CN104833691B - A kind of test method and testing equipment for optimizing rudderpost thermal environment - Google Patents
A kind of test method and testing equipment for optimizing rudderpost thermal environment Download PDFInfo
- Publication number
- CN104833691B CN104833691B CN201510232469.2A CN201510232469A CN104833691B CN 104833691 B CN104833691 B CN 104833691B CN 201510232469 A CN201510232469 A CN 201510232469A CN 104833691 B CN104833691 B CN 104833691B
- Authority
- CN
- China
- Prior art keywords
- rudderpost
- test
- water
- simulation part
- height
- 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
Landscapes
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention discloses a kind of test method for optimizing rudderpost thermal environment, it is specially：Prepare the test simulation part that rudder joins position with rudderpost；Install water-cooled baffle additional on test simulation part surface and experiment bottom plate, experiment bottom plate and test simulation part lower surface formation air-flow gap are installed in bottom；Pad is placed in air-flow gap to simulate the height that rudderpost heats seal blanking cover boss, identical outer gas stream when being worked to air-flow gap is incident with rudderpost, collection is with reference to test point and the hot-fluid and pressure of target detection point, target detection point is recorded to obtain rudderpost compared with corresponding pad quantity when gathering hot-fluid and pressure drop the low amplitude maximum with reference to test point, and then conversion and most preferably heat seal blanking cover boss height.The present invention simulates the flight thermal environment of the local thermal protection structure of rudderpost by incident high temperature gas flow, rudderpost interference protection airvane simulating piece outer mold surface is shifted using water-cooled baffle, using spacer height design optimization rudderpost thermal environment.
Description
Technical field
The invention belongs to hot property experimental technique field, and in particular to a kind of test method of optimization rudderpost thermal environment and examination
Test equipment.
Background technology
Nearby interference-free coverage area is severe for the general relative bomb body of guided missile airvane rudderpost part thermal environment, hot-fluid, pressure state compared with
Height, the heat protection design of rudderpost directly affects the realization of rudderpost normal rotation ability, closely bound up with STT missile ability success or failure,
Rudderpost tests checking device as assessing, and rudderpost heat protection design is excellent to be particularly important.Airvane rudder is examined using full mould
Axle, often due to size is too big, farther out, causing the heating efficiency of wind-tunnel or electro-arc heater can not meet in nozzle distance examination area
Design requirement.
The content of the invention
It is an object of the invention to provide a kind of test method and testing equipment for optimizing rudderpost thermal environment, pass through incident high temperature
The flight thermal environment of simulation of air flow rudderpost part thermal protection structure, shifts rudderpost interference protection airvane using water-cooled baffle and simulates
Part outer mold surface, reduction causes the risk of test failure because of the destruction of airvane simulating piece, using spacer height design optimization rudderpost heat
Environment, it is determined that sealing blanking cover thrust height, instructs rudderpost heat protection design.
A kind of test method for optimizing rudderpost thermal environment, comprises the following steps：
(1) according to the physical dimension of actual air rudderpost, the test simulation part that rudder joins position with rudderpost is prepared；
(2) water-cooled baffle is installed additional on test simulation part surface, with shield gas flow at the trial so as to prevent test simulation part
It is ablated；
(3) experiment bottom plate, the rudder lower surface of experiment plate upper surface and test simulation part are installed in test simulation part bottom
Form air-flow gap；
(4) pad is placed in air-flow gap to simulate the height that rudderpost heats seal blanking cover boss, is set in front of boss
With reference to test point, target detection point is set in boss upper surface；
(5) pad quantity is changed to simulate the different height that rudderpost heats seal blanking cover boss, in the simulation of each boss height
When, identical outer gas stream when being worked to air-flow gap is incident with rudderpost, collection is with reference to test point and the hot-fluid of target detection point
And pressure, record target detection point is compared with corresponding pad number when gathering hot-fluid and pressure drop the low amplitude maximum with reference to test point
Amount, accordingly conversion obtains rudderpost and most preferably heats seal blanking cover boss height.
The advantageous effects of the inventive method are embodied in：The present invention takes the local crucial thermal protection structure of airvane rudderpost can
Solve the problem of big energy of size is small, the flight thermal environment of the incident local thermal protection structure of high temperature gas flow simulation rudderpost, using water
Cold apron shifts rudderpost interference protection airvane simulating piece outer mold surface, and reduction causes test failure because of the destruction of airvane simulating piece
Risk, using spacer height design optimization rudderpost thermal environment, it is determined that sealing blanking cover thrust height, instructs rudderpost thermal protection to set
Meter.
