CN104648676A - Novel icing signal sensor - Google Patents
Novel icing signal sensor Download PDFInfo
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- CN104648676A CN104648676A CN201310607089.3A CN201310607089A CN104648676A CN 104648676 A CN104648676 A CN 104648676A CN 201310607089 A CN201310607089 A CN 201310607089A CN 104648676 A CN104648676 A CN 104648676A
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- bellows
- dynamic pressure
- plenum chamber
- pressure chamber
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Abstract
The invention belongs to the technical field of aviation, and relates to a novel icing signal sensor. The novel icing signal sensor comprises a socket, a contact point, a static pressure chamber, a diaphragm capsule, a dynamic pressure chamber, a static pressure hole, a pipe end heater, air inlets, a power source, an elbow shell and a signal lamp, wherein the air inlets are formed in the head portion of the novel icing signal sensor, and communicated with the dynamic pressure chamber, and the dynamic pressure chamber bears the total pressure of airflow flowing through the air inlets; the static pressure hole is formed in the side of the sensor, and communicated with the static pressure chamber, and the static pressure chamber bears the static pressure of airflow flowing through the static pressure hole; the pipe end heater is arranged behind the air inlets, and heat of the pipe end heater can be transmitted to the air inlets through heat conduction and can conduct heating de-icing operation on the air inlets; the diaphragm capsule is an electric conductor, stretching and withdrawal of the diaphragm capsule are automatically adjusted through the difference of pressure, inside and outside the diaphragm capsule, of the static pressure chamber and the dynamic pressure chamber, the diaphragm capsule and the contact point are connected and disconnected to control energization and de-energization of the signal lamp and the pipe end heater, and when a circuit is connected, the air inlets are heated to remove ice through the pipe end heater.
Description
Technical field
The invention belongs to technical field of aerospace, relate to a kind of novel ice signal transducer.
Background technology
Traditional pneumatic type ice-sensor in order t o cannot by blocking and the dust blocking differentiation of freezing, and when dust blocking induction opening, signal lamp is also always bright, causes traditional ice-sensor in order t o false alarm rate high, in the urgent need to carrying out adaptive improvement to it.
The object of the invention is: provide that a kind of structure is simple, reliable operation, easy to maintenance, without the need to manual intervention, ice-sensor in order t o that false alarm rate is low.
Technical scheme of the present invention is: a kind of novel ice signal transducer, it comprises socket 1, contact point 2, plenum chamber 3, bellows 4, dynamic pressure room 5, static aperture 6, tube head temperature booster 7, induction opening 8, power supply 9, bending tube shell 10 and signal lamp 11, wherein, induction opening 8 is arranged on the head of sensor, be communicated with dynamic pressure room 5, the air-flow stagnation pressure that induction opening 8 flows into is born in dynamic pressure room 5, static aperture 6 is arranged on the side of sensor, be communicated with plenum chamber 3, plenum chamber 3 bears the air-flow static pressure that static aperture 6 flows into, induction opening 8 rear portion is provided with tube head temperature booster 7, bellows 4 is electric conductor, the flexible of automatic adjustable bellows 4 is carried out by plenum chamber inside and outside bellows 43 and the pressure reduction on both sides, dynamic pressure room 5, by contact and the power on/off disconnecting control signal lamp 11 and tube head temperature booster 7 of bellows 4 and contact point 2, when after circuit ON, tube head temperature booster 7 is utilized to heat deicing to induction opening 8.
During engine operation, when dynamic pressure room 5 internal pressure is less than or equal to plenum chamber 3 internal pressure, end face and the contact point 2 of bellows 4 are in closure state, and when dynamic pressure room 5 internal pressure is greater than plenum chamber 3 internal pressure, end face and the contact point 2 of bellows 4 are in off-state.
The advantageous effect that the present invention has: icing blocking combines with electrical heating deicing by this novel ice signal transducer, utilize the periodicity of signal lamp 11 glittering predict icing, and utilize the always bright unforeseen circumstances (as induction opening 8 is blocked by dust) of predicting of signal lamp 11, compared with traditional ice-sensor in order t o, greatly can reduce the generation of false alarm rate.And whole process is without the need to manual intervention, reliable operation, easy to maintenance, structure is simple, has larger actual application value.
Accompanying drawing explanation
Fig. 1 is the structural representation of this novel ice signal transducer.
