CN107200138A - Icing signal detecting device - Google Patents
Icing signal detecting device Download PDFInfo
- Publication number
- CN107200138A CN107200138A CN201710389825.0A CN201710389825A CN107200138A CN 107200138 A CN107200138 A CN 107200138A CN 201710389825 A CN201710389825 A CN 201710389825A CN 107200138 A CN107200138 A CN 107200138A
- Authority
- CN
- China
- Prior art keywords
- air
- icing
- radome fairing
- velocity
- playpipe
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
Abstract
A kind of a kind of icing signal detecting device disclosed by the invention, it is desirable to provide simple in construction, icing detector of dependable performance, the technical scheme is that：Icing detection bar（3）Positioned at air inlet（4）Near, playpipe（2）Positioned at radome fairing（1）Contraction section, to playpipe（2）Bottom compression contracting air, air is from spout（6）Project at a high speed, the high-velocity jets of formation hit spout（6）Neighbouring static or velocity air, drives static or velocity air together from gas outlet（5）Accelerated discharge, after air discharge, is internally formed negative pressure, extraneous air is under pressure differential effect, from air inlet in radome fairing（5）Radome fairing is inhaled into, so as to be formed from air inlet（4）To gas outlet（5）One-way airflow.So that flowing through icing detection bar（3）Air velocity accelerate.Solve aircraft, the problem of particularly detection of helicopter low speed freezes difficult.
Description
Technical field
The present invention relates to a kind of sensor for detecting the body surface icing thickness such as aircraft, power transmission line, building, by freezing
Sensor can be converted to icing signal the electrical signal that can directly detect.Used on more particularly to a kind of low-speed operations device
Icing detector, more particularly in the icing detector used on helicopter.
Background technology
When aircraft flight, icing meteorology condition is often inevitably met with, so that before windshield, the tail wing
The key positions such as edge, propeller, engine inlets, pitot freeze.In airplane antifreezing and deicing technical elements, lifting airscrew
Anti-icing and deicing is a very unique field.Helicopter is in flight under the conditions of icing meteorology, and the super-cooling waterdrop in air can be fast
Speed is gathered in the rotor blade leading edge of rotation at a high speed and congealed into ice, and rotor blade, which freezes, to bring some to have a strong impact on, such as：
Change the aerodynamic configuration of rotor blade, so as to reduce the flying quality of helicopter, helicopter stall out of control is caused when serious, even
Crash.Change the Mass Distribution of rotor blade, influence the dynamics of rotor, cause rotor vibration increase, so that going straight up to
Machine is out of hand.Some ice cubes can come off from the rotor blade of high speed rotation, and the other parts damaged on helicopter, influence is straight
The flight safety of the machine of liter.Therefore, the influence frozen to the performance and efficiency of helicopter is very serious.Fly for fixed-wing
Machine, icing can not only cause flight vehicle aerodynamic penalty, and resistance increase, lift reduce, and primary control surface activity clamping stagnation causes to lose
Speed is out of control, and can make that engine power declines, windscreen visual field is unclear, relevant meter reading is inaccurate.Therefore, icing is directly affected
To the flight safety of aircraft.Overwhelming majority aircarrier aircraft uses icing detector and detects connection after ice-formation condition at present
The detection mode of anti-icing system.Icing detector is generally divided into direct viewing type and the major class of self-action two.Direct viewing type icing detector one
As be arranged on head in front of, windshield nearby etc. be relatively easy to observation region.Pilot manually connects after finding to freeze
Deicing system carries out deicing.Icing detector is Ji Nengxiang when detecting the thickness of icing to reach the minimum sensitivity of detector
Pilot sends icing signal, can carry out deicing with turn on automatically anti-icing system again.Conventional icing detector has vibrating type, pressure
Differential, radio isotope and optics icing detector etc..Vibrating type icing detector principle core component is ultrasonic wave axial direction
Concussion probe.Concussion probe is after icing, and frequency of oscillation can change, and using this principle, just can perceive whether aircraft is tied
Ice.Differential icing detector is also referred to as ram-air formula icing detector, and it utilizes the dynamic pressure for measuring windstream（Entirely
Pressure）With the difference of static pressure, to judge whether aircraft freezes.Optics icing detector is sentenced using the change of optical absorption intensity
It is disconnected whether to freeze.Radio isotope icing detector is then to utilize the β particles for arriving at counter after icing from radioactive source（Electricity
Son）The principle work of quantity reduction.Icing detector has temporal advanced to icing detection, so that with icing early warning
Function；System can also provide the different icing rates (icing intensity) at multiple icing positions, absolute icing thickness (icing degree)
Etc. information, make on icing conditions information specifically and comprehensively；System can also provide deicing effect information etc..In a word, it is
The detection and early warning that system freezes to aircraft are more timely, accurate and reliable, greatly promote what aircrew disposed to icing danger
Ability, strengthens aircraft icing safety protection level.Icing detector has a variety of, but classifies according to the position installed aboard,
Generally there are two classes：One class is to be stretched in outside icing detector outside airframe, the knot such as generally installed in a certain outside of head
Ice signalling means, and for visual icing detection rod of aircrew etc., this is referred to as first kind icing detector.Another kind of is peace
Loaded on the position that those easily freeze, such as wing, empennage leading edge, engine inlets, lifting airscrew etc., this is referred to as second
Class icing detector.Generally may require that this kind of icing signaller small volume, it is lightweight, and conformal installation can be flushed, to reduce knot
Influence of the ice signalling means to institute's installation position aerodynamic configuration.Due to the icing in the icing and airframe on icing detector it
Corresponding relation is extremely complex, it is difficult to the icing conditions from the icing supposition airframe on icing detector, therefore airframe
Whether those upper easy icing positions really freeze and how is icing conditions, and this kind of icing detector there is no method to determine.This is
The maximum defect of icing detector.
Due to the harmfulness that aircraft freezes, people do a lot of work at the anti-icing aspect of aircraft accumulated ice：On the one hand change
Enter the anti-icing equipment of aircraft, on the other hand strengthen the anti-icing of ground, deicing and check work.Even if but the anti-icing system of aircraft
System is fairly perfect, but deicing, anti-icing system can not be attained by Expected Results in all cases, and icing is still aircraft
One big hidden danger of flight.Accordingly, it would be desirable to be monitored to the ice condition of aircraft and early warning.Aircraft freezes generally using electricity
Hot de-icing techniques.The technology is to convert electrical energy into heat energy, and heater block treats protection coating, it is not frozen.Electricity
Thermal anti-icing system is general to be made up of power supply, selecting switch, overtemperature protection system, and electrical heating elements etc..Selecting switch has " hand
It is dynamic ", the position such as " automatic ", when positioned at " automatic " position, aircraft ice detector experiences icing electric signal, turn on automatically or breaks
Open system power supply.Overtemperature protection system includes Temperature probe and relay, is deformed for preventing part skin from overheating.
Electrical heating elements convert electrical energy into heat energy, to parts surface heating, deicing.The anti-icing mode of heating of electricity have laser heating and
Two kinds of interruption heating.General fixed wing aircraft uses laser heating mode, and lifting airscrew is then different, because it allows table
There is a small amount of icing in face, while rotor is rotatable parts, air-flow is driven when rotated, inherently there is cooling effect, therefore to rotor
Heating, power consumption ratio is much bigger to the heating of fixed wing aircraft part, therefore in order to economize on electricity, it is general to lifting airscrew using week
The mode of phase heating.At present, it is common to use icing detector be all shaft-like mostly, this icing detection bar is typically direct
Installed in aircraft surfaces, when the air-flow containing super-cooling waterdrop or ice crystal flows through icing detection bar, super-cooling waterdrop or ice crystal and knot
Ice detection bar hits, and icing detection bar is frozen, and realizes the monitoring to icing.But if the flying speed of aircraft is relatively low,
Because air is low with respect to the speed of feeler lever, so as to be hit on feeler lever, to form ice less and can not detect.Especially for helicopter,
Not only flying speed is slow, and more because it has the rotor constantly rotated, the downwash flow that rotor is produced is very mixed and disorderly, makes to flow through knot
The size and Orientation of the air-flow of ice detection bar all constantly changes, so that the ice shape of feeler lever is mixed and disorderly, has a strong impact on measurement essence
Degree.
The content of the invention
Present invention seek to address that during aircraft low-speed operations, icing detection bar less icy, and the spy that frozen on helicopter
At measuring staff air-flow it is mixed and disorderly caused by icing detection it is difficult the problem of there is provided one kind is simple in construction, the icing signal of dependable performance is visited
Device is surveyed, the air velocity of icing detection bar can be flowed through by improving, and makes airflow direction stable, feeler lever is more likely formed rule
Ice shape then.
