CN103264773A - Seasonal icing test bench - Google Patents
Seasonal icing test bench Download PDFInfo
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- CN103264773A CN103264773A CN2013101489241A CN201310148924A CN103264773A CN 103264773 A CN103264773 A CN 103264773A CN 2013101489241 A CN2013101489241 A CN 2013101489241A CN 201310148924 A CN201310148924 A CN 201310148924A CN 103264773 A CN103264773 A CN 103264773A
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Abstract
The invention aims to provide a seasonal icing test bench. The seasonal icing test bench comprises a collection section, a power section, an expansion section, a stabilizing section, a protective net, a supporting piece, a fairing, a hub, blades, a motor, rotation stopping pieces, a separation preventing net, a honeycomb and a spraying device. The protective net is mounted in the collection section which is connected with the power section through a flange, the motor is mounted in the fairing, the expansion section is connected with the power section through a flange, the separation preventing net in a layer is mounted in the expansion section which is connected with the stabilizing section through a flange, the honeycomb is mounted in the stabilizing section, and the spraying device is connected with the tail end of the stabilizing section. All the parts are designed to adapt to low temperature, thereby the seasonal icing test bench can be operated in the low-temperature environment. The spraying device is arranged at an outlet of the test bench, so that the test bench has a universal blowing capability as well as a capability of performing icing test on the ground, and has an extensive capability of simulating icing test of an overall aircraft or parts.
Description
Technical field
The present invention relates to a kind of aircraft environment simulation experiment system, be specifically related to a kind of seasonal icing tests platform, be used for aircraft complete machine or parts are carried out the icing simulated environment test in ground.
Background technology
Along with the development at home of various novel machines, more and more for the demand of wind tunnel test, require also more and more higher.The aircraft that flies in atmospheric envelope may be run into the icing phenomenon of parts, freezing influences flight safety and the airworthiness of aircraft, make a general survey of countries in the world, the country of all capable independent research and development aircraft, great majority have research, the assessment aircraft freezes and anti-icing experimental investigation platform.Development along with aircraft research, wind-tunnel is also in development, for the demand that makes the development of aircraft icing tests ability and contemporary aircraft adapts, external old equipment constantly renovates, and the design and construction of new installation is also more modern, practical, multi-functional.
Be accompanied by the development of aircraft of new generation in recent years, require each parts of aircraft to have stronger anti-icing ability, to adapt to the requirement of various flight environment of vehicle, for example aircraft wing and engine nacelle when high-altitude low temperature environment flies can freeze, this just requires airplane design that the leading edge of a wing and engine nacelle are carried out anti-icing processing, and the sufficiency by anti-icing and deicing system works in the experimental examination flight envelope, and guarantee that the ice cube that falls down from the surface of no anti-icing device must not cause the damage of driving engine or other crucial annex.
Mainly adopting CFD in the icing characteristic of aerodynamics area research aircraft is computational fluid mechanics, flight test and icing tests three big means.And accurate and effective, study the freeze method of characteristic of new aircraft rapidly, no more than developing the freeze icing tests platform of state of a kind of simulated flight device.The test cell of this new ideas all have great potential and using value at prototype and the model aircraft characteristic data that freezes aspect obtaining.
Summary of the invention
The purpose of this invention is to provide a kind of seasonal icing tests platform that utilizes seasonal climate aircraft complete machine or parts to be carried out icing tests.
The present invention is achieved in that a kind of seasonal icing tests platform, comprise the collection section, power section, diffuser, settling chamber, grille guard, supporting blade, fairing, wheel hub, blade, motor, end blade, anti-separate mesh, honeycombs and atomising installation, one deck grille guard is installed in the collection section, the collection section is connected with power section by flange, fairing by supporting blade with end blade and be connected with power section, motor is installed in the fairing, wheel hub is connected with the output shaft of motor, blade is connected with wheel hub, diffuser is connected with power section by flange, the anti-separate mesh of one deck is installed in the diffuser, diffuser is connected with settling chamber by flange, honeycombs is installed in the settling chamber, and atomising installation is connected with the end of settling chamber.
The present invention has taked the low-temperature adaptation design to each parts, can enough move under low temperature environment.The test cell exit is provided with atomising installation, makes these test cell except having general blowing ability, also possesses the ability of carrying out icing tests on ground, has aircraft complete machine or parts icing tests analog capability widely.
Description of drawings
Fig. 1 is structural representation of the present invention.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing:
As shown in Figure 1, test cell are made up of collection section 1, power section 2, diffuser 3, settling chamber 4 and atomising installation 14, each section coaxial tandem successively connects, one deck grille guard 5 is installed in the collection section 1, power section 2 is utilized motor 10 to drive the fan system rotation and is produced lasting airflow flowing, the anti-separate mesh 12 of one deck is installed in the diffuser 3, honeycombs 13 is installed in the settling chamber 4, the exit arranges atomising installation 14.Collection section 1 is used for collecting air-flow, and interior dress one deck grille guard 5 prevents that fan when operation aspirated foreign body from breaking fan component, and collection section 1 directly is connected by flange with power section 2.Power section 2 mainly by fairing 7, supporting blade 6, end blade 11, blade 9 and wheel hub 8 and motor 10 is formed.Fairing 7 by supporting blade 6 and only blade 11 be connected with the power section housing.Blade 9 uniform being installed on the wheel hub 8, motor 10 is installed in the fairing 7, and the output shaft of motor 10 directly is connected with wheel hub 8, and drive fan systems rotation produces air-flow, and power section 2 and collection section 1 and diffuser 3 directly are connected by flange.Diffuser 3 is used for adjusting stream pressure, and interior dress one deck is prevented separate mesh 12, prevents that air-flow from separating, and diffuser 3 and power section 2 and settling chamber 4 directly are connected by flange.
Settling chamber 4 is used for steady air flow, and interior dress honeycombs 13 is used for reducing the turbulence of air-flow, forms stable exit flow.Settling chamber 4 and diffuser 3 directly are connected by flange.Atomising installation 14 is used for producing the steam particle, utilizes the air-flow of settling chamber 4 outlet ejections to form stable spraying.
The test cell operational process is as follows: motor 10 drives blade 9 and wheel hub 8 rotations, air is sucked collection section 1, through the fairing 7 of power section 2 with end blade 11 backs and produce stable air-flow, adjust stream pressure through diffuser 3, pass through settling chamber 4 and inner honeycombs 13 again, greatly reduce the turbulence of air-flow, thereby produce stable high-quality flow field, the air-flow that settling chamber 4 outlets produce produces spraying with the steam particle ejection that atomising installation 14 produces.Each parts of test cell adopt the low-temperature adaptation design, can be at stable operation under the low temperature environment.
Claims (1)
1. seasonal icing tests platform, comprise collection section (1), power section (2), diffuser (3), settling chamber (4), grille guard (5), supporting blade (6), fairing (7), wheel hub (8), blade (9), motor (10), end blade (11), anti-separate mesh (12), honeycombs (13) and atomising installation (14), it is characterized in that: one deck grille guard (5) is installed in collection section (1), collection section (1) is connected with power section (2) by flange, fairing (7) by supporting blade (6) and only blade (11) be connected with power section (2), motor (10) is installed in the fairing (7), wheel hub (8) is connected with the output shaft of motor (10), blade (9) is connected with wheel hub (8), diffuser (3) is connected with power section (2) by flange, the anti-separate mesh (12) of one deck is installed in the diffuser (3), diffuser (3) is connected with settling chamber (4) by flange, honeycombs (13) is installed in the settling chamber (4), and atomising installation (14) is connected with the end of settling chamber (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310148924.1A CN103264773B (en) | 2013-04-26 | 2013-04-26 | Seasonal icing test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310148924.1A CN103264773B (en) | 2013-04-26 | 2013-04-26 | Seasonal icing test bench |
Publications (2)
| Publication Number | Publication Date |
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| CN103264773A true CN103264773A (en) | 2013-08-28 |
| CN103264773B CN103264773B (en) | 2015-05-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310148924.1A Expired - Fee Related CN103264773B (en) | 2013-04-26 | 2013-04-26 | Seasonal icing test bench |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104913898A (en) * | 2015-06-01 | 2015-09-16 | 东北农业大学 | Horizontal axis wind turbine icing wind tunnel experimental system and method utilizing natural low temperature airflow |
| CN107084829A (en) * | 2017-06-12 | 2017-08-22 | 西南交通大学 | A kind of atmospheric boundary layer wind tunnel |
| CN109186925A (en) * | 2018-08-20 | 2019-01-11 | 中国飞机强度研究所 | Wind-tunnel and wind tunnel test system |
| CN110702419A (en) * | 2019-10-11 | 2020-01-17 | 中国直升机设计研究所 | Anti-icing conformance test system and method for engine air inlet system |
| WO2021088097A1 (en) * | 2019-11-07 | 2021-05-14 | 中国科学院空天信息创新研究院 | Aerostat icing characteristic numerical simulation and experimental verification system |
| CN114894430A (en) * | 2022-07-13 | 2022-08-12 | 中国航空工业集团公司沈阳空气动力研究所 | Installation accuracy measurement method of wind tunnel honeycomb device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009025578A1 (en) * | 2007-08-14 | 2009-02-26 | Central Institute Of Aviation Motors (Ciam) | Method for ground testing of aerospace engineering objects exposed to icing and a device for carrying out said method |
| CN102166536A (en) * | 2011-03-02 | 2011-08-31 | 中国民航大学 | An environment analogue means for surface freezing of airplanes on ground |
| CN102914416A (en) * | 2012-09-20 | 2013-02-06 | 同济大学 | Direct-cooling freezing wind tunnel realization method and direct-cooling freezing wind tunnel realization system |
| CN203372397U (en) * | 2013-04-26 | 2014-01-01 | 中国航空工业空气动力研究院 | Seasonal icing test bench |
-
2013
- 2013-04-26 CN CN201310148924.1A patent/CN103264773B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009025578A1 (en) * | 2007-08-14 | 2009-02-26 | Central Institute Of Aviation Motors (Ciam) | Method for ground testing of aerospace engineering objects exposed to icing and a device for carrying out said method |
| CN102166536A (en) * | 2011-03-02 | 2011-08-31 | 中国民航大学 | An environment analogue means for surface freezing of airplanes on ground |
| CN102914416A (en) * | 2012-09-20 | 2013-02-06 | 同济大学 | Direct-cooling freezing wind tunnel realization method and direct-cooling freezing wind tunnel realization system |
| CN203372397U (en) * | 2013-04-26 | 2014-01-01 | 中国航空工业空气动力研究院 | Seasonal icing test bench |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104913898A (en) * | 2015-06-01 | 2015-09-16 | 东北农业大学 | Horizontal axis wind turbine icing wind tunnel experimental system and method utilizing natural low temperature airflow |
| CN104913898B (en) * | 2015-06-01 | 2017-08-11 | 东北农业大学 | Utilize natural low temperature flow level axle wind energy conversion system icing tunnel experimental system and method |
| CN107084829A (en) * | 2017-06-12 | 2017-08-22 | 西南交通大学 | A kind of atmospheric boundary layer wind tunnel |
| CN109186925A (en) * | 2018-08-20 | 2019-01-11 | 中国飞机强度研究所 | Wind-tunnel and wind tunnel test system |
| CN110702419A (en) * | 2019-10-11 | 2020-01-17 | 中国直升机设计研究所 | Anti-icing conformance test system and method for engine air inlet system |
| WO2021088097A1 (en) * | 2019-11-07 | 2021-05-14 | 中国科学院空天信息创新研究院 | Aerostat icing characteristic numerical simulation and experimental verification system |
| US11161629B2 (en) | 2019-11-07 | 2021-11-02 | Aerospace Information Research Institute, Chinese Academy Of Sciences | System for numerical simulation and test verification of icing characteristics of an aerostat |
| CN114894430A (en) * | 2022-07-13 | 2022-08-12 | 中国航空工业集团公司沈阳空气动力研究所 | Installation accuracy measurement method of wind tunnel honeycomb device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103264773B (en) | 2015-05-20 |
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