.The control ability of this readily controlled instrument of method load mode influences, and leads to shaking for non-test direction
Dynamic input, to influence experiment input purity and characterization result measurement accuracy.If there is eccentric, reaction in instrument cabin structure
Influence meeting bigger to testing stand, causes the crosslinking of table top to couple larger, to further influence the input purity of experiment table top.
Therefore, for carrier rocket instrument room, the method input precision of angular oscillation load is carried out not using existing six degree of freedom platform
Height reduces the accuracy of test result, loads purity to improve angular vibration test, it is necessary to design new pilot system.
Invention content
In view of the above-mentioned problems, the present invention provides a kind of carrier rocket instrument room angular vibration test platform of low cross-linking coupling,
The pure angular oscillation excitation load for realizing single-degree-of-freedom, solve crosslinking when the excitation of current carrier rocket instrument room angular vibration test compared with
Big problem improves experiment loading accuracy, ensures the accuracy of measurement result.
A kind of carrier rocket instrument room angular vibration test platform of low cross-linking coupling, including the big plate 1 of installation, shaft installation pedestal
2, vibrator installation pedestal 3, hydraulic vibration exciter 4, connecting column 5, hydraulic pressure flexural pivot 6, shaft fixed pedestal 7, shaft 8, rolling bearing
9, test platform 10；
Wherein, big plate 1 is installed to be fixedly connected with the track on ground, shaft installation pedestal 2 is solid with vibrator installation pedestal 3
It is scheduled on and installs on big plate 1, hydraulic vibration exciter 4 is fixedly mounted in vibrator installation pedestal 3, and 4 upper end of hydraulic vibration exciter is by turning
It connects column 5 with hydraulic pressure flexural pivot 6 to be connected, hydraulic pressure flexural pivot 6 is connected with test platform 10, can be freely rotated；7 bottom end of shaft fixed pedestal
It is fixed in shaft installation pedestal 2, upper and lower ends fix shaft 8 in such a way that semicircle is to card, and two rolling bearings 9 penetrate
Shaft 8 carries oil film, rolling bearing 9 can be allowed 8 to be freely rotated around the shaft, on rolling bearing 9 between shaft 8 and rolling bearing 9
End is fixedly connected with test platform 10, and test platform 10 is fallen on entire rolling bearing 9, in the promotion by hydraulic vibration exciter 4
Afterwards, it follows rolling bearing 9 together, realizes the rotation around axis.
Further, big plate 1 is installed, shaft installation pedestal 2, vibrator installation pedestal 3, shaft fixed pedestal 7 is all made of
A3 steel.
Further, there is limiting device in shaft 8.
Further, rolling bearing 9 can constrain other sides there are one freedom of motion using the rigidity of its oil film
To movement.
Description of the drawings
Fig. 1 is that the carrier rocket instrument room angular vibration test platform of low cross-linking coupling removes the side view after test platform；
As shown in Figure 1, the wherein 1 big plate of installation, 2 shaft installation pedestals, 3 vibrator installation pedestals, 4 hydraulic vibration exciters, 5 turns
Connect column, 6 hydraulic pressure flexural pivots；
Fig. 2 is that the carrier rocket instrument room angular vibration test platform of low cross-linking coupling removes the front view after test platform；
As shown in Fig. 2, wherein 7 shaft fixed pedestals, 8 shafts, 9 rolling bearings；
Fig. 3 is the side view of the carrier rocket instrument room angular vibration test platform of low cross-linking coupling；
As shown in figure 3, wherein 10 test platforms；
Fig. 4 is the front view of the carrier rocket instrument room angular vibration test platform of low cross-linking coupling.
Specific implementation mode
Technical scheme of the present invention is described in further details with reference to the accompanying drawings and detailed description.Obviously, institute
The embodiment of description is only a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiment of the present invention,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts, belongs to this hair
Bright claimed range.
The carrier rocket instrument room angular vibration test platform structural representation of low cross-linking coupling is as shown in Figure 1, Figure 2, Figure 3 and Figure 4,
Including installing big plate, shaft installation pedestal, vibrator installation pedestal, hydraulic vibration exciter, connecting column, hydraulic pressure flexural pivot, shaft fixes
Pedestal, shaft, rolling bearing, test platform；Above-mentioned 10 part-structures from the bottom up, constitute angle vibration table main body successively.Its
In, it is A3 steel to install big plate, shaft installation pedestal, vibrator installation pedestal, by the way of welding and processing, is ensured enough
Coupling stiffness.Big plate is installed with the track on ground to be connected, is fixed using foundation bolt, shaft installation pedestal is pacified with vibrator
Dress pedestal is fixed on big plate, is respectively used to support shaft and vibrator.Hydraulic vibration exciter is the excitational equipment of angle vibration table, is used
In driving test platform movement, it is fixedly mounted in vibrator installation pedestal.Hydraulic vibration exciter upper end passes through connecting column and hydraulic pressure
Flexural pivot is connected.Hydraulic pressure flexural pivot is connected with test platform, can be freely rotated, and interference is generated when preventing hydraulic vibration exciter from moving.
Shaft fixed pedestal is A3 steel, and bottom end is fixed in shaft installation pedestal, and upper and lower ends will turn in such a way that semicircle is to card
Axis is fixed, and has limiting device in shaft, prevents shaft play in an axial direction.Two hydraulic rotation bearings penetrate shaft, shaft and axis
Oil film is carried between holding, and bearing can be allowed to be freely rotated around axis, and constrain the movement in other directions.Hydraulic rotation bearing upper end with
Test platform is connected, and test platform is fallen in entire rotation axis, after the promotion by hydraulic vibration exciter, follows hydraulic rotation moving axis
It holds together, realizes the rotation around axis.
The present invention provides excitation using hydraulic vibration exciter, carries out mobile decoupling using hydraulic pressure flexural pivot, uses hydraulic rotation moving axis
The other degree of freedom constraint for carrying out angular oscillation is held, the carrier rocket instrument room angle vibration table of low cross-linking coupling is constituted.Due to making
With hydraulic rotation bearing, the oil film rigidity in bearing is very big, can effectively be inhibited to the movement of crosslinking coupling, and oily
Film frictional force very little does not influence rotational motion substantially.In addition, since test platform has carried out design optimization, platform weight
Very light and intrinsic frequency is high, effectively increases test capability.Experiment application the result shows that, the crosslinking coupling of the angular vibration test platform
Conjunction is very low, has reached test index demand.
The foregoing description of the disclosed embodiments enables those skilled in the art to realize or use.To these implementations
A variety of modifications of example are it will be apparent that the general principles defined herein can be with for the patented technology personnel of this field
Without departing from the present invention, it realizes in other embodiments.Therefore, the present invention is not intended to be limited to this paper institutes
These embodiments shown, and it is to fit to widest range consistent with the principles and novel features disclosed in this article.
Claims (4)
1. a kind of carrier rocket instrument room angular vibration test platform of low cross-linking coupling, which is characterized in that including installing big plate (1),
Shaft installation pedestal (2), vibrator installation pedestal (3), hydraulic vibration exciter (4), connecting column (5), hydraulic pressure flexural pivot (6), shaft is solid
Determine pedestal (7), shaft (8), rolling bearing (9), test platform (10)；
Wherein, big plate (1) is installed to be fixedly connected with the track on ground, shaft installation pedestal (2) and vibrator installation pedestal (3)
It is fixed on the big plate (1) of installation, hydraulic vibration exciter (4) is fixedly mounted in vibrator installation pedestal (3), hydraulic vibration exciter (4)
Upper end is connected by connecting column (5) with hydraulic pressure flexural pivot (6), and hydraulic pressure flexural pivot (6) is connected with test platform (10), can freely turn
It is dynamic；Shaft fixed pedestal (7) bottom end is fixed in shaft installation pedestal (2), and upper and lower ends will turn in such a way that semicircle is to card
Axis (8) is fixed, and two rolling bearings (9) penetrate shaft (8), and oil film, Ke Yirang are carried between shaft (8) and rolling bearing (9)
(8) are freely rotated rolling bearing (9) around the shaft, and rolling bearing (9) upper end is fixedly connected with test platform (10), test platform
(10) it falls on entire rolling bearing (9), behind the promotion by hydraulic vibration exciter (4), follows rolling bearing (9) together, it is real
Now around the rotation of axis.
2. vibration mechine according to claim 1, it is characterised in that install big plate (1), shaft installation pedestal (2) swashs
Device installation pedestal of shaking (3), shaft fixed pedestal (7) are all made of A3 steel.
3. vibration mechine according to claim 1, it is characterised in that shaft has limiting device on (8).
4. vibration mechine according to claim 1, it is characterised in that rolling bearing (9) only there are one freedom of motion,
Using the rigidity of its oil film, the movement in other directions can be constrained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610395835.0A CN106052992B (en) | 2016-06-07 | 2016-06-07 | The carrier rocket instrument room angular vibration test platform of low cross-linking coupling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610395835.0A CN106052992B (en) | 2016-06-07 | 2016-06-07 | The carrier rocket instrument room angular vibration test platform of low cross-linking coupling |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106052992A CN106052992A (en) | 2016-10-26 |
| CN106052992B true CN106052992B (en) | 2018-11-06 |
Family
ID=57169569
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610395835.0A Active CN106052992B (en) | 2016-06-07 | 2016-06-07 | The carrier rocket instrument room angular vibration test platform of low cross-linking coupling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106052992B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108709708A (en) * | 2018-03-22 | 2018-10-26 | 天津航天瑞莱科技有限公司 | A kind of vibration experiment of aircraft aileron actuator |
| CN112414656B (en) * | 2020-11-06 | 2023-02-10 | 中国电子科技集团公司第十四研究所 | Cabin section vibration test automatic transmission installation system |
| CN114112274A (en) * | 2021-11-05 | 2022-03-01 | 上海机电工程研究所 | Separation test device under random vibration ejection condition and installation test method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006129556A1 (en) * | 2005-05-31 | 2006-12-07 | Idex Co., Ltd. | Transportation packaging test apparatus |
| CN101559396A (en) * | 2009-05-15 | 2009-10-21 | 江苏大学 | Triaxial vibration-decreasing/vibration-isolating platform of hammer crusher |
| CN101936803A (en) * | 2010-07-30 | 2011-01-05 | 中国船舶重工集团公司第七一七研究所 | Large-load mechanical angular vibration table |
| CN203811625U (en) * | 2014-04-30 | 2014-09-03 | 中国地震局工程力学研究所 | Rotating vibration table |
| CN104236836A (en) * | 2013-06-08 | 2014-12-24 | 北京强度环境研究所 | Pressure balancing system and method for rocket conveying pipeline system vibration test |
-
2016
- 2016-06-07 CN CN201610395835.0A patent/CN106052992B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006129556A1 (en) * | 2005-05-31 | 2006-12-07 | Idex Co., Ltd. | Transportation packaging test apparatus |
| KR20070085115A (en) * | 2005-05-31 | 2007-08-27 | 아이덱스 가부시키가이샤 | Transportation packaging test apparatus |
| CN101559396A (en) * | 2009-05-15 | 2009-10-21 | 江苏大学 | Triaxial vibration-decreasing/vibration-isolating platform of hammer crusher |
| CN101936803A (en) * | 2010-07-30 | 2011-01-05 | 中国船舶重工集团公司第七一七研究所 | Large-load mechanical angular vibration table |
| CN104236836A (en) * | 2013-06-08 | 2014-12-24 | 北京强度环境研究所 | Pressure balancing system and method for rocket conveying pipeline system vibration test |
| CN203811625U (en) * | 2014-04-30 | 2014-09-03 | 中国地震局工程力学研究所 | Rotating vibration table |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106052992A (en) | 2016-10-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106052992B (en) | The carrier rocket instrument room angular vibration test platform of low cross-linking coupling | |
| CN104865034B (en) | A kind of six-degree of freedom vibration excitation system | |
| CN101281088B (en) | Three-axis six-freedom degree vibration test apparatus | |
| Zhang et al. | Coupled microvibration analysis of a reaction wheel assembly including gyroscopic effects in its accelerance | |
| Nicholas et al. | Improving Critical Speed Calculations Using Flexible Bearing Support FRF Compliance Data. | |
| CN110095241B (en) | Method for testing and determining rigidity of cable between separate spacecraft cabins | |
| CN107941442B (en) | Vibration test device and method for performing vibration test on product | |
| CN201173849Y (en) | Rotor test stand | |
| Hwang et al. | Rotordynamic Performance Measurements and Predictions of a FCEV Air Compressor Supported on Gas Foil Bearings | |
| Nässelqvist et al. | Experimental and numerical simulation of unbalance response in vertical test rig with tilting-pad bearings | |
| Guan et al. | Nonlinear dynamic responses of a rigid rotor supported by active bump-type foil bearings | |
| JP2007271392A (en) | Method for calculating deviation in gravity center position of biaxial gimbal | |
| CN110426147B (en) | Device and method for measuring friction torque of deep groove ball bearing under gravity or microgravity | |
| Lee et al. | Analysis of Three-Pad Gas Foil Journal Bearing for Increasing Mechanical Preloads | |
| Shaik et al. | Tuning criteria of nonlinear flexible rotor mounted on squeeze film damper using analytical approach | |
| CN203037461U (en) | Bearing dynamic characteristic parameter testing apparatus | |
| CN209014233U (en) | Vibration device | |
| CN113031668A (en) | Method and system for estimating disturbance moment caused by asymmetric rotation scanning load | |
| CN110395415B (en) | Universal zero-gravity unloading device | |
| Forte et al. | Commissioning of a novel test apparatus for the identification of the dynamic coefficients of large tilting pad journal bearings | |
| RU2329467C1 (en) | Inertial platform | |
| CN103837348A (en) | Systems and methods for determining mass properties of vehicle components | |
| Kim et al. | Identification of dynamic characteristics of gas foil thrust bearings using base excitation | |
| CN201193977Y (en) | Vibration experiment apparatus with three axes and six degree of freedom | |
| RU2677942C2 (en) | Method of decontamination and excitation of vibrations in modal tests and device for its implementation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |