CN105466713A - Testing device for simulating plane anti-icing and de-icing system - Google Patents
Testing device for simulating plane anti-icing and de-icing system Download PDFInfo
- Publication number
- CN105466713A CN105466713A CN201510920741.6A CN201510920741A CN105466713A CN 105466713 A CN105466713 A CN 105466713A CN 201510920741 A CN201510920741 A CN 201510920741A CN 105466713 A CN105466713 A CN 105466713A
- Authority
- CN
- China
- Prior art keywords
- icing
- valve
- nozzle
- deicing
- multinomial
- 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
- G01M99/00—Subject matter not provided for in other groups of this subclass
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention discloses a testing device for simulating a plane anti-icing and de-icing system. The device relates to the technical field of prevention and removal of aircraft icing. The testing device for simulating the plane anti-icing and de-icing system comprises an atomization device, a mist spray droplet size analyzer (10), a low-temperature control compartment (11) and a testing part (13), wherein the low-temperature control compartment (11) is used to simulate an actual work environment temperature of the testing part (13); the testing part (13) is disposed in the low-temperature control compartment (11); the atomization device provides simulated liquid water drops for the testing part (13); and the mist spray droplet size analyzer (10) is disposed between the atomization device and the testing part (13) and used to detect the droplet size of the liquid water drops sprayed by the atomization device to the testing part (13). The device disclosed by the invention has the beneficial effects that a real working environment of the plane anti-icing and de-icing system is simulated; reliability of design of the anti-icing and de-icing system can be enhanced; and plane safety is improved.
Description
Technical field
The present invention relates to aircraft de-icing techniques field, be specifically related to a kind of simulated aircraft anti-icing and deicing STS system test set.
Background technology
When aircraft flies in containing the cloud layer of super-cooling waterdrop, many parts there will be icing phenomenon.Aircraft freezes and can destroy the aerodynamic configuration of aircraft, hinder the flowing of air, increase friction force and reduce lift, especially the ice on wing and empennage is larger on aircraft impact, this not only can make aircraft lifting resistance characteristic worsen, but also the flight safety of aircraft can be made to reduce, even cause the accident of fatal crass.
In order to ensure flight safety, most of airplane design anti-icing and deicing system.In order to anti-icing and deicing system and performance verification, before the Flight Test that danger is high, all ground experiment or examination can be carried out.Therefore, the invention provides one for simulated aircraft ground anti-icing and deicing STS system test set.
Summary of the invention
The object of this invention is to provide a kind of simulated aircraft anti-icing and deicing STS system test set, with the problem at least one place solved or existing at least alleviating in background technology.
Technical scheme of the present invention is: provide a kind of simulated aircraft anti-icing and deicing STS system test set, comprises between atomising device, granularity of spray analyser, low temperature control and testpieces, wherein, for the actual working environment temperature of simulation test piece between described low temperature control; Described testpieces is arranged in low temperature control; Described atomising device provides simulation liquid water droplets for testpieces; Described granularity of spray analyser is arranged between described atomising device and testpieces, for detecting the granule size of the liquid water droplets that atomising device sprays to testpieces.
Preferably, described atomising device comprises valve, reserve tank, gas-holder, heterogeneous nozzle, and wherein, described heterogeneous nozzle is provided with multiple, and heterogeneous nozzle is connected with air jet pipe and sparge pipe; The other end of described air jet pipe connects gas-holder, and the other end of described sparge pipe connects reserve tank, and gas-holder is connected with reserve tank by pipeline; Described valve is for controlling the break-make in specified tube section in atomising device.
Preferably, described atomising device also comprises air strainer, and described air strainer is arranged on the air jet pipe between gas-holder and heterogeneous nozzle.
Preferably, described atomising device also comprises liquid filter, and described liquid filter is arranged on the sparge pipe between reserve tank and heterogeneous nozzle.
Preferably, described atomising device also comprises well heater, air jet pipe between multinomial nozzle and gas-holder is connected by pipeline with the sparge pipe between multinomial nozzle and reserve tank, and pipeline is provided with valve, described well heater is arranged on the air jet pipe between gas-holder and pipeline, for having tested the dry multinomial nozzle of rear heated air.
Preferably, described valve comprises the first valve and the second valve, and the first valve and the second valve are autocontrol valve, the first valve and the second valve receive described granularity of spray analyser feedback signal and the opening of autocontrol valve.
Preferably, described testpieces is hot air anti-icing deicing system testpieces, electric anti-icing and deicing system test part or mechanical type deicing system testpieces.
Preferably, described multiple multinomial nozzle, can relatively independent work by Valve controlling.
Preferably, described reserve tank is provided with level indicator and automatic pressure reducing valve.
Beneficial effect of the present invention: the invention provides a kind of airplane antifreezing and deicing STS system test set, for the actual working environment temperature of simulation test piece between low temperature control; Testpieces is arranged in low temperature control; By atomising device for testpieces provides simulation liquid water droplets; Granularity of spray analyser can detect the granule size of the liquid water droplets that atomising device sprays to testpieces, the real simulation working environment of airplane antifreezing and deicing system, is conducive to the reliability improving anti-icing and deicing system, improves the security of aircraft.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of simulated aircraft anti-icing and deicing STS system test set of the present invention.
Wherein, 1-air strainer, 2-first valve, 3-well heater, 4-valve, the heterogeneous nozzle of 5-, 7-liquid filter, 8-reserve tank, 9-gas-holder, 10-granularity of spray analyser, between the low temperature control of 11-, 13-testpieces, 14-pipeline, 15-second valve, 16-valve, 17-valve, 18-valve.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
As shown in Figure 1, a kind of simulated aircraft anti-icing and deicing STS system test set, to comprise between atomising device, granularity of spray analyser 10, low temperature control 11 and testpieces 13, and wherein, between low temperature control, 11 for the actual working environment temperature of simulation test piece 13; Testpieces 13 to be arranged between low temperature control in 11; Atomising device provides simulation liquid water droplets for testpieces 13; Granularity of spray analyser 10 is arranged between described atomising device and testpieces 13, for detecting the granule size of the liquid water droplets that atomising device sprays to testpieces 13.
Simulated aircraft anti-icing and deicing STS system test set of the present invention, the real simulation working environment of airplane antifreezing and deicing system, is conducive to the reliability improving anti-icing and deicing system, improves the security of aircraft.
In the present embodiment, atomising device comprises valve, reserve tank 8, gas-holder 9, heterogeneous nozzle 5, and wherein, heterogeneous nozzle 5 is provided with multiple, and each heterogeneous nozzle 5 is all connected with air jet pipe and sparge pipe; The other end of air jet pipe connects gas-holder 9, and the other end of sparge pipe connects reserve tank 8, and gas-holder 9 is connected with reserve tank 8 by pipeline; Valve is for controlling the break-make in specified tube section in atomising device.
In the present embodiment, gas-holder 9 is connected with reserve tank 8 by pipeline, and its advantage is, when carrying out the atomization of liquid, just gas passes into reserve tank 8, is conducive to the atomization with moisture in reserve tank 8.
In the present embodiment, multinomial nozzle 5 is provided with 4, as shown in Figure 1, from according to display orientation in figure, be defined as the first multinomial nozzle, the second multinomial nozzle, the 3rd multinomial nozzle, the 4th multinomial nozzle from top to bottom successively.Wherein the draft tube of the second multinomial nozzle and the 3rd multinomial nozzle is an inlet manifold, and is subject to the control of valve 4, and valve 4 is opened, and the second multinomial nozzle and the 3rd multinomial nozzle have gas, and valve 4 is closed, and the second multinomial nozzle and the 3rd multinomial nozzle do not have gas; The feed tube of the second multinomial nozzle and the 3rd multinomial nozzle is a feed liquor house steward, and is subject to the control of valve 16, and valve 16 is opened, and the second multinomial nozzle and the 3rd multinomial nozzle have liquid, and valve 16 is closed, and the second multinomial nozzle and the 3rd multinomial nozzle do not have liquid.
The draft tube of the first multinomial nozzle and the 4th multinomial nozzle is an inlet manifold, and is subject to the control of valve 17, and valve 17 is opened, and the first multinomial nozzle and the 4th multinomial nozzle have gas, and valve 17 is closed, and the first multinomial nozzle and the 4th multinomial nozzle do not have gas; The feed tube of the first multinomial nozzle and the 4th multinomial nozzle is a feed liquor house steward, and is subject to the control of valve 18, and valve 18 is opened, and the first multinomial nozzle and the 4th multinomial nozzle have liquid, and valve 18 is closed, and the first multinomial nozzle and the 4th multinomial nozzle do not have liquid.