Wherein: socket 1; Contact point 2; Plenum chamber 3; Bellows 4; Dynamic pressure room 5; Static aperture 6; Tube head temperature booster 7; Induction opening 8; Power supply 9; Bending tube shell 10; Signal lamp 11.
Detailed description of the invention
Below in conjunction with concrete accompanying drawing, the invention will be further described.
Refer to Fig. 1, it is the structural representation of this novel ice signal transducer.This novel ice signal transducer comprises socket 1, contact point 2, plenum chamber 3, bellows 4, dynamic pressure room 5, static aperture 6, tube head temperature booster 7, induction opening 8, power supply 9, bending tube shell 10 and signal lamp 11, wherein, induction opening 8 is arranged on the head of sensor, be communicated with dynamic pressure room 5, the air-flow stagnation pressure that induction opening 8 flows into is born in dynamic pressure room 5, static aperture 6 is arranged on the side of sensor, be communicated with plenum chamber 3, plenum chamber 3 bears the air-flow static pressure that static aperture 6 flows into, induction opening 8 rear portion is provided with tube head temperature booster 7, its heat is passed to induction opening 8 by heat transfer and can to its deicing of heating, bellows 4 is electric conductor, during engine operation, when dynamic pressure room 5 internal pressure is less than or equal to plenum chamber 3 internal pressure, end face and the contact point 2 of bellows 4 are in closure state, when dynamic pressure room 5 internal pressure is greater than plenum chamber 3 internal pressure, end face and the contact point 2 of bellows 4 are in off-state.
The principle of work of this novel ice signal transducer is as follows:
The flexible of automatic adjustable bellows 4 is carried out by plenum chamber inside and outside bellows 43 and the pressure reduction on both sides, dynamic pressure room 5; By contact and the power on/off disconnecting control signal lamp 11 and tube head temperature booster 7 of bellows 4 and contact point 2; When after circuit ON, tube head temperature booster 7 is utilized to heat deicing to induction opening 8.
Practical work process is as follows:
When the engine is not in operation, do not have air-flow punching press effect, between dynamic pressure room 5 and plenum chamber 3, pressure reduction is 0, and contact point 2 closes, and because power supply 9 is not energized, signal lamp 11 goes out; When the engine operates, the air-flow stagnation pressure that induction opening 8 flows into is born in dynamic pressure room 5, and plenum chamber 3 bears the air-flow static pressure that static aperture 6 flows into, because dynamic pressure room 5 internal pressure is greater than plenum chamber 3 internal pressure, bellows 4 is compressed, and contact point 2 disconnects, though now power supply 9 is energized, signal lamp 11 goes out; Icing when meeting with in-flight, head induction opening 8 is blocked by ice, air-flow can not enter dynamic pressure room 5, because dynamic pressure room 5 internal pressure is less than plenum chamber 3 internal pressure, bellows 4 returns to initial position, and contact point 2 closes, now power supply 9 is energized, engagement light 11, meanwhile, the circuit connecting tube head temperature booster 7 is heated to induction opening 8; When heating to the ice-out on induction opening 8, induction opening 8 is opened, and air-flow enters again dynamic pressure room 5, and because dynamic pressure room 5 internal pressure is greater than plenum chamber 3 internal pressure, bellows 4 is compressed, and contact point 2 disconnects, and signal lamp 11 goes out, and stops heating of tube head temperature booster 7 simultaneously; If aircraft still flies under ice-formation condition, induction opening 8 will be plugged again; When aircraft flies under ice-formation condition, signal lamp 11 will be periodically glittering; When induction opening 8 is blocked by dust, signal lamp 11 keeps bright (false-alarm) always.
Claims (2)
1. a novel ice signal transducer, it is characterized in that, it comprises socket (1), contact point (2), plenum chamber (3), bellows (4), dynamic pressure room (5), static aperture (6), tube head temperature booster (7), induction opening (8), power supply (9), bending tube shell (10) and signal lamp (11), wherein, induction opening (8) is arranged on the head of sensor, be communicated with dynamic pressure room (5), the air-flow stagnation pressure that induction opening (8) flows into is born in dynamic pressure room (5), static aperture (6) is arranged on the side of sensor, be communicated with plenum chamber (3), plenum chamber (3) bears the air-flow static pressure that static aperture (6) flows into, induction opening (8) rear portion is provided with tube head temperature booster (7), bellows (4) is electric conductor, the flexible of automatic adjustable bellows (4) is carried out with the pressure reduction on dynamic pressure room (5) both sides by the inside and outside plenum chamber (3) of bellows (4), by contact and the power on/off disconnecting control signal lamp (11) and tube head temperature booster (7) of bellows (4) and contact point (2), when after circuit ON, tube head temperature booster (7) is utilized to heat deicing to induction opening (8).
2. a kind of novel ice signal transducer as claimed in claim 1, it is characterized in that, during engine operation, when dynamic pressure room (5) internal pressure is less than or equal to plenum chamber (3) internal pressure, end face and the contact point (2) of bellows (4) are in closure state, when dynamic pressure room (5) internal pressure is greater than plenum chamber (3) internal pressure, end face and the contact point (2) of bellows (4) are in off-state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310607089.3A CN104648676B (en) | 2013-11-22 | 2013-11-22 | Icing signal sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310607089.3A CN104648676B (en) | 2013-11-22 | 2013-11-22 | Icing signal sensor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104648676A true CN104648676A (en) | 2015-05-27 |
| CN104648676B CN104648676B (en) | 2017-02-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310607089.3A Active CN104648676B (en) | 2013-11-22 | 2013-11-22 | Icing signal sensor |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105863845A (en) * | 2016-06-07 | 2016-08-17 | 中国南方航空工业(集团)有限公司 | Icing indicating system |
| CN106005431A (en) * | 2016-06-24 | 2016-10-12 | 北京航空航天大学 | Icing-preventing and deicing device for jetting type helicopter rotor |
| CN107499520A (en) * | 2017-07-13 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of icing detector |
| CN107966216A (en) * | 2017-10-27 | 2018-04-27 | 中国航发南方工业有限公司 | A kind of freezing sensor |
| CN108357683A (en) * | 2017-12-29 | 2018-08-03 | 西北工业大学 | A kind of small drone icing detection method based on pitot |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1398085A (en) * | 1971-06-23 | 1975-06-18 | Kendall H M | Sensor for carburettor icing |
| US4095456A (en) * | 1975-06-04 | 1978-06-20 | Lucas Industries Limited | Apparatus for indicating rate of ice accretion |
| US5585551A (en) * | 1993-12-09 | 1996-12-17 | Labko Ice Detection Oy | Method for identification of different states of water, and sensor arrangement for use in the method |
| CN1673035A (en) * | 2003-11-18 | 2005-09-28 | 奥谢陶尔公司 | Ice detection assembly installed on an aircraft |
| CN1820289A (en) * | 2003-08-20 | 2006-08-16 | 波音公司 | Methods and systems for detecting icing conditions |
-
2013
- 2013-11-22 CN CN201310607089.3A patent/CN104648676B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1398085A (en) * | 1971-06-23 | 1975-06-18 | Kendall H M | Sensor for carburettor icing |
| US4095456A (en) * | 1975-06-04 | 1978-06-20 | Lucas Industries Limited | Apparatus for indicating rate of ice accretion |
| US5585551A (en) * | 1993-12-09 | 1996-12-17 | Labko Ice Detection Oy | Method for identification of different states of water, and sensor arrangement for use in the method |
| CN1820289A (en) * | 2003-08-20 | 2006-08-16 | 波音公司 | Methods and systems for detecting icing conditions |
| CN1673035A (en) * | 2003-11-18 | 2005-09-28 | 奥谢陶尔公司 | Ice detection assembly installed on an aircraft |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105863845A (en) * | 2016-06-07 | 2016-08-17 | 中国南方航空工业(集团)有限公司 | Icing indicating system |
| CN105863845B (en) * | 2016-06-07 | 2017-12-15 | 中国南方航空工业(集团)有限公司 | Icing instruction system |
| CN106005431A (en) * | 2016-06-24 | 2016-10-12 | 北京航空航天大学 | Icing-preventing and deicing device for jetting type helicopter rotor |
| CN106005431B (en) * | 2016-06-24 | 2018-04-13 | 北京航空航天大学 | A kind of injecting type lifting airscrew prevents/deicer |
| CN107499520A (en) * | 2017-07-13 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of icing detector |
| CN107966216A (en) * | 2017-10-27 | 2018-04-27 | 中国航发南方工业有限公司 | A kind of freezing sensor |
| CN108357683A (en) * | 2017-12-29 | 2018-08-03 | 西北工业大学 | A kind of small drone icing detection method based on pitot |
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| Publication number | Publication date |
|---|---|
| CN104648676B (en) | 2017-02-22 |
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