The technical solution adopted for the present invention to solve the technical problems is, a kind of icing signal detecting device, including：Make gas
The radome fairing 1 for flowing steady flow, the playpipe 6 and icing detection bar 3 that connect firmly in radome fairing and eject high-velocity jets,
It is characterized in that：Radome fairing 1 is formed with air inlet 4 and the gas outlet 5 of connection outside atmosphere, and it is attached that icing detection bar 3 is located at air inlet 4
Closely, playpipe 2 is located at the contraction section of radome fairing 1, to the bottom compression contracting air of playpipe 2, and is projected at a high speed from spout 6, formation
The static or velocity air near spout 6 is hit in high-speed jet, drives static or velocity air together from the accelerated row in gas outlet 5
Go out, after air discharge, negative pressure is internally formed in radome fairing, extraneous air is inhaled into rectification under pressure differential effect from air inlet 5
Cover, and accelerate in contraction section, so as to form the one-way airflow from air inlet 4 to gas outlet 5.
The present invention has the advantages that.
It is simple in construction：The present invention connects firmly icing detection bar, playpipe in radome fairing, the air inlet and outlet of radome fairing
Mouth is connected with outside atmosphere, simple in construction.
Dependable performance：Playpipe is placed in the contraction section of radome fairing by the present invention, and high speed is projected from the spout of playpipe
Air-spray, under the drive of jet, the static or velocity air of surrounding is accelerated, and reaches outside atmosphere from gas outlet together,
So as to be internally formed negative pressure in radome fairing, outside air can be inhaled into radome fairing from air inlet, utilize the contraction of radome fairing
Section Lavalle principle, which is improved, flows through icing detection bar airflow direction identical air velocity.It is low so as to solve solution aircraft
The problem of speed flight and difficult helicopter icing detection.
Brief description of the drawings
Fig. 1 is the front view of icing signal detecting device of the present invention.
Fig. 2 is the left view of icing signal detecting device of the present invention.
Fig. 3 is Fig. 2 A-A to sectional view.
Fig. 4 is Fig. 2 B-B direction sectional view.
In figure：1 radome fairing, 2 playpipes, 3 icing detection bars, 4 air inlets, 5 gas outlets, 6 spouts.
Embodiment
Refering to Fig. 1-Fig. 4, in embodiment described below, a kind of icing signal detecting device, including：Make steady air current
The radome fairing 1 of flowing, the playpipe 6 for connecting firmly in radome fairing and ejecting high-velocity jets and icing detection bar 3, its feature
It is：Radome fairing 1 is formed with air inlet 4 and the gas outlet 5 of connection outside atmosphere, and icing detection bar 3 is located near air inlet 4, spray
Pipe 2 is penetrated positioned at the contraction section of radome fairing 1, compressed air is projected at a high speed by the bottom of playpipe 2, and from spout 6, the high rapid fire of formation
Stream hits the static or velocity air near spout 6, drives static or velocity air together from the accelerated discharge in gas outlet 5, empty
After gas discharge, negative pressure is internally formed in radome fairing, extraneous air is inhaled into radome fairing under pressure differential effect from air inlet 5, and
Accelerate in contraction section, so as to form the one-way airflow from air inlet 4 to gas outlet 5.
Claims (1)
1. a kind of icing signal detecting device, including：The radome fairing for flowing steady air current（1）, connect firmly in radome fairing and spray
Project the playpipe of high-velocity jets（6）With icing detection bar（3）, it is characterised in that：Icing detection bar（3）Positioned at air inlet
（4）Near, playpipe（2）Positioned at radome fairing（1）Contraction section, to playpipe（2）Bottom compression contracting air, air is from spout（6）
Project at a high speed, the high-velocity jets of formation hit spout（6）Neighbouring static or velocity air, drives static or velocity air
Together from gas outlet（5）Accelerated discharge, after air discharge, negative pressure is internally formed in radome fairing, extraneous air is made in pressure differential
Under, from air inlet（5）Radome fairing is inhaled into, so as to be formed from air inlet（4）To gas outlet（5）One-way airflow, make
The air velocity that icing detection bar must be flowed through is accelerated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710389825.0A CN107200138A (en) | 2017-05-27 | 2017-05-27 | Icing signal detecting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710389825.0A CN107200138A (en) | 2017-05-27 | 2017-05-27 | Icing signal detecting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107200138A true CN107200138A (en) | 2017-09-26 |
Family
ID=59906310
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710389825.0A Pending CN107200138A (en) | 2017-05-27 | 2017-05-27 | Icing signal detecting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107200138A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466779A (en) * | 2019-08-20 | 2019-11-19 | 中国商用飞机有限责任公司 | A kind of ice crystal detector |
| CN112572809A (en) * | 2020-12-17 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Hybrid icing detection method suitable for unmanned aerial vehicle platform |
| CN114162331A (en) * | 2022-02-14 | 2022-03-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing detection device and icing detection method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3940622A (en) * | 1972-10-23 | 1976-02-24 | Canadian Patents & Development Limited | Icing detector |
| WO2005020175A1 (en) * | 2003-08-20 | 2005-03-03 | The Boeing Company | Methods and systems for detecting icing conditions |
| CN205256681U (en) * | 2015-08-31 | 2016-05-25 | 中国商用飞机有限责任公司 | Ice -formation condition detection system and aircraft that has this system |
| CN106081123A (en) * | 2016-06-20 | 2016-11-09 | 华中科技大学 | A kind of ice crystal detector probe and include the complicated ice formation condition detector of this probe |
| CN205940856U (en) * | 2016-06-26 | 2017-02-08 | 成都凯天电子股份有限公司 | Pick -up is always pressed in steam deicing |
| CN207433810U (en) * | 2017-05-27 | 2018-06-01 | 成都凯天电子股份有限公司 | Icing detector |
-
2017
- 2017-05-27 CN CN201710389825.0A patent/CN107200138A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3940622A (en) * | 1972-10-23 | 1976-02-24 | Canadian Patents & Development Limited | Icing detector |
| WO2005020175A1 (en) * | 2003-08-20 | 2005-03-03 | The Boeing Company | Methods and systems for detecting icing conditions |
| CN1820289A (en) * | 2003-08-20 | 2006-08-16 | 波音公司 | Methods and systems for detecting icing conditions |
| CN205256681U (en) * | 2015-08-31 | 2016-05-25 | 中国商用飞机有限责任公司 | Ice -formation condition detection system and aircraft that has this system |
| CN106081123A (en) * | 2016-06-20 | 2016-11-09 | 华中科技大学 | A kind of ice crystal detector probe and include the complicated ice formation condition detector of this probe |
| CN205940856U (en) * | 2016-06-26 | 2017-02-08 | 成都凯天电子股份有限公司 | Pick -up is always pressed in steam deicing |
| CN207433810U (en) * | 2017-05-27 | 2018-06-01 | 成都凯天电子股份有限公司 | Icing detector |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466779A (en) * | 2019-08-20 | 2019-11-19 | 中国商用飞机有限责任公司 | A kind of ice crystal detector |
| CN110466779B (en) * | 2019-08-20 | 2023-02-21 | 中国商用飞机有限责任公司 | Ice crystal detector |
| CN112572809A (en) * | 2020-12-17 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Hybrid icing detection method suitable for unmanned aerial vehicle platform |
| CN114162331A (en) * | 2022-02-14 | 2022-03-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing detection device and icing detection method |
| CN114162331B (en) * | 2022-02-14 | 2022-04-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing detection device and icing detection method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10717536B2 (en) | Fluid ice protection system flow conductivity sensor | |
| CN102336272B (en) | Icing detector probe and icing detector comprising same | |
| US3940622A (en) | Icing detector | |
| EP1396425A1 (en) | Large spectrum icing conditions detector | |
| US9352841B2 (en) | Virtual ice accretion meter display | |
| CN107132278B (en) | Multi-cylinder array icing detection method | |
| CN106081123B (en) | Ice crystal detector probe and complex icing condition detector comprising same | |
| CN107200138A (en) | Icing signal detecting device | |
| US20110147526A1 (en) | Aircraft | |
| CN208053657U (en) | A kind of icing signal sensor for medium-and-large-sized fixed-wing unmanned plane | |
| CN206876374U (en) | A kind of super-cooling waterdrop ice detection | |
| Wallisch et al. | UAV icing: experimental investigation of ice shedding times with an electrothermal de-icing system | |
| Al-Khalil et al. | Mixed phase icing simulation and testing at the cox icing wind tunnel | |
| CN110466779B (en) | Ice crystal detector | |
| CN209972788U (en) | Supercooled water drop icing detector and mixed icing detector | |
| Jackson et al. | Ice detection systems: a historical perspective | |
| CN207433810U (en) | Icing detector | |
| CN110077601A (en) | Super-cooling waterdrop icing detector and mixed state icing detector | |
| Oleskiw | A review of 65 years of aircraft in-flight icing research at NRC | |
| van't Hoff et al. | Icing certification of korean utility helicopter KUH-1: artificial icing flight test | |
| CN113044224A (en) | Aircraft anti-icing method and system | |
| CN110466778B (en) | Icing detector | |
| Mingione et al. | Flight in icing conditions | |
| Pellicano et al. | Residual and inter-cycle ice for lower-speed aircraft with pneumatic boots | |
| Wu et al. | Effect of and protection from ice accretion on aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |