CN106124144A - A kind of aerostatics mode testing method and system - Google Patents
A kind of aerostatics mode testing method and system Download PDFInfo
- Publication number
- CN106124144A CN106124144A CN201610425437.9A CN201610425437A CN106124144A CN 106124144 A CN106124144 A CN 106124144A CN 201610425437 A CN201610425437 A CN 201610425437A CN 106124144 A CN106124144 A CN 106124144A
- Authority
- CN
- China
- Prior art keywords
- aerostatics
- utricule
- excitation
- signal
- section
- 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.)
- Pending
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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The present invention relates to aerostatics mould measurement technical field, particularly relate to a kind of aerostatics mode testing method and system.The method at least includes: is sling by aerostatics and is suspended in closing space；Choose the nose cone position of described aerostatics and gondola position respectively as excitation point；Described aerostatics is divided into multiple cross section, each cross section is arranged some sensors；Excitation to nose cone position and gondola position clicks on row energization respectively；Pumping signal and the vibration signal produced during excitation is acquired.This system at least includes vibrator, sensor, Acquisition Instrument and computer.The present invention is for determining the eigenfrequncies and vibration models of aerostatics, it is possible to making aerostatics avoid resonance in the design process, the clearest and the most definite aerostatics is for the response condition of different dynamic load.
Description
Technical field
The present invention relates to aerostatics mould measurement technical field, particularly relate to a kind of aerostatics mode testing method and be
System.
Background technology
Aerostatics is the lighter-than-air craft as platform with balloon and dirigible, and wherein balloon is a kind of motorless flies
Row device, is generally divided into aerostat and captive balloon two class by its version with or without mooring device.Dirigible is then a kind of
There is the aerostatics of propulsion plant, the power of advance can be independently provided, blimp can be divided into by structure type, rigid flown
Ship and blimp.The basic structure of aerostatics is made up of nose cone, utricule, empennage, equipment pod and heaving pile etc..Nose cone is floating
The pocket important load assembly when Ground Mooring；Utricule be mainly used in filling be lighter than air gas be aerostatics provide rise
Power, is also the most typical structure member of aerostatics；The effect of empennage mainly provides stability and handling for aerostatics；Equipment
Gondola then mainly provides mounting space for staff or system equipment；Heaving pile is the peculiar parts of captive balloon, for mooring
The fixed point mooring of balloon provides constraint, can be also that ball carries equipment offer electric energy, it is possible to the data transmission carrying equipment for ball provides logical
Letter circuit.
The eyelid covering of aerostatics uses flexible thin-film material, is filled with the pressure helium higher than extraneous air to carry inside utricule
Make it keep certain profile and rigidity to bear certain external applied load for lift and generation prestressing force, belong to typical inflation thin
Membrane structure.The vibration of large deformation, low frequency and high-damping is generally there is in this membrane structure due to its light weight, feature that tension force is big
Feature, this produces serious influence for the form accuracy of structure, fatigue strength, bearing capacity etc..When utricule carry have with
During the load of track orientating function, owing to its rigidity is little, under the drive feedback of property loading period encourages, may induction from exciting
Dynamic.Being positioned at the empennage of utricule afterbody because of yardstick greatly, bladders afterbody rigidity is little, in himself motion and the common effect of air-flow
Under, the shimmy of empennage may be caused.For dirigible, the frequency under propeller rated speed is close with the fundamental frequency of hull, easily leads
Cause propeller, propeller is installed hull region near pedestal and pedestal and is resonated.This resonance has the biggest wound to structure
Evil, it might even be possible to directly result in utricule structural deterioration.
Accordingly, it would be desirable to design a kind of system and method that aerostatics is carried out mould measurement, come by this system and method
Aerostatics is identified and evaluates, so that it is determined that the eigenfrequncies and vibration models of the vibration characteristics of aerostatics, i.e. aerostatics, thus
Making aerostatics avoid resonance in the design process, the clearest and the most definite aerostatics is for the response condition of different types of dynamic load(loading).
Summary of the invention
(1) to solve the technical problem that
It is an object of the invention to provide a kind of aerostatics mode testing method and system, for determining the intrinsic frequency of aerostatics
Rate and the vibration shape, it is possible to making aerostatics avoid resonance in the design process, the clearest and the most definite aerostatics is for the sound of different dynamic load
Answer situation.
(2) technical scheme
In order to solve above-mentioned technical problem, the invention provides a kind of aerostatics mode testing method, at least include as follows
Step:
Aerostatics is sling and is suspended in closing space；
Choose the nose cone position of described aerostatics and gondola position respectively as excitation point；
Described aerostatics is divided into multiple cross section, each cross section is arranged some sensors；
Excitation to nose cone position and gondola position clicks on row energization respectively；
Pumping signal and the vibration signal produced during excitation is acquired.
Further, described aerostatics mode testing method also includes: by the described pumping signal collected and described
Vibration signal carries out signal conversion, is processed by model analysis software by the signal data after conversion.
Specifically, described aerostatics is sling by two ropes, and two described ropes are separately positioned on described floating
Both sides before and after the utricule of pocket.
Specifically, when nose cone position is encouraged, its excitation orientation include respectively the utricule axial direction along aerostatics,
Utricule horizontal direction along aerostatics and the utricule direction straight up along aerostatics, carried out three times on each excitation orientation
Excitation；When encouraging gondola position, its excitation orientation includes the utricule axial direction along aerostatics, respectively along aerostatics
Utricule horizontal direction and the utricule direction straight up along aerostatics, carry out three excitations on each excitation orientation.
Specifically, 6 cross sections of decile on the utricule of aerostatics, on each cross section, hoop is evenly arranged 8 sensors；
3 cross sections of decile on the empennage of aerostatics, arrange 3 sensors on each cross section.
Especially, described aerostatics carrying out exciting test in batches, the step of described exciting test in batches includes:
S1, on a cross section of aerostatics placement sensor；
S2, respectively excitation to nose cone position and gondola position click on row energization, the excitation produced during gathering excitation
Signal and vibration signal；
S3, sensor is moved being arranged to next cross section, repeating step S2, until completing swashing of described cross section
Encourage test.
In order to solve above-mentioned technical problem, present invention also offers a kind of aerostatics mould measurement system, including: exciting
Device, sensor, Acquisition Instrument and computer, wherein said vibrator, described sensor be connected with described Acquisition Instrument respectively, described in adopt
Collection instrument is connected with described computer；
Described vibrator is for encouraging the balloon generating vibrations of aerostatics, and output drive signal is to described Acquisition Instrument；Institute
State sensor for picking up the vibration signal that aerostatics produces, and export vibration signal to described Acquisition Instrument；Described Acquisition Instrument is used
In gathering described pumping signal and described vibration signal and carrying out signal conversion, the signal output after converting is to described calculating
Machine；Described computer is for carrying out model analysis process to the signal data gathered.
Further, it is connected between described vibrator with described Acquisition Instrument and has signal conditioner, described signal conditioner
For avoiding described pumping signal to be interfered.
Specifically, described vibrator uses pulse hammer, and described pulse hammer includes tup, force transducer and hammer handle, Qi Zhongsuo
Stating tup is rubber tup.
Specifically, described sensor uses power transformation to hold piezoelectric acceleration transducer.
(3) beneficial effect
The technique scheme of the present invention has the advantage that
The aerostatics mode testing method of present invention offer and system, by 2 exciting tests, namely choose aerostatics
Nose cone position and gondola position as excitation point, can solve owing to the huge response signal brought of aerostatics utricule structure declines
Subtract the problem causing picking up；By sectionalization test, also will be divided into multiple cross section by aerostatics, difference cloth on each cross section
Put sensor such that it is able to obtain measurement data more accurate, comprehensive.The aerostatics mould measurement side provided by the present invention
Method and system, it is possible to determine the eigenfrequncies and vibration models of aerostatics, make aerostatics avoid resonance in the design process, the most clearly
Aerostatics is for the response condition of different dynamic load.And mould measurement is also by harmonic responding analysis or transient dynamic analysis
Necessary early stage process.
Accompanying drawing explanation
Fig. 1 is the structural representation of the aerostatics mould measurement system of the embodiment of the present invention；
Fig. 2 is the pulse hammer structural representation of the embodiment of the present invention；
Fig. 3 is that schematic diagram is arranged in the aerostatics cross section of the embodiment of the present invention；
Fig. 4 is that the utricule cross-section sensor of the embodiment of the present invention arranges schematic diagram；
Fig. 5 is the empennage transducer arrangements schematic diagram of the embodiment of the present invention.
In figure: 1: utricule；2: nose cone position；3: gondola position；4: vibrator；5: sensor；6: signal conditioner；7: adopt
Collection instrument；8: computer；9: empennage；10: rope.
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained on the premise of not making creative work, broadly falls into the scope of protection of the invention.
Mould measurement and analysis are effective ways of research structure vibration.In test process, it is necessary first to will treat
Geodesic structure under static state carries out artificial exciting, by measuring exciting force and response and being analyzed, draw any two points it
Between transmission function, with Modal Analysis Theory by test transmission function curve matching, identify the mode treating geodesic structure
Parameter.
Owing to aerostatics volume and size are relatively big and structure is complicated, but relative density and quality are less, and single-point-excitation seems
Excitation energy is inadequate, and is lost relatively big in transmittance process, therefore encourages some place farther out in distance, and response signal is more weak,
Noise is smaller.If increasing exciting force, the most easily produce local acknowledgement excessive, cause non-linear phenomena.Additionally during single-point-excitation,
If excitation point is placed exactly in the node location of certain order mode state, for this order mode state, system will become uncontrollable and the most considerable,
Therefore will be unable to this order mode state of identification, the phenomenon of mode will occur to miss.Therefore, the aerostatics mould measurement of the present invention uses
2 exciting tests, be can effectively solve the problem that due to the huge response signal brought of aerostatics utricule structure by 2 exciting tests
The problem that decay causes picking up.
Current mould measurement and parameter identification method mainly have single-input single-output, single input and multi-output and multi input many
Export three kinds of methods.And multi-input multi-output system is built upon on the basis of " totally ", " simultaneously " identification, therefore it can profit
With measured full detail, decreasing artificial intervention and judgement, identification precision is high, and the modal parameter concordance of gained is good.
Therefore, the aerostatics mould measurement of the present invention uses multiple-input multiple-output method.
As Figure 1-5, the embodiment of the present invention select the utricule structure 1 that test target thing is captive balloon, then this
Bright aerostatics mode testing method, specifically includes following steps:
The utricule 1 of aerostatics is sling and is suspended in closing space, prevent air flowing from balloon vibrations is produced interference.
Choose the nose cone position 2 of described aerostatics and gondola position 3 respectively as excitation point.
Described aerostatics is divided into multiple cross section, each cross section is arranged some sensors 5.
Excitation to nose cone position and gondola position clicks on row energization respectively.
Pumping signal and the vibration signal produced during excitation is acquired.
The described pumping signal collected and described vibration signal are carried out signal conversion, the signal data after conversion is led to
Cross model analysis software to process.
Specifically, when carrying out mould measurement, need to make aerostatics utricule be in suspended state, and by aerostatics utricule
The working method that structure suspends completely means that any point does not produce with ground and contacts, and this constraints is relatively difficult to achieve, because of
This can replace by the way of rope suspensions, in embodiments of the present invention, by described aerostatics by two ropes 10
Slinging, two described ropes are separately positioned on both sides before and after the utricule of described aerostatics.Although this mode cannot be complete
The full actual condition simulating aerostatics, but rope is relative the least with utricule structure interface joint, and influence area is the most relatively
Little, simulation can be approximated, thus obtain accurate measurement data.
Specifically, owing to hammering method has feature fast, easily, to tested structure without additional mass and rigidity about
Bundle, therefore the energisation mode of the embodiment of the present invention is chosen hammering method and respectively nose cone position and gondola position is carried out pulse excitation.
When encouraging nose cone position, its excitation orientation includes respectively along utricule axial direction, along utricule horizontal direction and edge
Utricule direction straight up, carries out three excitations in each direction, and excitation need to treat that the response signal encouraged last time is basic every time
Carry out after disappearance, prevent double hit.When gondola position is encouraged, its excitation orientation, number of times all with nose cone position phase
With.
As in Figure 3-5, owing to aerostatics has the contour structures of complexity, therefore launch to survey respectively to utricule 1 and empennage 9
Examination.Relatively big in view of aerostatics physical dimension again, therefore utricule 1 and empennage 9 are carried out sectionalization test.That is, on utricule decile 6
Individual cross section, on each cross section, hoop is evenly arranged 8 sensors 5.3 cross sections of decile, cloth on each cross section on empennage 9
Put 3 sensors 5.Wherein said sensor 5 is firmly bonded with the eyelid covering of aerostatics.Certainly, divided on aerostatics cuts
Face quantity and the number of sensors arranged on each cross section, can be according to the concrete structure of aerostatics to be measured and reality
Measurement demand and be changed.
Owing to the volume of aerostatics is relatively big, if after all arranging sensor on each cross section, then carry out exciting test,
Then simultaneously need to greater number of sensor is arranged, the experimentation cost of this test mode is higher.In order to solve this
Problem, in further embodiment of the present invention, carries out exciting test in batches to described aerostatics, and concrete steps include:
S1, on a cross section of aerostatics placement sensor；
S2, respectively excitation to nose cone position and gondola position click on row energization, the excitation produced during gathering excitation
Signal and vibration signal；
S3, sensor is moved being arranged to next cross section, repeating step S2, until completing swashing of described cross section
Encourage test.
By above-mentioned exciting test method in batches, efficiently solve simultaneously need to a difficult problem for multiple sensor, and then fall
Low experimentation cost.
As shown in Figure 1-2, the embodiment of the present invention additionally provides a kind of aerostatics mould measurement system, including vibrator 4, passes
Sensor 5, Acquisition Instrument 7 and computer 8, wherein said vibrator 4, described sensor 5 are connected with described Acquisition Instrument 7 respectively, described
Acquisition Instrument 7 is connected with described computer 8.
Described vibrator 4 is for encouraging the utricule 1 of aerostatics to produce vibration, and output drive signal is to described Acquisition Instrument 7.
Described sensor 5 is for picking up the vibration signal that aerostatics produces, and exports vibration signal to described Acquisition Instrument 7.Described collection
Instrument 7 is used for gathering described pumping signal and described vibration signal and carrying out signal conversion, and the signal output after converting is to described
Computer 8.Described computer 8 is for carrying out model analysis process to the signal data gathered.
Furthermore, between described vibrator 4 and described Acquisition Instrument 7, it is also associated with signal conditioner 6, by described
Signal conditioner 6 can exempt the interference of shunt capacitance, it is to avoid signal is affected by line length.
Specifically, described vibrator uses pulse hammer, by pulse hammer, incentives target is clicked on horizontal pulse and encourages.Such as figure
Shown in 2, described pulse hammer includes tup, force transducer and hammer handle, due to the low frequency characteristic of aerostatics utricule structure, described tup
Use rubber tup.
Specifically, when the response measurement of modal test, owing to piezoelectric acceleration transducer has lightweight, volume
Little, frequency response width and highly sensitive feature, the most described sensor uses power transformation to hold piezoelectric acceleration transducer.
During use, first by described transducer arrangements on a cross section of utricule 1, utilize pulse hammer to nose cone position 2
Excitation point carries out exciting, and direction of excitation is respectively as follows: along utricule axial direction, utricule horizontal direction and direction straight up, often
Individual direction carries out three excitations, and each excitation need to be treated that the response signal encouraged last time disappears substantially and carry out afterwards, the company of preventing
Hit.When nose cone position 2 encourage complete after, pulse hammer is moved to gondola position 3 and encourages, excitation orientation and number of times and nose cone
Position is identical.Gondola position 3 encourage complete after, then complete single cross section signals collecting work, then movable sensor 5
Arrange to next section, until all cross sectional testings are complete.Finally utilize the model analysis software in computer 8 to measured
Data process, complete aerostatics mould measurement work.
In sum, the present invention provide aerostatics mode testing method and system, it is possible to determine the intrinsic frequency of aerostatics
Rate and the vibration shape, make aerostatics avoid resonance in the design process, and the clearest and the most definite aerostatics is for the response feelings of different dynamic load
Condition.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit；Although
With reference to previous embodiment, the present invention is described in detail, it will be understood by those within the art that: it still may be used
So that the technical scheme described in foregoing embodiments to be modified, or wherein portion of techniques feature is carried out equivalent；
And these amendment or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (10)
1. an aerostatics mode testing method, it is characterised in that at least comprise the steps:
Aerostatics is sling and is suspended in closing space；
Choose the nose cone position of described aerostatics and gondola position respectively as excitation point；
Described aerostatics is divided into multiple cross section, each cross section is arranged some sensors；
Excitation to nose cone position and gondola position clicks on row energization respectively；
Pumping signal and the vibration signal produced during excitation is acquired.
Aerostatics mode testing method the most according to claim 1, it is characterised in that also include: described in collecting
Pumping signal and described vibration signal carry out signal conversion, will conversion after signal data by model analysis software at
Reason.
Aerostatics mode testing method the most according to claim 1, it is characterised in that described aerostatics passes through two ropes
Slinging, two described ropes are separately positioned on both sides before and after the utricule of described aerostatics.
Aerostatics mode testing method the most according to claim 1, it is characterised in that when nose cone position is encouraged,
Its excitation orientation includes the utricule axial direction along aerostatics, the utricule horizontal direction along aerostatics and along aerostatics respectively
Utricule direction straight up, carries out three excitations on each excitation orientation；When gondola position is encouraged, its excitation orientation
Include respectively the utricule axial direction along aerostatics, the utricule horizontal direction along aerostatics and along aerostatics utricule vertically to
Upper direction, carries out three excitations on each excitation orientation.
Aerostatics mode testing method the most according to claim 1, it is characterised in that decile 6 on the utricule of aerostatics
Individual cross section, on each cross section, hoop is evenly arranged 8 sensors；3 cross sections of decile on the empennage of aerostatics, at each section
3 sensors are arranged on face.
Aerostatics mode testing method the most according to claim 1, it is characterised in that: described aerostatics is swashed in batches
Encouraging test, the step of described exciting test in batches includes:
S1, on a cross section of aerostatics placement sensor；
S2, respectively excitation to nose cone position and gondola position click on row energization, the pumping signal produced during gathering excitation
And vibration signal；
S3, sensor is moved it is arranged to next cross section, repeat step S2, until the excitation completing described cross section is surveyed
Examination.
7. an aerostatics mould measurement system, it is characterised in that including: vibrator, sensor, Acquisition Instrument and computer, its
Described in vibrator, described sensor be connected with described Acquisition Instrument respectively, described Acquisition Instrument is connected with described computer；
Described vibrator is for encouraging the balloon generating vibrations of aerostatics, and output drive signal is to described Acquisition Instrument；Described biography
Sensor is for picking up the vibration signal that aerostatics produces, and exports vibration signal to described Acquisition Instrument；Described Acquisition Instrument is used for adopting
Collecting described pumping signal and described vibration signal and carry out signal conversion, the signal output after converting is to described computer；Institute
State computer for the signal data gathered is carried out model analysis process.
Aerostatics mould measurement system the most according to claim 7, it is characterised in that in described vibrator and described collection
Connecting between instrument has signal conditioner, described signal conditioner to be used for avoiding described pumping signal to be interfered.
Method for aerostatics utricule mould measurement the most according to claim 7, it is characterised in that: described vibrator is adopted
By pulse hammer, described pulse hammer includes that tup, force transducer and hammer handle, wherein said tup are rubber tup.
Method for aerostatics utricule mould measurement the most according to claim 7, it is characterised in that: described sensor
Power transformation is used to hold piezoelectric acceleration transducer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610425437.9A CN106124144A (en) | 2016-06-15 | 2016-06-15 | A kind of aerostatics mode testing method and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610425437.9A CN106124144A (en) | 2016-06-15 | 2016-06-15 | A kind of aerostatics mode testing method and system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106124144A true CN106124144A (en) | 2016-11-16 |
Family
ID=57469980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610425437.9A Pending CN106124144A (en) | 2016-06-15 | 2016-06-15 | A kind of aerostatics mode testing method and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106124144A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN108846234A (en) * | 2018-06-29 | 2018-11-20 | 中国航空工业集团公司成都飞机设计研究所 | A kind of gondola is taken a flight test vibration monitoring method |
| CN110816882A (en) * | 2019-11-07 | 2020-02-21 | 中国科学院光电研究院 | Test method for surface water adhesion characteristics of aerostat |
| CN110816883A (en) * | 2019-11-07 | 2020-02-21 | 中国科学院光电研究院 | Aerostat surface water adhesion characteristic test system |
| CN110816881A (en) * | 2019-11-01 | 2020-02-21 | 中国科学院光电研究院 | Aerostat thermal characteristic test method |
| CN110816880A (en) * | 2019-11-01 | 2020-02-21 | 中国科学院光电研究院 | Aerostat thermal characteristic test system |
| CN111591408A (en) * | 2020-06-18 | 2020-08-28 | 中国船舶科学研究中心 | Real-scale marine propeller vibration mode measurement method |
| CN113306675A (en) * | 2021-07-06 | 2021-08-27 | 中国船舶工业集团公司第七0八研究所 | Modal parameter test measurement method under true prestress of marine propeller rotor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2666656A1 (en) * | 1990-09-11 | 1992-03-13 | Thomson Csf | Method and device for inspecting a structure by modal analysis |
| CN201408105Y (en) * | 2009-05-15 | 2010-02-17 | 北京工业大学 | Time-sharing fast steady-state sine sweep frequency shock excitation frequency response function measuring system |
| CN102135466A (en) * | 2010-11-18 | 2011-07-27 | 西安航空动力股份有限公司 | Method for testing vibration mode |
| CN103308263A (en) * | 2013-05-16 | 2013-09-18 | 哈尔滨工程大学 | Exciting device for testing modal of large structural component |
| CN104964805A (en) * | 2015-06-30 | 2015-10-07 | 宁波大学 | Method of measuring modal vibration mode and torsion vibration mode of flexible structure |
| CN105043698A (en) * | 2015-06-26 | 2015-11-11 | 东北大学 | Synchronous excitation system used for thin shell high-order modal shape test and test method |
| CN105424797A (en) * | 2015-11-05 | 2016-03-23 | 北京航空航天大学 | Device and method for performing modal testing on inflatable flexible film structure based on hammering excitation method |
-
2016
- 2016-06-15 CN CN201610425437.9A patent/CN106124144A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2666656A1 (en) * | 1990-09-11 | 1992-03-13 | Thomson Csf | Method and device for inspecting a structure by modal analysis |
| CN201408105Y (en) * | 2009-05-15 | 2010-02-17 | 北京工业大学 | Time-sharing fast steady-state sine sweep frequency shock excitation frequency response function measuring system |
| CN102135466A (en) * | 2010-11-18 | 2011-07-27 | 西安航空动力股份有限公司 | Method for testing vibration mode |
| CN103308263A (en) * | 2013-05-16 | 2013-09-18 | 哈尔滨工程大学 | Exciting device for testing modal of large structural component |
| CN105043698A (en) * | 2015-06-26 | 2015-11-11 | 东北大学 | Synchronous excitation system used for thin shell high-order modal shape test and test method |
| CN104964805A (en) * | 2015-06-30 | 2015-10-07 | 宁波大学 | Method of measuring modal vibration mode and torsion vibration mode of flexible structure |
| CN105424797A (en) * | 2015-11-05 | 2016-03-23 | 北京航空航天大学 | Device and method for performing modal testing on inflatable flexible film structure based on hammering excitation method |
Non-Patent Citations (2)
| Title |
|---|
| 余建新等: "薄膜充气环动态特性试验研究", 《振动与冲击》 * |
| 陈宇峰等: "柔性飞艇主气囊干湿模态分析与影响因素", 《上海交通大学学报》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107727340B (en) * | 2017-08-18 | 2019-09-17 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN108846234A (en) * | 2018-06-29 | 2018-11-20 | 中国航空工业集团公司成都飞机设计研究所 | A kind of gondola is taken a flight test vibration monitoring method |
| CN110816881B (en) * | 2019-11-01 | 2022-11-15 | 中国科学院空天信息创新研究院 | Aerostat thermal characteristic test method |
| CN110816880B (en) * | 2019-11-01 | 2022-11-15 | 中国科学院空天信息创新研究院 | Aerostat thermal characteristic test system |
| CN110816881A (en) * | 2019-11-01 | 2020-02-21 | 中国科学院光电研究院 | Aerostat thermal characteristic test method |
| CN110816880A (en) * | 2019-11-01 | 2020-02-21 | 中国科学院光电研究院 | Aerostat thermal characteristic test system |
| CN110816882A (en) * | 2019-11-07 | 2020-02-21 | 中国科学院光电研究院 | Test method for surface water adhesion characteristics of aerostat |
| CN110816883B (en) * | 2019-11-07 | 2021-07-16 | 中国科学院空天信息创新研究院 | Aerostat surface water adhesion characteristic test system |
| CN110816882B (en) * | 2019-11-07 | 2022-01-11 | 中国科学院空天信息创新研究院 | Test method for surface water adhesion characteristics of aerostat |
| CN110816883A (en) * | 2019-11-07 | 2020-02-21 | 中国科学院光电研究院 | Aerostat surface water adhesion characteristic test system |
| CN111591408B (en) * | 2020-06-18 | 2021-05-28 | 中国船舶科学研究中心 | Real-scale marine propeller vibration mode measurement method |
| CN111591408A (en) * | 2020-06-18 | 2020-08-28 | 中国船舶科学研究中心 | Real-scale marine propeller vibration mode measurement method |
| CN113306675A (en) * | 2021-07-06 | 2021-08-27 | 中国船舶工业集团公司第七0八研究所 | Modal parameter test measurement method under true prestress of marine propeller rotor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106124144A (en) | A kind of aerostatics mode testing method and system | |
| CN107121254B (en) | A kind of large size guided missile on-hook vibration rig and method | |
| CN108226399B (en) | A kind of beam-string structure damage combined recognising method based on modal parameter | |
| CN107101927B (en) | Experimental device and method for permeability test of aerostat capsule material | |
| WO2016060417A1 (en) | Fairing, and fatigue test apparatus and method using same | |
| WO2022016907A1 (en) | Two-axis loading fatigue testing method for fan full-size blade and two-axis loading device | |
| CN107264834B (en) | A kind of agricultural unmanned plane indoor test platform and test method | |
| CN106840559B (en) | A kind of adjustable single layer and double-layer vibration isolating system vibration mechine and test method | |
| CN109050970B (en) | A kind of ground experiment method under simulation aircraft components dangerous position is loaded in the sky | |
| CN103308295A (en) | Control and check test method for flight control mechanical control system | |
| CN106289947A (en) | A kind of high-strength light girder construction damnification recognition method | |
| CN108088731A (en) | A kind of aircraft nose landing gear outer barrel strut connector launch slow test method | |
| CN107085633A (en) | The device and method of multiple spot vibratory response frequency domain prediction based on SVMs | |
| CN107357980A (en) | A kind of damnification recognition method of axial functionally gradient beam | |
| CN109086501A (en) | A kind of flutter prediction technique | |
| Gundlach et al. | Experimental modal analysis of aeroelastic tailored rotor blades in different boundary conditions | |
| CN112729734B (en) | Method for measuring transfer characteristics of series-type vibration isolator | |
| CN110361187A (en) | A kind of flexible structure test pneumatic load test device | |
| CN213714668U (en) | Aircraft spoiler vibration fatigue test loading device | |
| CN115962887B (en) | Method for calculating vibration fatigue load spectrum of external store on-hook of airplane by experimental analogization method | |
| CN205776415U (en) | Piled-box foundaton isolation property test model case | |
| CN209410359U (en) | A kind of flexible annular skeleton radial mechanical performance experimental rig | |
| CN105644801A (en) | Adjustment method for helicopter rotor single blade interchange | |
| CN108398248A (en) | The method and apparatus that the load of pulling in aerostatics utricule structure is measured | |
| CN107036802A (en) | A kind of shock absorber overloading-vibrating environment pilot system and test method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161116 |