CN108195543A - A kind of aircraft wind tunnel model flutter blowing test system - Google Patents
A kind of aircraft wind tunnel model flutter blowing test system Download PDFInfo
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- CN108195543A CN108195543A CN201711231196.5A CN201711231196A CN108195543A CN 108195543 A CN108195543 A CN 108195543A CN 201711231196 A CN201711231196 A CN 201711231196A CN 108195543 A CN108195543 A CN 108195543A
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to aircraft wind-tunnel flutter test field, more particularly to a kind of aircraft wind tunnel model flutter blowing test system, including：Wind-tunnel；Model to be measured is fixed at by test fixture on the wind tunnel floor in wind-tunnel；Limiting device is arranged on model bottom to be measured, for limiting the amplitude of model to be measured；Sensor, positioned on model to be measured at the larger position of relative amplitude, for monitoring the real-time amplitude of model to be measured in real time；Data acquisition control system, for the real-time amplitude information of real-time reception sensor transmissions, and when real-time amplitude is more than predetermined amplitude, control limiting device limits the amplitude of model to be measured；Blowing test control system, for the model to be measured in the wind-tunnel to be controlled to carry out flutter blowing test.The aircraft wind tunnel model flutter blowing test system of the present invention, can prevent model from infinitely dissipating by model vibration control in a fixed amplitude, and flutter failure will not occur for protection model.
Description
Technical field
The present invention relates to aircraft wind-tunnel flutter test field, more particularly to a kind of aircraft wind tunnel model flutter blowing test system
System.
Background technology
The design of airplane flutter characteristic is an important link of airplane design, during aircraft Top-Down Design, to touch
The buffet characteristic of clear aircraft, will carry out a series of wind tunnel model flutter blowing test, make to fly by adjusting tunnel airstream parameter
Machine wind tunnel model reaches chatter state, obtains related data, and foundation is provided for actual airplane design, once and model enters flutter
State, if take not in time corresponding measure prevent model chatter state further dissipate, model will disintegration and failure, Wu Fajin
Row follow-up test, and the production cost of wind tunnel model is very high, and huge economic loss is also brought along once destroying.
Invention content
The object of the present invention is to provide a kind of aircraft wind tunnel model flutter blowing test system, to solve existing aircraft wind
Existing at least one problem during the model flutter blowing test of hole.
The technical scheme is that：
A kind of aircraft wind tunnel model flutter blowing test system, including：
Wind-tunnel；
Model to be measured is fixed at by test fixture on the wind tunnel floor in wind-tunnel；
Limiting device is arranged on the model bottom to be measured, for reaching the flutter of predetermined amplitude in the model to be measured
During state, the amplitude of the model to be measured is limited；
Sensor, at the larger position of relative amplitude on the model to be measured, for monitoring the model to be measured in real time
Real-time amplitude；
Data acquisition control system, for the real-time amplitude letter of the model to be measured of sensor transmissions described in real-time reception
Breath, and when the real-time amplitude is more than predetermined amplitude, the limiting device is controlled to limit the amplitude of the model to be measured；
Blowing test control system, for the model to be measured in the wind-tunnel to be controlled to carry out flutter blowing test.
Optionally, the limiting device includes：
Limited block is fixed at the model bottom to be measured, limiting slot is offered on the limited block；
Pressurized strut is fixed on the wind tunnel floor, and the pressurized strut is configured to extend to longest in its piston rod
During position, the piston rod end is extend into the limiting slot of the limited block, the piston rod end and the limiting slot it
Between have predetermined gap；
Pressurized strut driving device, for controlling the pressurized strut work according to the control instruction of the data acquisition control system
Make.
Optionally, the pressurized strut driving device is air compressor machine, is connected by pipeline with the pressurized strut；
The limiting device further includes：
Solenoid valve is arranged on the pipeline between the air compressor machine and the pressurized strut, the data acquisition control system
Pass through pressurized strut described in the solenoid valve control.
Optionally, the sensor is amplitude sensor, is fixed at the wind turbine apparatus, and apart from the mould to be measured
There is preset distance in the larger position of relative amplitude in type, for monitoring the amplitude information of the model to be measured in real time.
Invention effect：
The aircraft wind tunnel model flutter blowing test system of the present invention, can be by model vibration control in a fixed width
In degree, prevent model from infinitely dissipating, flutter failure will not occur for protection model.
Description of the drawings
Fig. 1 is the structure diagram of aircraft wind tunnel model flutter blowing test system of the present invention；
Fig. 2 is the schematic diagram of aircraft wind tunnel model flutter blowing test system of the present invention.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of range.
1 to Fig. 2 the present invention is described in further details below in conjunction with the accompanying drawings.
The present invention provides a kind of aircraft wind tunnel model flutter blowing test system, including wind-tunnel, model to be measured 1, limiting
Device, sensor 4, data acquisition control system 5 and blowing test control system.
Model 1 to be measured is fixed at by test fixture 2 on the wind tunnel floor 3 in wind-tunnel；Wind-tunnel can be at present
The a variety of suitable construction of wind tunnel known.
Limiting device is arranged on 1 bottom of model bottom to be measured, for reaching the chatter state of predetermined amplitude in model 1 to be measured
When, limit the amplitude of model 1 to be measured.
Sensor 4 is located on model 1 to be measured at the larger position of relative amplitude, for monitoring the real-time of model 1 to be measured in real time
Amplitude；
The model to be measured 1 that data acquisition control system 5 (i.e. processor) transmits for real-time reception sensor 4 shakes in real time
Width information, and when real-time amplitude is more than predetermined amplitude, control limiting device limits the amplitude of model 1 to be measured.Specifically, it senses
Device 4 is connect by signal wire with signal regulating device, then is connect with data acquisition control system.Wherein, predetermined amplitude can root
According to needing to carry out suitable setting.
Blowing test control system is used to control the model to be measured 1 in wind-tunnel to carry out flutter blowing test.
The aircraft wind tunnel model flutter blowing test system of the present invention, can be by model vibration control in a fixed width
In degree, prevent model from infinitely dissipating, flutter failure will not occur for protection model.
Further, in the present embodiment, preferably limiting device includes limited block 61, pressurized strut 62 and pressurized strut driving dress
It puts.
Limited block 61 is fixed at model bottom 1 to be measured, in addition, offering limiting slot on limited block 61；Pressurized strut 62
It is fixed on wind tunnel floor 3, pressurized strut 62 is configured to when its piston rod is extended to longest position, and piston rod end stretches into
Into the limiting slot of limited block 61, there is predetermined gap between piston rod end and limiting slot；Pressurized strut driving device is used for root
It works according to the control instruction control pressurized strut 62 of data acquisition control system 5.
Further, preferably pressurized strut driving device is air compressor machine 63, is connected by pipeline with pressurized strut 62；Correspondingly, it limits
Position device can also include 64 solenoid valve 64 of solenoid valve；
Solenoid valve 64 is arranged on the pipeline between air compressor machine and pressurized strut 62, and data acquisition control system 5 passes through electromagnetism
Valve 64 controls pressurized strut 62.
Further, in the present embodiment, preferably sensor 4 is amplitude sensor, is fixed at wind turbine apparatus, and distance is treated
Surveying the larger position of relative amplitude on model 1 has preset distance, for monitoring the amplitude information of model 1 to be measured in real time, due to sensing
Device is contactless, does not interfere with the buffet characteristic of model.
The experiment process of the aircraft wind tunnel model flutter blowing test system of the present invention is as follows：
Model 1 to be measured is installed in wind-tunnel, model 1 to be measured is after installation is complete, when flutter occurs for model 1 to be measured amplitude compared with
Amplitude sensor 4 is nearby installed in big position, and amplitude sensor 4 acquires the vibration signal of response point, the conditioned system tune of signal
Data acquisition control system 5 (data acquisition and analysis system) is transferred to after reason, by analysis, the vibration amplitude to meet with a response a little,
The vibration informations such as frequency, phase.According to 1 finite element stimulation of model to be measured as a result, can obtain flutter occur when amplitude compared with
Big response dot position information, while the information such as the vibration amplitude that response point during flutter occurs for model 1 to be measured, frequency can be obtained,
With reference to actual conditions, enter information into number and adopt in analysis and Control system software, which can be amplitude information combination frequency
Information, such as continuous multiple amplitudes reach expected horizontal, and frequency is stable sinusoidal signal frequency, you can regards as flutter.
After on-test, wind tunnel speed gradually changes, and slowly approaches flutter condition, and whole system works at the same time, and data are adopted
Collect 5 real-time collection analysis of control system from 4 collected information of amplitude sensor, when signal reaches the flutter condition of expected setting
When, system sends out control signal automatically, and control pressure solenoid valve 64 acts, so as to which 62 piston rod of control pressure pressurized strut pops up,
Piston rod is inserted into the limit hole of limiting device, makes model 1 to be measured that can only control amplitude in limiting amplitude internal vibration, prevent from treating
It surveys model 1 infinitely to dissipate, model is avoided to damage.
The test principle of the aircraft wind tunnel model flutter blowing test system of the present invention is as follows：
After installation is complete in wind-tunnel, in model flutter amplitude larger part (such as at wing tip) corresponding position occurs for test model
Non-contact optical fiber amplitude sensor is installed, sensor acquires the amplitude signal of response point, is transferred to control system computer, and one
Denier amplitude signal reaches the default chatter state thought, computer automatic trigger is mounted on the limiting device on model, by model
Vibration control prevents model from infinitely dissipating in a fixed amplitude, and flutter failure will not occur for protection model, simultaneously because
Sensor is contactless, does not interfere with the buffet characteristic of model.
All aircraft will strictly consider Flutter Problem in design and use, and the performance and safety for aircraft are
Essential key link, and model wind tunnel test is the Key experiments that must be carried out in every type airplane design flow, this hair
Bright aircraft wind tunnel model flutter blowing test system proposes infinitely diverging after inhibiting model generation flutter in wind tunnel test
One kind has been supplied to efficiently solve approach, it is particularly evident especially for the larger low-speed wind tunnel model test effect of model amplitude, it is right
There is important application value in terms of airplane flutter characteristic design analysis and verification experimental verification.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (4)
1. a kind of aircraft wind tunnel model flutter blowing test system, which is characterized in that including：
Wind-tunnel；
Model (1) to be measured, on the wind tunnel floor (3) being fixed in wind-tunnel by test fixture (2)；
Limiting device is arranged on model to be measured (1) bottom, for reaching quivering for predetermined amplitude in the model (1) to be measured
During state of shaking, the amplitude of the model (1) to be measured is limited；
Sensor (4), at the larger position of relative amplitude on the model (1) to be measured, for monitoring the mould to be measured in real time
The real-time amplitude of type (1)；
Data acquisition control system (5), for sensor described in real-time reception (4) transmission the model (1) to be measured it is real-time
Amplitude information, and when the real-time amplitude is more than predetermined amplitude, the limiting device is controlled to limit the model (1) to be measured
Amplitude；
Blowing test control system, for the model to be measured (1) in the wind-tunnel to be controlled to carry out flutter blowing test.
2. aircraft wind tunnel model flutter blowing test system according to claim 1, which is characterized in that the limiting device
Including：
Limited block (61) is fixed at the model bottom to be measured (1), limiting slot is offered on the limited block (61)；
Pressurized strut (62) is fixed on the wind tunnel floor (3), and the pressurized strut (62) is configured to extend in its piston rod
During to longest position, the piston rod end is extend into the limiting slot of the limited block (61), the piston rod end and institute
Stating has predetermined gap between limiting slot；
Pressurized strut driving device, for controlling the pressurized strut according to the control instruction of the data acquisition control system (5)
(62) it works.
3. aircraft wind tunnel model flutter blowing test system according to claim 2, which is characterized in that the pressurized strut is driven
Dynamic device is air compressor machine (63), is connected by pipeline with the pressurized strut (62)；
The limiting device further includes：
Solenoid valve (64) is arranged on the pipeline between the air compressor machine and the pressurized strut (62), the data acquisition control
System (5) controls the pressurized strut (62) by the solenoid valve (64).
4. according to claim 1-3 any one of them aircraft wind tunnel model flutter blowing test systems, which is characterized in that described
Sensor (4) is amplitude sensor, is fixed at the wind turbine apparatus, and the relative amplitude on the model (1) to be measured
There is preset distance in larger position, for monitoring the amplitude information of the model to be measured (1) in real time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231196.5A CN108195543A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft wind tunnel model flutter blowing test system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231196.5A CN108195543A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft wind tunnel model flutter blowing test system |
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| Publication Number | Publication Date |
|---|---|
| CN108195543A true CN108195543A (en) | 2018-06-22 |
Family
ID=62573404
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|---|---|---|---|
| CN201711231196.5A Pending CN108195543A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft wind tunnel model flutter blowing test system |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109297668A (en) * | 2018-10-30 | 2019-02-01 | 中国航天空气动力技术研究院 | A kind of rudder face gap wind-tunnel experiment simulator |
| CN109870289A (en) * | 2019-04-11 | 2019-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of T-type horizontal tail flutter model protective device and its application |
| CN111855132A (en) * | 2020-08-28 | 2020-10-30 | 中国航空工业集团公司沈阳空气动力研究所 | Flutter test safety protection system and method |
| CN111982454A (en) * | 2020-08-28 | 2020-11-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Arresting net protection system for flutter wind tunnel test and protection method thereof |
| CN113432820A (en) * | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel test system and method based on automation |
| CN113447235A (en) * | 2021-06-01 | 2021-09-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter model protection method and structure based on safe controllable damage |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109297668A (en) * | 2018-10-30 | 2019-02-01 | 中国航天空气动力技术研究院 | A kind of rudder face gap wind-tunnel experiment simulator |
| CN109870289A (en) * | 2019-04-11 | 2019-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of T-type horizontal tail flutter model protective device and its application |
| CN109870289B (en) * | 2019-04-11 | 2024-04-09 | 中国空气动力研究与发展中心高速空气动力研究所 | T-shaped horizontal tail flutter model protection device and application thereof |
| CN111855132A (en) * | 2020-08-28 | 2020-10-30 | 中国航空工业集团公司沈阳空气动力研究所 | Flutter test safety protection system and method |
| CN111982454A (en) * | 2020-08-28 | 2020-11-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Arresting net protection system for flutter wind tunnel test and protection method thereof |
| CN113432820A (en) * | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel test system and method based on automation |
| CN113447235A (en) * | 2021-06-01 | 2021-09-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter model protection method and structure based on safe controllable damage |
| CN113432820B (en) * | 2021-06-01 | 2022-05-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter wind tunnel test system and method based on automation |
| CN113447235B (en) * | 2021-06-01 | 2022-05-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Flutter model protection method and structure based on safe controllable damage |
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