The draft tube of the second multinomial nozzle and the 3rd multinomial nozzle is set to an inlet manifold, feed tube is set to a feed liquor house steward, first multinomial nozzle and the 4th multinomial nozzle are set to an inlet manifold, the advantage that feed tube is set to a feed liquor house steward is: when the pilot region area of testpieces 13 is less, only can open the second multinomial nozzle and the 3rd multinomial nozzle, when the pilot region area of testpieces 13 is larger, can by the first multinomial nozzle, second multinomial nozzle, 3rd multinomial nozzle and the 4th multinomial nozzle are all opened, the spraying in large face is provided, the working environment that testpieces 13 is provided closer to actual condition, Appropriate application resource.
In the present embodiment, atomising device also comprises air strainer 1, and air strainer 1 is arranged on the air jet pipe between gas-holder 9 and heterogeneous nozzle 5.
As shown in Figure 1, in the present embodiment, air strainer 1 is arranged on the connecting line between gas-holder 9 and valve 2, and its advantage is, namely gas be out cleaned afterwards from gas-holder 9, protects test unit parts below, and is conducive to atomization.
In the present embodiment, atomising device also comprises liquid filter 7, and liquid filter 7 is arranged on the sparge pipe between reserve tank 8 and heterogeneous nozzle 5.
As shown in Figure 1, in the present embodiment, liquid filter 7 is arranged on the connecting line between reserve tank 8 and the second valve 15, and its advantage is, namely liquid be out cleaned afterwards from reserve tank 8, protects test unit parts below, and is conducive to atomization.
In the present embodiment, atomising device also comprises well heater 3, air jet pipe between multinomial nozzle 5 and gas-holder 9 is connected by pipeline 14 with the sparge pipe between multinomial nozzle 5 and reserve tank 8, and pipeline 14 is provided with valve, well heater 3 is arranged on the air jet pipe between gas-holder 9 and pipeline 14, for having tested the dry multinomial nozzle 5 of rear heated air.
As shown in Figure 1; in the present embodiment; well heater 3 is arranged between the first valve 2 and valve 4; one end that pipeline 14 connects gas piping is connected between well heater 3 and valve 4, and the advantage arranging well heater 3 is, after having tested; the gas of gas-holder 9 discharge can be heated by well heater 3; for pipeline and the multinomial nozzle of drying experiment unit, be conducive to protection test equipment, improve result of use and the serviceable life of equipment.The advantage arranging the second valve 15 is, when carrying out drying test equipment, closed by the second valve 15, hot-air can not enter reserve tank 8.
In the present embodiment, the first valve 2 and the second valve 15 are autocontrol valve, the first valve 2 and the second valve 15 receive described granularity of spray analyser 10 feedback signal and the opening of autocontrol valve, realize the adjustment to granularity of spray.
Be understandable that, testpieces 13 can be hot air anti-icing deicing system testpieces, electric anti-icing and deicing system test part or mechanical type deicing system testpieces.
In the present embodiment, multiple multinomial nozzle 5, can relatively independent work by Valve controlling.
In the present embodiment, reserve tank 8 is provided with level indicator and automatic pressure reducing valve.
For the ease of understanding specific embodiment of the invention process, for the present embodiment, now contrasting Fig. 1 and illustrating: the area needing to accept spray area according to testpieces 13, determining the number that multinomial nozzle 5 works.When only needing the second multinomial nozzle and the 3rd multinomial nozzle operation, valve 17 and valve 18 are closed, valve closing on pipeline 14, all the other valves are all opened, well heater 3 does not work, the openings of sizes of the signal autocontrol valve that the first valve 2 and the second valve 15 feed back according to granularity of spray analyser 10, to control the ratio of gas and liquid, realizes the adjustment to granularity of spray.
When the first multinomial nozzle, the second multinomial nozzle, the 3rd multinomial nozzle and the 4th multinomial nozzle need to work simultaneously, the valve closing on pipeline 14 has been gone out in this experimental provision, outside well heater 3 does not work, all the other valves are all opened, the openings of sizes of the signal autocontrol valve that the first valve 2 and the second valve 15 feed back according to granularity of spray analyser 10, to control the ratio of gas and liquid, realize the adjustment to granularity of spray.
After having tested, close the valve between gas-holder 9 and reserve tank 8, close the second valve 15, all the other valves are all opened, heater 3, and gas-holder 9 air feed, for drying test equipment.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (9)
1. a simulated aircraft anti-icing and deicing STS system test set, is characterized in that: comprise (11) and testpieces (13) between atomising device, granularity of spray analyser (10), low temperature control, wherein,
Between described low temperature control, (11) are for the actual working environment temperature of simulation test piece (13);
Described testpieces (13) to be arranged between low temperature control in (11);
Described atomising device is that testpieces (13) provides simulation liquid water droplets;
Described granularity of spray analyser (10) is arranged between described atomising device and testpieces (13), for detecting the granule size of the liquid water droplets that atomising device sprays to testpieces (13).
2. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 1, is characterized in that: described atomising device comprises valve, reserve tank (8), gas-holder (9), heterogeneous nozzle (5), wherein,
Described heterogeneous nozzle (5) is provided with multiple, and heterogeneous nozzle (5) is connected with air jet pipe and sparge pipe; The other end of described air jet pipe connects gas-holder (9), and the other end of described sparge pipe connects reserve tank (8), and gas-holder (9) is connected with reserve tank (8) by pipeline;
Described valve is for controlling the break-make in specified tube section in atomising device.
3. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 2, it is characterized in that: described atomising device also comprises air strainer (1), described air strainer (1) is arranged on the air jet pipe between gas-holder (9) and heterogeneous nozzle (5).
4. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 3, it is characterized in that: described atomising device also comprises liquid filter (7), described liquid filter (7) is arranged on the sparge pipe between reserve tank (8) and heterogeneous nozzle (5).
5. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 4, it is characterized in that: described atomising device also comprises well heater (3), air jet pipe between multinomial nozzle (5) and gas-holder (9) is connected by pipeline (14) with the sparge pipe between multinomial nozzle (5) and reserve tank (8), and pipeline (14) is provided with valve, described well heater (3) is arranged on the air jet pipe between gas-holder (9) and pipeline (14), for having tested the dry multinomial nozzle (5) of rear heated air.
6. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 5, it is characterized in that: described valve comprises the first valve (2) and the second valve (15), first valve (2) and the second valve (15) are autocontrol valve, and the first valve (2) and the second valve (15) receive the signal the opening of autocontrol valve that described granularity of spray analyser (10) feeds back.
7. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 6, is characterized in that: described testpieces (13) is hot air anti-icing deicing system testpieces, electric anti-icing and deicing system test part or mechanical type deicing system testpieces.
8. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 7, is characterized in that: described multiple multinomial nozzle (5), can relatively independent work by Valve controlling.
9. simulated aircraft anti-icing and deicing STS system test set as claimed in claim 8, is characterized in that: (8) are provided with level indicator and automatic pressure reducing valve with described reserve tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510920741.6A CN105466713A (en) | 2015-12-11 | 2015-12-11 | Testing device for simulating plane anti-icing and de-icing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510920741.6A CN105466713A (en) | 2015-12-11 | 2015-12-11 | Testing device for simulating plane anti-icing and de-icing system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105466713A true CN105466713A (en) | 2016-04-06 |
Family
ID=55604655
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510920741.6A Pending CN105466713A (en) | 2015-12-11 | 2015-12-11 | Testing device for simulating plane anti-icing and de-icing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105466713A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105797890A (en) * | 2016-05-06 | 2016-07-27 | 武汉航空仪表有限责任公司 | Spraying device for freezing simulation device |
| CN105836159A (en) * | 2016-05-18 | 2016-08-10 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft icing detector ground test method |
| CN106017858A (en) * | 2016-07-08 | 2016-10-12 | 中国民用航空总局第二研究所 | Air channel testing system for aerodynamic performance of fluid for deicing and preventing ice development |
| CN106081155A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft anti-deicing system test analog |
| CN106644363A (en) * | 2016-12-02 | 2017-05-10 | 武汉航空仪表有限责任公司 | Lab deicing testing method for air bag deicing system |
| CN107200147A (en) * | 2017-06-05 | 2017-09-26 | 中电科芜湖通用航空产业技术研究院有限公司 | Jelly cloud icing temperature control simulation laboratory suitable for middle-size and small-size aircraft |
| CN107745828A (en) * | 2017-11-28 | 2018-03-02 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of anti-deicing experiment air entraining device of hot gas |
| CN108508144A (en) * | 2018-03-12 | 2018-09-07 | 中国民用航空总局第二研究所 | A kind of experimental box movement spraying device |
| CN110589026A (en) * | 2019-10-10 | 2019-12-20 | 中国商用飞机有限责任公司 | Closed-loop aircraft electric anti-icing system ground test device |
| CN111957459A (en) * | 2020-06-29 | 2020-11-20 | 中国航发湖南动力机械研究所 | Engine rain absorption test device and test method thereof |
| CN113551865A (en) * | 2021-04-26 | 2021-10-26 | 南京航空航天大学 | Spraying system capable of removing residual water in pipeline |
| CN115780118A (en) * | 2023-02-08 | 2023-03-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Supercooled large-water-drop icing cloud and mist simulation nozzle device |
| CN117483131A (en) * | 2023-11-03 | 2024-02-02 | 哈尔滨理工大学 | Spraying system and method in controllable low-temperature environment |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001013043A (en) * | 1999-07-02 | 2001-01-19 | Nittetsu Elex Co Ltd | Constant temperature apparatus for test of device with heat generating property |
| CN101583870A (en) * | 2006-12-18 | 2009-11-18 | 空中客车法国公司 | Device and method for monitoring the particle contamination in flowing hydraulic fluids |
| 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 |
| CN102582843A (en) * | 2011-11-11 | 2012-07-18 | 中国商用飞机有限责任公司 | Ground icing condition simulation system |
| CN202453205U (en) * | 2011-11-28 | 2012-09-26 | 成都民航六维航化有限责任公司 | Low temperature anti-icing test box |
| CN203614126U (en) * | 2013-12-03 | 2014-05-28 | 淮南润成科技股份有限公司 | Air injection linkage type spraying device |
| CN104122063A (en) * | 2013-04-24 | 2014-10-29 | 武汉航空仪表有限责任公司 | Freezing weather chamber |
| CN204314045U (en) * | 2014-12-09 | 2015-05-06 | 杨文鑫 | A kind of small-sized reverse-flow type icing wind tunnel equipment |
-
2015
- 2015-12-11 CN CN201510920741.6A patent/CN105466713A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001013043A (en) * | 1999-07-02 | 2001-01-19 | Nittetsu Elex Co Ltd | Constant temperature apparatus for test of device with heat generating property |
| CN101583870A (en) * | 2006-12-18 | 2009-11-18 | 空中客车法国公司 | Device and method for monitoring the particle contamination in flowing hydraulic fluids |
| 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 |
| CN102582843A (en) * | 2011-11-11 | 2012-07-18 | 中国商用飞机有限责任公司 | Ground icing condition simulation system |
| CN202453205U (en) * | 2011-11-28 | 2012-09-26 | 成都民航六维航化有限责任公司 | Low temperature anti-icing test box |
| CN104122063A (en) * | 2013-04-24 | 2014-10-29 | 武汉航空仪表有限责任公司 | Freezing weather chamber |
| CN203614126U (en) * | 2013-12-03 | 2014-05-28 | 淮南润成科技股份有限公司 | Air injection linkage type spraying device |
| CN204314045U (en) * | 2014-12-09 | 2015-05-06 | 杨文鑫 | A kind of small-sized reverse-flow type icing wind tunnel equipment |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105797890B (en) * | 2016-05-06 | 2018-05-22 | 武汉航空仪表有限责任公司 | A kind of spraying device for icing simulation equipment |
| CN105797890A (en) * | 2016-05-06 | 2016-07-27 | 武汉航空仪表有限责任公司 | Spraying device for freezing simulation device |
| CN105836159A (en) * | 2016-05-18 | 2016-08-10 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft icing detector ground test method |
| CN106081155A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft anti-deicing system test analog |
| CN106017858A (en) * | 2016-07-08 | 2016-10-12 | 中国民用航空总局第二研究所 | Air channel testing system for aerodynamic performance of fluid for deicing and preventing ice development |
| CN106017858B (en) * | 2016-07-08 | 2018-08-14 | 中国民用航空总局第二研究所 | System is tested in a kind of air duct for ice-removing and ice-preventing liquid air aerodynamic properties |
| CN106644363A (en) * | 2016-12-02 | 2017-05-10 | 武汉航空仪表有限责任公司 | Lab deicing testing method for air bag deicing system |
| CN107200147A (en) * | 2017-06-05 | 2017-09-26 | 中电科芜湖通用航空产业技术研究院有限公司 | Jelly cloud icing temperature control simulation laboratory suitable for middle-size and small-size aircraft |
| CN107745828A (en) * | 2017-11-28 | 2018-03-02 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of anti-deicing experiment air entraining device of hot gas |
| CN108508144A (en) * | 2018-03-12 | 2018-09-07 | 中国民用航空总局第二研究所 | A kind of experimental box movement spraying device |
| CN110589026A (en) * | 2019-10-10 | 2019-12-20 | 中国商用飞机有限责任公司 | Closed-loop aircraft electric anti-icing system ground test device |
| CN111957459A (en) * | 2020-06-29 | 2020-11-20 | 中国航发湖南动力机械研究所 | Engine rain absorption test device and test method thereof |
| CN111957459B (en) * | 2020-06-29 | 2021-07-27 | 中国航发湖南动力机械研究所 | Engine rain absorption test device and test method thereof |
| CN113551865A (en) * | 2021-04-26 | 2021-10-26 | 南京航空航天大学 | Spraying system capable of removing residual water in pipeline |
| CN115780118A (en) * | 2023-02-08 | 2023-03-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Supercooled large-water-drop icing cloud and mist simulation nozzle device |
| CN117483131A (en) * | 2023-11-03 | 2024-02-02 | 哈尔滨理工大学 | Spraying system and method in controllable low-temperature environment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105466713A (en) | Testing device for simulating plane anti-icing and de-icing system | |
| CN203858089U (en) | Aircraft anti-icing system testing device | |
| CN204314045U (en) | A kind of small-sized reverse-flow type icing wind tunnel equipment | |
| US10717536B2 (en) | Fluid ice protection system flow conductivity sensor | |
| US10737792B2 (en) | Turbofan engine fluid ice protection delivery system | |
| CN203643124U (en) | Supercooling large water drop simulation device | |
| CN112798214B (en) | Testing device and testing method capable of controlling icing area | |
| CN110702419B (en) | Anti-icing conformance test system and method for engine air inlet system | |
| CN103048109A (en) | Wing type test piece for icing wind tunnel test of aircraft wing anti-icing system | |
| CN108058832B (en) | Combined type anti-icing liquid-air bag anti-icing and deicing system | |
| CN103434652A (en) | Method for forming and detecting supercooled water drops in ground icing condition simulation system and target simulation device | |
| CN204911938U (en) | Intelligence water -spraying system of filling station | |
| CN107200138A (en) | Icing signal detecting device | |
| CN216523420U (en) | Operation and maintenance system of oversized span inflatable airplane camouflage device | |
| CN209521886U (en) | Aircraft anti-icing arranges rain system experimental | |
| CN109720582A (en) | A kind of combined type electric heating-anti-deicing system of anti-freeze fluid | |
| De Bruin et al. | KAI Surion helicopter full-scale air intake testing at CIRA Icing Wind Tunnel | |
| CN110589026B (en) | Ground test device of closed-loop aircraft electric anti-icing system | |
| Liu et al. | Experimental research on blowing-rain intensity and uniformity of rain tunnel for aircraft rain removal testing | |
| CN114251979A (en) | Operation and maintenance system of oversized span inflatable airplane camouflage device | |
| CN210953884U (en) | Spray icing test system based on Bernoulli effect in low-temperature environment | |
| CN103776122B (en) | A kind of icing tunnel humidity control method and special humidification system thereof | |
| Zhang et al. | Research progress of aircraft icing hazard and ice wind tunnel test technology | |
| Lu et al. | Numerical simulation of rain accumulation on aircraft windshield | |
| CN117705862A (en) | Airborne high-altitude icing, freezing, rain and condensation test equipment 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 |
Application publication date: 20160406 |
|
| RJ01 | Rejection of invention patent application after publication |