CN108332933A - The adjusting fixing device and arc tunnel experimental rig of thermally protective materials/structure - Google Patents
The adjusting fixing device and arc tunnel experimental rig of thermally protective materials/structure Download PDFInfo
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- CN108332933A CN108332933A CN201711163054.XA CN201711163054A CN108332933A CN 108332933 A CN108332933 A CN 108332933A CN 201711163054 A CN201711163054 A CN 201711163054A CN 108332933 A CN108332933 A CN 108332933A
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- testpieces
- tooling
- angle
- fixedly connected
- mounting tool
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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
Abstract
The present invention discloses a kind of the adjusting fixing device and arc tunnel experimental rig of thermally protective materials/structure, and it includes switching tooling to adjust fixing device, is fixedly connected with the front end of pedestal by angle of attack adjusting block and it is fixedly connected with the jet pipe of supersonic speed injector；Testpieces mounting tool rear portion bottom surface is fixedly connected with pedestal；Water conservancy diversion tooling is fixedly connected between testpieces mounting tool and the middle front part of pedestal；Testpieces is fixedly connected on testpieces mounting tool middle front part top surface；Testpieces mounting tool rear portion top surface is fixedly connected with induction shock wave tooling；Shock wave tooling leading-edge radius, angle of sweep, side pressure angle are induced, the testpieces mounting tool angle of attack, gap size realizes the formation of testpieces surface flow field state during experiment jointly between angle of attack adjusting block angle size and induction shock wave tooling and testpieces；Water conservancy diversion tooling is used to carry out water conservancy diversion to the boundary layer low energy fluid influenced by jet pipe cooling.Small-power wind-tunnel can be achieved to local high state thermal environment simulation in the present invention.
Description
Technical field
The present invention relates to thermally protective materials/technical field of structures.More particularly, to a kind of thermally protective materials/structure
Adjust fixing device and arc tunnel experimental rig.
Background technology
Currently, external spacefaring nation is in the development work of Efforts To Develop hypersonic aircraft, for outer thermal protection struc ture
Test evaluation demand under conditions of use is also increasingly urgent.Outer thermal protection struc ture as hypersonic aircraft key technology it
One, to ensure flight test success, it is necessary to carry out perfect ground experiment verification.The main examination material tolerance of arc tunnel experiment
The Burning corrosion resistance energy of flight environment of vehicle high temperature gas flow is of great significance to hypersonic aircraft thermally protective materials/structure examination.
Existing arc tunnel experimental rig includes supersonic speed injector, testpieces fixing device and vacuum system, is carried out
When arc tunnel is tested, electric arc heated of the air-flow through supersonic speed injector flows into the mixing chamber of supersonic speed injector, in mixing chamber
It is blended with cold air, after Rafael nozzle, with high temperature, enters test section at a high speed, it is solid to being fixed on testpieces in test section
The testpieces determined on device is washed away, and enters vacuum system through rear end pipeline (diffuser, cooler etc.), then by vacuum pump
Extraction is discharged into air.But it is limited by current ground-testing plant energy power limit, existing testpieces fixing device only plays fixed work
With cannot achieve the simulation to aircraft thermally protective materials/structure partial high state thermal environment so that heat protection design scheme
Reliability can not be verified, and there are larger technical risks.
Accordingly, it is desirable to provide the adjusting fixing device and arc tunnel experimental rig of a kind of thermally protective materials/structure.
Invention content
The purpose of the present invention is to provide a kind of can be improved, and the analog capability of environment is cut to local high pressure-temperature height, realizes small
Power wind-tunnel tests dress to the adjusting fixing device and arc tunnel of thermally protective materials/structure of local high state thermal environment simulation
It sets.
In order to achieve the above objectives, the present invention uses following technical proposals：
The invention discloses a kind of adjusting fixing devices of thermally protective materials/structure, including switching tooling, the angle of attack to adjust
Block, pedestal, water conservancy diversion tooling, testpieces mounting tool and induction shock wave tooling；
Switching tooling is fixedly connected with the front end of pedestal by angle of attack adjusting block and switching tooling and supersonic speed injector
The flange plate bolt of jet pipe is fixedly connected；The rear portion bottom surface of testpieces mounting tool is fixedly connected with the rear portion top surface of pedestal；It leads
Stream tooling is fixedly connected between the middle front part bottom surface of testpieces mounting tool and the middle front part top surface of pedestal；Thermally protective materials/
Structure is fixedly connected on the middle front part top surface of testpieces mounting tool as testpieces；The rear portion top surface of testpieces mounting tool with
The rear portion bottom surface of induction shock wave tooling is fixedly connected；
The leading-edge radius of induction shock wave tooling, angle of sweep, side pressure angle, the angle of attack of testpieces mounting tool, angle of attack adjusting block
Angle size and induction shock wave tooling and testpieces between gap size realizes jointly experiment during testpieces surface stream
The formation of field state；Water conservancy diversion tooling is used to carry out water conservancy diversion to the boundary layer low energy fluid influenced by jet pipe cooling.
Preferably, before thermally protective materials/structure is bonded or is bolted in testpieces mounting tool as testpieces
Portion top surface.
Preferably, the rear portion bottom surface of testpieces mounting tool and the rear portion top surface of pedestal are bolted.
Preferably, the rear portion top surface of testpieces mounting tool and the rear portion bottom surface of induction shock wave tooling are bolted.
The invention also discloses the adjustings of a kind of arc tunnel experimental rig, including above-mentioned thermally protective materials/structure to fix
Device
Beneficial effects of the present invention are as follows：
The arc tunnel experimental rig that technical solution of the present invention may make ground power smaller is realized to hypersonic
Outer surface regional area thermally protective materials/high hot-fluid of structure, high shear, the simulation of high-pressure environment during aircraft flight,
Experimentation cost, period are effectively reduced, discharges risk in advance, there is weight to the performance evaluation of thermal protection struc ture outside hypersonic aircraft
Want meaning.
Description of the drawings
Specific embodiments of the present invention will be described in further detail below in conjunction with the accompanying drawings；
Fig. 1 shows the assembling schematic diagram of the adjusting fixing device of thermally protective materials/structure.
Fig. 2 shows the vertical views of the adjusting fixing device of thermally protective materials/structure.
Fig. 3 shows the sectional view of the adjusting fixing device of thermally protective materials/structure.
Fig. 4 shows the assembling schematic diagram of arc tunnel experimental rig.
Specific implementation mode
In order to illustrate more clearly of the present invention, the present invention is done further with reference to preferred embodiments and drawings
It is bright.Similar component is indicated with identical reference numeral in attached drawing.It will be appreciated by those skilled in the art that institute is specific below
The content of description is illustrative and be not restrictive, and should not be limited the scope of the invention with this.
As Fig. 1-3 it is common shown in, a kind of adjusting fixing device of thermally protective materials/structure provided in this embodiment includes turn
Connect tooling 101, angle of attack adjusting block 102, pedestal 103, water conservancy diversion tooling 104, testpieces mounting tool 105 and induction shock wave tooling
106；
Switching tooling 101 be fixedly connected with the front end of pedestal 103 by angle of attack adjusting block 102 and switching tooling 101 with it is super
The flange plate bolt of the jet pipe of velocity of sound injector is fixedly connected；Behind the rear portion bottom surface of testpieces mounting tool 105 and pedestal 103
Portion top surface is fixedly connected (preferred bolt connection)；Water conservancy diversion tooling 104 is fixedly connected on the middle front part bottom of testpieces mounting tool 105
Between face and the middle front part top surface of pedestal 103；Thermally protective materials/structure is fixedly connected on testpieces erector as testpieces 40
The middle front part top surface for filling 105, to simulate the assembled state in aircraft outer surface；The rear portion top surface of testpieces mounting tool 105
It is fixedly connected (preferred bolt is connect) with the rear portion bottom surface of induction shock wave tooling 106；
The leading-edge radius of induction shock wave tooling 106, angle of sweep, side pressure angle, the angle of attack of testpieces mounting tool 105, the angle of attack
Gap size between the angle size and induction shock wave tooling 106 and testpieces 40 of adjusting block 102 realizes experiment process jointly
The formation of 40 surface flow field state of middle testpieces.Wherein, the incoming flow conditions for the gas that angle of attack adjusting block 102 is used to spray jet pipe
With the adjusting of the angle (i.e. the incoming angle of attack) of testpieces 40, the leading-edge radius for inducing shock wave tooling 106, angle of sweep, side pressure are adjusted
Angle, the angle of attack of testpieces mounting tool 105, the angle size and induction shock wave tooling 106 and testpieces 40 of angle of attack adjusting block 102
Between gap size, it can be achieved that adjusting to 40 surface flow field state of testpieces.Water conservancy diversion tooling 104 is used for being cooled down by jet pipe
The boundary layer low energy fluid of influence carries out water conservancy diversion, and the part low energy fluid is avoided to act on 40 surface of testpieces, causes experiment shape
State owes examination.
The assembly method of the adjusting fixing device 10 of thermally protective materials/structure provided in this embodiment is：It first will experiment
Part 40 is carried out be bonded or is bolted (using bonding, testpieces when testpieces 40 is composite material with testpieces mounting tool 105
40 are connected by screw bolts when being metal material)；Then by testpieces mounting tool 105 and induction shock wave tooling 106, pedestal 103
It is fixedly connected to combine；Switching tooling 101 is consolidated by angle of attack adjusting block 102 with the front end of pedestal 103 after combining again
Fixed connection, the adjusting fixing device for completing combination finally by the connecting hole of 101 both sides of switching tooling and supersonic speed injector
The flange plate bolt of jet pipe be fixedly connected.
Fixture structure characteristic size is adjusted by adjusting, specifically by the leading edge for adjusting induction shock wave tooling 106
Radius, angle of sweep, side pressure angle, the angle of attack of testpieces mounting tool 105, the angle size and induction shock wave of angle of attack adjusting block 102
Gap size between tooling 106 and testpieces 40 realizes the adjusting to 40 surface flow field state of testpieces, changes testpieces 40
The thermal environment on surface is remarkably improved the hot-fluid of 40 surface regional area of testpieces, the simulation effect of pressure and shearing force.
As shown in figure 4, a kind of arc tunnel experimental rig provided in this embodiment, including above-mentioned thermally protective materials/structure
Adjusting fixing device 10, supersonic speed injector 20 and vacuum system 30.
In the description of the present invention, it should be noted that the orientation or positional relationship of the instructions such as term "upper", "lower" is base
It in orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than indicates or imply
Signified device or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as to this
The limitation of invention.Unless otherwise clearly defined and limited, term " installation ", " connected ", " connection " shall be understood in a broad sense, example
Such as, it may be fixed connection or may be dismantle connection, or integral connection；It can be mechanical connection, can also be to be electrically connected
It connects；It can be directly connected, can also can be indirectly connected through an intermediary the connection inside two elements.For this
For the those of ordinary skill in field, the specific meanings of the above terms in the present invention can be understood according to specific conditions.
It should also be noted that, in the description of the present invention, relational terms such as first and second and the like are only used
Distinguish one entity or operation from another entity or operation, without necessarily requiring or implying these entities or
There are any actual relationship or orders between operation.Moreover, the terms "include", "comprise" or its any other change
Body is intended to non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wrapped
Those elements are included, but also include other elements that are not explicitly listed, or further include for this process, method, article
Or the element that equipment is intrinsic.In the absence of more restrictions, the element limited by sentence "including a ...", and
It is not excluded in process, method, article or equipment in the process, method, article or apparatus that includes the element that there is also other identical elements.
Obviously, the above embodiment of the present invention be only to clearly illustrate example of the present invention, and not be pair
The restriction of embodiments of the present invention for those of ordinary skill in the art on the basis of the above description can be with
It makes other variations or changes in different ways, all embodiments can not be exhaustive here, it is every to belong to the present invention
The obvious changes or variations extended out of technical solution still in protection scope of the present invention row.
Claims (5)
1. a kind of adjusting fixing device of thermally protective materials/structure, which is characterized in that including switching tooling, angle of attack adjusting block, bottom
Seat, water conservancy diversion tooling, testpieces mounting tool and induction shock wave tooling；
Switching tooling is fixedly connected with the front end of pedestal by angle of attack adjusting block and the jet pipe of switching tooling and supersonic speed injector
Flange plate bolt be fixedly connected；The rear portion bottom surface of testpieces mounting tool is fixedly connected with the rear portion top surface of pedestal；Water conservancy diversion work
Dress is fixedly connected between the middle front part bottom surface of testpieces mounting tool and the middle front part top surface of pedestal；Thermally protective materials/structure
The middle front part top surface of testpieces mounting tool is fixedly connected on as testpieces；The rear portion top surface of testpieces mounting tool and induction
The rear portion bottom surface of shock wave tooling is fixedly connected；
The leading-edge radius of induction shock wave tooling, angle of sweep, side pressure angle, the angle of attack of testpieces mounting tool, the folder of angle of attack adjusting block
Gap size between angle square cun and induction shock wave tooling and testpieces realizes testpieces surface flow field shape during experiment jointly
The formation of state；Water conservancy diversion tooling is used to carry out water conservancy diversion to the boundary layer low energy fluid influenced by jet pipe cooling.
2. the adjusting fixing device of thermally protective materials/structure according to claim 1, which is characterized in that thermally protective materials/
Structure is bonded as testpieces or is bolted in the middle front part top surface of testpieces mounting tool.
3. the adjusting fixing device of thermally protective materials/structure according to claim 1, which is characterized in that testpieces is installed
The rear portion bottom surface of tooling and the rear portion top surface of pedestal are bolted.
4. the adjusting fixing device of thermally protective materials/structure according to claim 1, which is characterized in that testpieces is installed
The rear portion top surface of tooling and the rear portion bottom surface of induction shock wave tooling are bolted.
5. a kind of arc tunnel experimental rig, which is characterized in that include the thermal protection material as described in any in claim 1-4
The adjusting fixing device of material/structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711163054.XA CN108332933B (en) | 2017-11-21 | 2017-11-21 | The fixed device of thermally protective materials/structure adjusting and arc tunnel experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711163054.XA CN108332933B (en) | 2017-11-21 | 2017-11-21 | The fixed device of thermally protective materials/structure adjusting and arc tunnel experimental rig |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108332933A true CN108332933A (en) | 2018-07-27 |
| CN108332933B CN108332933B (en) | 2019-03-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711163054.XA Active CN108332933B (en) | 2017-11-21 | 2017-11-21 | The fixed device of thermally protective materials/structure adjusting and arc tunnel experimental rig |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109253669A (en) * | 2018-10-29 | 2019-01-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of electro-arc heater change angle of attack test method |
| CN110457773A (en) * | 2019-07-19 | 2019-11-15 | 北京空天技术研究所 | High-speed aircraft leading edge shock interference arc wind-tunnel certification test model and method |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04142437A (en) * | 1990-10-02 | 1992-05-15 | Mitsubishi Heavy Ind Ltd | Start load reducing system for wind tunnel test model support device |
| US6481106B1 (en) * | 2001-01-03 | 2002-11-19 | Fiskars Consumer Oy Ab | Scissor action tool |
| CN102156143A (en) * | 2011-03-15 | 2011-08-17 | 哈尔滨工业大学 | Three-dimensional adjustable heat-preventing/insulating material ground simulation test device |
| CN102353512A (en) * | 2011-07-22 | 2012-02-15 | 北京航空航天大学 | Attack angle control method based on synchronous operation of multiple motors and multifunctional supporting device |
| CN103076152A (en) * | 2012-12-31 | 2013-05-01 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| CN103542997A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment |
| CN204188365U (en) * | 2014-10-11 | 2015-03-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of variable angle of attack supportive device for high-speed wind tunnel flutter model |
| CN106768829A (en) * | 2016-11-14 | 2017-05-31 | 北京航天长征飞行器研究所 | A kind of model transverse direction delivery device in high-temperature tunnel experimental cabin |
| CN206339360U (en) * | 2016-11-23 | 2017-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of arc tunnel treadmill test model support |
| CN206339361U (en) * | 2016-11-23 | 2017-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of warm test device of the arc tunnel flat plate model back of the body |
-
2017
- 2017-11-21 CN CN201711163054.XA patent/CN108332933B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04142437A (en) * | 1990-10-02 | 1992-05-15 | Mitsubishi Heavy Ind Ltd | Start load reducing system for wind tunnel test model support device |
| US6481106B1 (en) * | 2001-01-03 | 2002-11-19 | Fiskars Consumer Oy Ab | Scissor action tool |
| CN102156143A (en) * | 2011-03-15 | 2011-08-17 | 哈尔滨工业大学 | Three-dimensional adjustable heat-preventing/insulating material ground simulation test device |
| CN102353512A (en) * | 2011-07-22 | 2012-02-15 | 北京航空航天大学 | Attack angle control method based on synchronous operation of multiple motors and multifunctional supporting device |
| CN103076152A (en) * | 2012-12-31 | 2013-05-01 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| CN103542997A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment |
| CN204188365U (en) * | 2014-10-11 | 2015-03-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of variable angle of attack supportive device for high-speed wind tunnel flutter model |
| CN106768829A (en) * | 2016-11-14 | 2017-05-31 | 北京航天长征飞行器研究所 | A kind of model transverse direction delivery device in high-temperature tunnel experimental cabin |
| CN206339360U (en) * | 2016-11-23 | 2017-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of arc tunnel treadmill test model support |
| CN206339361U (en) * | 2016-11-23 | 2017-07-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of warm test device of the arc tunnel flat plate model back of the body |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109253669A (en) * | 2018-10-29 | 2019-01-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of electro-arc heater change angle of attack test method |
| CN110457773A (en) * | 2019-07-19 | 2019-11-15 | 北京空天技术研究所 | High-speed aircraft leading edge shock interference arc wind-tunnel certification test model and method |
| CN110457773B (en) * | 2019-07-19 | 2023-07-18 | 北京空天技术研究所 | High-speed aircraft leading edge shock wave interference arc wind tunnel assessment test model and method |
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| Publication number | Publication date |
|---|---|
| CN108332933B (en) | 2019-03-05 |
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