The present invention also provides the water-cooled baffle for realizing methods described, and the water-cooled baffle is energy envelope rudderpost rotational angle
Arcuate structure；The inner mold face of water-cooled baffle is multistage hierarchic structure, its multistage hierarchic structure in outer surface with test simulation part
Gas channel is bent with being formed；Water-cooling channel is machined with the plate of water-cooled baffle.
The advantageous effects of present device are embodied in：The present invention will be placed on water-cooled baffle in the installation of rudderpost testpieces
In, the maskable front incident air flow of water-cooled baffle front apron, the bending airflow channel structure that inner mold face is formed is reduced by bending
Air-flow velocity, can protect airvane simulating piece outer mold surface to wash away ablation from high temperature, and be cooled by interior water-cooling channel, identical
The incidence effect of state high temperature gas flow is issued to the purpose of examination rudderpost thermal protection structure.
Brief description of the drawings
Fig. 1 is test layouts schematic diagram of the invention.
Fig. 2 is point layout schematic diagram.
Fig. 3 (a) is anhydrous cold apron result schematic diagram of the invention, and Fig. 3 (b) is that the present invention has the signal of water-cooled baffle result
Figure.
Embodiment
Technical scheme is described further with preferred embodiment below in conjunction with the accompanying drawings.
Fig. 1 is referred to, the test method preferred embodiment of present invention optimization rudderpost thermal environment comprises the following steps：
(1) according to the physical dimension of actual air rudderpost, the test simulation part 1 that rudder joins position with rudderpost is prepared.Due to
Airvane full scale model is larger, and enough energy can not be provided during experiment and meet full-scale airvane rudderpost gap thermal environment,
Airvane is crucial thermal protection position with rudderpost handover region, and the thermal environment height in the region directly determines rudderpost thermal protection
The work accommodation ability of structure, therefore selection rudder prepares test simulation part with rudderpost handing-over position passing ratio diminution.
(2) water-cooled baffle 2 is installed additional on test simulation part surface, its shield gas flow is so as to prevent test simulation part at the trial
Ablated, reduction causes the risk of test failure because of the destruction of airvane simulating piece.The water-cooled baffle 2 rotates for energy envelope rudderpost
The arcuate structure of angle；The inner mold face of water-cooled baffle is multistage hierarchic structure, its multistage ladder in outer surface with test simulation part
Structure matching formation bending gas channel, reduces air-flow velocity by bending, can protect airvane simulating piece outer mold surface from height
Temperature washes away ablation；Water-cooling channel is machined with the plate of water-cooled baffle, quickly heat is taken away in flowing to in-channel water.
(3) experiment bottom plate 3, the experiment upper surface of bottom plate 3 and the rudder following table of test simulation part 1 are installed in test simulation part bottom
Face forms air-flow gap.
(4) pad 4 is placed in air-flow gap to simulate the height that rudderpost heats seal blanking cover boss, is set in front of boss
With reference to test point, target detection point is set in boss upper surface.Refer in Fig. 2, the embodiment of the present invention and set in front of boss
Two test references point a, b, target detection point c is set in boss upper surface, hot-fluid and pressure ratio compared with when adopted using a, b point
Set value average value is compared with c point collection values.In embodiment, single boss spacer thickness H3, single spacer thickness is 0.5mm,
It is N number of altogether, and ensure H3 × N<H1, i.e., do not influence rudderpost to rotate.
(5) quantity of pad 4 is changed to simulate the different height that rudderpost heats seal blanking cover boss, in the simulation of each boss height
When, identical outer gas stream when being worked to air-flow gap is incident with rudderpost, collection is with reference to test point and the hot-fluid of target detection point
And pressure, record target detection point is compared with corresponding pad number when gathering hot-fluid and pressure drop the low amplitude maximum with reference to test point
Measure, and then conversion obtains rudderpost and most preferably heats seal blanking cover boss height.It is described as follows：
Using the high temperature and high pressure gas of the incident certain flow of free jet equipment, on the basis of measuring point a, b in front of pad
(numerical simulation finds the measuring point interference most serious near boss, hot-fluid highest), debugs out hot-fluid Q corresponding with flying condition0、
Pressure step P0.The arc chamber stagnation pressure P of control incident air flow parameter is recorded simultaneouslys, voltage U, electric current A.Pad quantity is folded one by one
Plus, it is fixed into flow control parameter of emanating (arc chamber stagnation pressure Ps, voltage U, electric current A), measuring point c during different pad quantity is measured successively
Hot-fluid, pressure.When the hot c streams of measuring point, pressure reach minimum with reference to test point relatively, pad quantity N is recorded.With spacer thickness H3
× quantity N heats seal the central raised height H2 of blanking cover foundation as movable sealing structure.
Experiment is proved, whether there is boss Contrast on effect：Increase after boss, hot-fluid relative reduction amplitude reaches 46%~70%,
It is obvious to optimization rudderpost thermal environment effect.
Experiment proves there is the contrast of Non-water-cooled protecting effect：Under anhydrous cold apron protective condition, airvane simulating piece ablation is tight
Weight, gap length is unable to maintain that heat seal blanking cover screw melts substantially, and structure destruction is very risky, such as shown in 3 (a).Water cooling is kept off
Plate is obvious for the interference of transfer rudderpost, maintenance rudderpost seam shape effect, as shown in Fig. 3 (b).
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
Any modifications, equivalent substitutions and improvements made within refreshing and principle etc., should be included in the scope of the protection.
Claims (2)
1. a kind of test method for optimizing rudderpost thermal environment, it is characterised in that comprise the following steps：
(1) according to the physical dimension of actual air rudderpost, the test simulation part that rudder joins position with rudderpost is prepared；
(2) water-cooled baffle is installed additional on test simulation part surface, with shield gas flow at the trial so as to prevent that test simulation part from being burnt
Erosion；
(3) experiment bottom plate is installed in test simulation part bottom, the rudder lower surface of experiment plate upper surface and test simulation part is formed
Air-flow gap；
(4) pad is placed in air-flow gap to simulate the height that rudderpost heats seal blanking cover boss, reference is set in front of boss
Test point, target detection point is set in boss upper surface；
(5) pad quantity is changed to simulate the different height that rudderpost heats seal blanking cover boss, when each boss height is simulated, to
Identical outer gas stream when the incidence of air-flow gap works with rudderpost, collection is with reference to test point and the hot-fluid and pressure of target detection point
Power, corresponding pad quantity when record target detection point is compared with the hot-fluid and maximum pressure drop low amplitude for gathering reference test point, according to
This conversion obtains rudderpost and most preferably heats seal blanking cover boss height.
2. realize the water-cooled baffle of claim 1 methods described, it is characterised in that the water-cooled baffle rotates for energy envelope rudderpost
The arcuate structure of angle；The inner mold face of water-cooled baffle is multistage hierarchic structure, its multistage ladder in outer surface with test simulation part
Structure matching formation bending gas channel；Water-cooling channel is machined with the plate of water-cooled baffle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510232469.2A CN104833691B (en) | 2015-05-08 | 2015-05-08 | A kind of test method and testing equipment for optimizing rudderpost thermal environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510232469.2A CN104833691B (en) | 2015-05-08 | 2015-05-08 | A kind of test method and testing equipment for optimizing rudderpost thermal environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104833691A CN104833691A (en) | 2015-08-12 |
| CN104833691B true CN104833691B (en) | 2017-10-24 |
Family
ID=53811705
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510232469.2A Active CN104833691B (en) | 2015-05-08 | 2015-05-08 | A kind of test method and testing equipment for optimizing rudderpost thermal environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104833691B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181317B (en) * | 2015-09-22 | 2018-11-23 | 中国航天空气动力技术研究院 | Rudderpost heats seal experimental rig |
| CN106809375B (en) * | 2016-12-19 | 2019-05-24 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
| CN107991057A (en) * | 2017-12-28 | 2018-05-04 | 中国航天空气动力技术研究院 | A kind of airvane surface cold wall heat flow density and device for pressure measurement |
| CN109470374B (en) * | 2018-11-13 | 2020-11-10 | 中国航天空气动力技术研究院 | Rudder spindle heat flow measuring device in gap of 3-4mm |
| CN110567669A (en) * | 2019-08-06 | 2019-12-13 | 北京空天技术研究所 | method and device for measuring wing rudder gap heat flow of high-speed aircraft in wind tunnel test |
| CN110595971A (en) * | 2019-10-16 | 2019-12-20 | 恒天益科技（深圳）有限公司 | Ultra-low dust meter |
| CN110987353B (en) * | 2019-11-29 | 2022-04-22 | 中国航天空气动力技术研究院 | Surface pressure measuring device of rudder shaft interference area for arc wind tunnel aerodynamic heat test |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1375042A (en) * | 1999-10-20 | 2002-10-16 | Abb涡轮系统有限公司 | Method and device for the indirect cooling of a flow regime in radial slits formed between the rotors and stators of turbomachines |
| CN102494863A (en) * | 2011-11-15 | 2012-06-13 | 中国航天空气动力技术研究院 | Device used for testing height of hypersonic wind tunnel continuous variable projection |
| CN103954389A (en) * | 2014-05-09 | 2014-07-30 | 中国航天空气动力技术研究院 | Gas vane force measuring test device |
-
2015
- 2015-05-08 CN CN201510232469.2A patent/CN104833691B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1375042A (en) * | 1999-10-20 | 2002-10-16 | Abb涡轮系统有限公司 | Method and device for the indirect cooling of a flow regime in radial slits formed between the rotors and stators of turbomachines |
| CN102494863A (en) * | 2011-11-15 | 2012-06-13 | 中国航天空气动力技术研究院 | Device used for testing height of hypersonic wind tunnel continuous variable projection |
| CN103954389A (en) * | 2014-05-09 | 2014-07-30 | 中国航天空气动力技术研究院 | Gas vane force measuring test device |
Non-Patent Citations (4)
| Title |
|---|
| Numerical Simulation of Heating over the Rudder Shaft Gap in;J. M.Lei 等;《procedia engineering》;20131231;第412-419页 * |
| 大尺度空气舵超声速烧蚀热结构试验;张友华;《宇航材料工艺》;20081231(第5期);第78-80页 * |
| 飞行器典型热密封结构;李凡;《宇航材料工艺》;20131231(第1期);第20-25页 * |
| 高超声速飞行器结构材料与热防护系统;郭朝邦;《飞航导弹》;20101231(第4期);第88-94页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104833691A (en) | 2015-08-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104833691B (en) | A kind of test method and testing equipment for optimizing rudderpost thermal environment | |
| CN105181317B (en) | Rudderpost heats seal experimental rig | |
| CN106981321B (en) | Simulate the experimental rig and method of sodium-cooled fast reactor fuel assembly hot-working hydraulic characteristic | |
| CN103487345A (en) | High-temperature flame flow device for dynamically and cyclically testing thermal shock resistance of thermal barrier coating | |
| CN106952669B (en) | Stagnation pressure external container cooling test rack in a kind of fusant heap | |
| CN103016958A (en) | Method and system for temperature and humidity monitoring of high-energy pipeline subject to medium leakage in nuclear power plant | |
| CN111792061A (en) | Pneumatic thermal test device and method utilizing shock wave boundary layer interference | |
| CN102650571A (en) | System for measuring parameters of fluid flow in turbomachinery | |
| CN206725184U (en) | A kind of high temperature heat exchange wind tunnel testing system | |
| CN108332934A (en) | A kind of arc tunnel test method of non-ablative thermally protective materials/structure | |
| CN212621466U (en) | Aeroengine combustion chamber test bench test piece installation system | |
| CN109101764A (en) | The experiment simulator and method of rocket launching site fire heating environment | |
| Andrei et al. | Heat transfer in internal channel of a blade: effects of rotation in a trailing edge cooling system | |
| Bonanni et al. | Experimental survey on heat transfer in a trailing edge cooling system: effects of rotation in internal cooling ducts | |
| Han et al. | Experimental investigation on the effects of hole pitch and blowing ratio on the leading edge region film cooling of a rotating twist turbine blade | |
| Chang et al. | Thermal performance of impinging jet-row onto trapezoidal channel with different effusion and discharge conditions | |
| Hong et al. | Heat/mass transfer in rotating impingement/effusion cooling with rib turbulators | |
| CN111811768A (en) | Recovery enthalpy calibration test piece and wind tunnel heat assessment method | |
| CN112577703A (en) | Arc wind tunnel variable angle flat plate narrow gap heat flow measurement test device | |
| CN106568802A (en) | Free jet type supersonic flue gas flow enthalpy value steady state measurement apparatus | |
| CN202928778U (en) | Orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field | |
| Liu et al. | An experimental investigation of heat transfer characteristics in a steam-cooled square channel with rib turbulators | |
| Dann et al. | Innovative measurement techniques for a cooled turbine casing operating at engine representative thermal conditions | |
| CN109084828A (en) | Coal working face law of drop temperature pilot system and test method | |
| CN114112288B (en) | Enthalpy drop measuring device and method for arc wind tunnel spray pipe |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |