CN105882979B - The anti-icing equipment of aircraft blade - Google Patents
The anti-icing equipment of aircraft blade Download PDFInfo
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- CN105882979B CN105882979B CN201510175391.5A CN201510175391A CN105882979B CN 105882979 B CN105882979 B CN 105882979B CN 201510175391 A CN201510175391 A CN 201510175391A CN 105882979 B CN105882979 B CN 105882979B
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Abstract
The present invention relates to a kind of anti-icing equipment (1), assemble the rotor (51 of rotary aircraft (50), 52) blade (53,54), the blade (53,54) there is intrados (22), extrados (23) and leading edge (21) and second end (25), except defrosting system (3) is positioned at the position of the leading edge (21).The anti-icing equipment (1) has the emissions groove (10) being longitudinal positioning of on each intrados (22) and extrados (23), which just in the downstream except defrosting system (3) and opens at the position of the second end (25).The emissions groove (10) also is able to water of the discharge flow on the intrados (22) and extrados (23) of the air force component (2).
Description
Technical field
Present invention relates generally to the technical fields more particularly to rotary wind type of the air force component defrosting to aircraft
The blade of aircraft.
The present invention relates to the defroster for aircraft blade, using as the supplement except defrosting system.
Background technology
It is known on the outer surface of aircraft, especially in the air force component of the blade of such as wing or rotor etc
The formation and accumulation of frost or ice in leading edge can adversely affect the operation of the aircraft.In fact, the presence of frost or ice can
Quickly and significantly change the aerodynamic characteristics of the outer surface.Especially in leaf of the outer surface for the main rotor of rotary aircraft
During piece, the presence of frost or ice can cause hydraulic performance decline, even result in the aircraft accident occur.
The known front edge area for limiting or even going to defrost or the Defrost method of ice is heating air force component.It should
Heating can make up-front temperature increase to over the temperature for advantageously forming frost.That is electric defrosting system, heat is usually by electric current
Supply.Therefore this frost and/or ice that can be removed except defrosting system on air force component.In next detailed description,
It only refers to and defrosting, term " frost " can be replaced by term " ice ".
In the presence of the different electric defrosting systems technologies of heating air force component front edge area.Such as known electric defrosting system
System, which has to be covered, is located in the leading edge of air force component and heats the up-front resistor.
Moreover, removing defrosting system there are some, wherein heat is generated by magnetic strength phenomenon, to heat in air force component
Leading edge locus at position one or more metal parts.
But such system consumption much electricity, especially turn in the lift master of such as aircraft wing or rotary aircraft
In the case of the big span air force component of the blade of son etc.Therefore it is more difficult even not continue to for such air
Such electric defrosting system power supply of dynamic component, the electric energy to be supplied are very big.
It is feasible to the power supply of such electric defrosting systems stay however, for small span air force component.In the feelings
Under condition, the leading edge of these air force components is heated continuously.So as to which frost will not be formed, but it is possible that water in leading edge
Drop even moisture film.It is exactly " anti-defrosting system ".Such anti-defrosting system turns after being used for example in the twisting resistance of rotary aircraft
On the blade of son.
In order to limit the electrical energy demands of electric defrosting system to be used for, it will usually will be divided into except defrosting system according to sky
Multiple longitudinal tape of the span positioning of aerodynamic force component and/or the multiple transverse belts for being divided into the side string positioning according to the component.
It alternately powers in a periodic manner to these different bands, so as to heat the up-front different zones of the air force component successively.
These electric defrosting systems can make frost be deposited on partly and temporarily air force between each heating cycle
In the up-front some regions of component.Although the local deposits of frost can temporarily change the efficiency of air force component, especially
It can demand of the limitation to electric energy.
Such electric defrosting system is generally used to protect the lift main rotor of rotary aircraft with frost prevention.
In fact, in the case where frost occurs in the leading edge of blade, the heat generated by each band of electric defrosting system draws
It rises and locally occurs thin water film between leading edge and frost.Then, the centrifugal force mainly generated by the rotation of blade acts on projecting
Remaining frost.
Additionally, it is known that file FR 1554838 describes a kind of electrical switching apparatus, for by the period and it is scheduled in a manner of pair
The different band power supply being located in the leading edge of the blade of the main rotor of rotary aircraft, the electrical switching apparatus form the main rotor
Electric defrosting system.
Moreover, file FR2354242 describe it is a kind of except defrosting system, for the blade of the main rotor of rotary aircraft,
The leading edge of the aircraft is detachable.Therefore it is easily changed the leading edge and then changes in the defrosting system failure or in the case of safeguarding
Becoming should be except defrosting system.Equally, leading edge can be made to assemble or not assemble except defrosting system according to the flight environment of vehicle that aircraft is encountered.
It it is known that file US5322246 describes the loading end of such as aircraft wing etc, which, which has, is positioned
Stepping in the loading end face overall length.The stepping is positioned in anti-defrosting system or the downstream except defrosting system.The stepping makes flowing
The boundary layer for moving the air on loading end is vortexed.The stepping also is able in frost prevention or is being held except the downstream of defrosting system will flow
Water on section is converted to the water droplet then discharged by the boundary layer of the air, so as to avoid the occurrence of frost or ice.
File DE709354 is then described using the hot-air flowed between the main body of loading end and its leading edge with resistance
The component of the formation of stagnant ice.It is empty that the guiding piece presented in the main body of the loading end can supply heat to the overall length of the loading end
Gas, the hole that leading edge downstream is presented on aerofoil can discharge the hot-air.
Another technology is intended to abolish the frost formed at leaf position.For example, pneumatic system can be to being located at air force
The coating member inflation of rubber material at the leading edge locus of component.The type except defrosting system more for such as aircraft wing or
The fixation air force component of the empennage of rotary wing aircraft or aircraft etc.However, such system is had also been assembled such as file
The blade of the described rotary aircrafts of FR2545785.
In addition, also there are other less universal methods, such as using ultrasonic wave or anti-icing fluid.
Invention content
It is an object of the invention to improve electric defrosting system, showed with eliminating the icing for declining such defrosting system effectiveness
As.
In fact, if electric defrosting system, which can effectively remove, is formed in what is formed at the leading edge locus of air force component
Frost, then the icing phenomenon commonly generated at the defrosting system downstream, that is, being placed exactly in composition, this removes defrosting system most
The rear of the latter band.
The use of term " downstream " and " upstream " is according to from the leading edge of air force component to the direction of rear.As a result,
It is located at the up-front upstream the phenomenon that front of leading edge generates.Conversely, the phenomenon that resulting from leading edge rear portion is located at leading edge downstream.
Icing phenomenon is actually the result of electric defrosting system effectiveness.Water droplet or moisture film at leading edge locus
Can on air force component from upstream flow downstream.This flow through may wherein project frost be heated band and not
Experience is taken at these to hinder.
Conversely, when the flow is when taking of not yet being heated encounters frost, aqueous fusion is in frost so as to extremely fast thicken frost layer.
In fact, the water droplet for forming the flow has temperature slightly above freezing, these water droplets are to pass through frost under the action of except defrosting system
Thawing formed.Next, these water droplets are in contact with the band not yet heated and cool down again, frost until transformation or
Ice.But it is temporary to cause the hydraulic performance decline of air force component by frost, once the band is powered again, frost will disappear
It loses.
Equally, the water of the flow and cold surface --- i.e. in the downstream of electric defrosting system --- can be extremely fast when being in contact
It freezes.The icing barrier being made of frost and/or ice is then formed in the downstream of electric defrosting system.Although electric defrosting system is deposited
It is being effective, but the icing barrier forms until the electric defrosting system tail portion of air force component and can significantly decrease sky
The aerodynamic quality of aerodynamic force component.
The weather conditions that are encountered according to aircraft and except defrosting system the thermal efficiency and mainly according to the environment of aircraft
Temperature and moisture content, the water flowed on air force component can change.If weather conditions are moist or aircraft for example across
Cloud, then the water may be larger, and water film can cover the leading edge of the air force component., whereas if weather conditions are more dry
It is dry, then the water can be limited to the form of several drops of dripping.It is apparent that if weather conditions are advantageous, then the water can be zero.
Center of the extrados of air force component for the strong secondary depression region at leading edge locus, followed downstream by the region
Be strong " recompression " region first, followed by the recompression region of moderate.The extrados is usually by the upper of air force component
Surface is formed.The presence of the icing barrier can be acceptable in some finite region in leading edge downstream, the icing barrier
There is moderate influence to the aerodynamic efficiency of air force component, the influence is identical there are barrier on the extrados.
There are the icing barriers in the finite region mainly to produce form drag, also referred to as profile drag.
However, inside or outside the finite region, the deterioration of the pressure distribution of the pumping and layer can be generated, and is generated therewith
The loss of the aerodynamic lift of air force component or air flow restriction layer relative to air force component disengaging, therewith
Greatly increase its aerodynamic resistance.
In fact, according to aerodynamic profile, side string on extrados, at up-front downstream 3% and 15% it
Between first area generation air force component most of lift.Therefore, the first area is preferably by usually extending to this
Defrosting system protection except first area is to avoid white formation.
In addition, that in the second area of side string 30%, should be avoided to sky on the extrados, at leading edge downstream
Gas limiting layer causes all additional interferences that the limiting layer is detached from, and the air limiting layer is extremely required to be located at the second area
Upstream.
There is aforementioned recompression region between first area and the second area, wherein air limiting layer is burbulent
Gushing and can most resist interference, this interference has moderate influence to the efficiency of the air motivation of air force component.
(intrados is the center in superpressure area and usually by the air force component on the intrados of air force component
Inner surface formed), icing barrier can partly hinder in the superpressure area be mainly stratiform air flow restriction floor.Inside
Thus the presence of icing barrier in cambered surface causes at least partially to stop the stratiform air limiting layer on intrados, so as to
Cause local secondary depression and make the stratiform limiting layer built on the sand, thus increase the resistance aerodynamic effect generated by the intrados
Power.
Therefore focus on limiting the presence of the icing barrier, to avoid the air force of air force component is significantly reduced
Efficiency, the aerodynamic efficiency especially on the intrados of the air force component.
The purpose of the present invention is to provide a kind of device, the device can limit even eliminate on air force component,
The formation of icing barrier especially on each blade of the rotor of rotary aircraft.
According to the present invention, anti-icing equipment is used for air force component, which has along the air force
Intrados that the second end of the span of component from first end to the air force component of the air force component is longitudinally extended and
Extrados.The air force component also has leading edge and rear.Leading edge is longitudinally extended along the span of the air force component, and
Couple the intrados and extrados in the upstream along the side string of the air force component of the air motivation component.The rear edge
The take offence span of component of the air is longitudinally extended, and the downstream of the side string along the air force component in the air force component
Couple intrados and extrados in area.In fact, the air force component is lateral along the side string of the air force component from leading edge
Extend to rear.The air force component, which is equipped with to be located at its leading edge locus, removes defrosting system.
The notable feature of the anti-icing equipment is that it has and is suitable in each intrados and the extrados upper edge air force
The emissions groove that the span of component is longitudinally extended.Each emissions groove is suitable for being positioned laterally on except defrosting system along the side string of the air force component
Positive downstream at, flowing water and make its upstream toward downstream from the air force component on the air force component to collect
Discharge.
Especially apply the aerodynamic lift generated in interior cambered surface and extrados by air flowing on the air force component.
The air force component may be, for example, aircraft wing and empennage or rudder.
Preferably, blade of the air force component for the rotor of rotary aircraft.The rotor can be to ensure this
Aircraft rises the main rotors even promoted or the rear rotor for mainly ensuring anti-yawing function.
The air force component is usually by its first end and the fuselage for being fixed on such as aircraft or the rotor of aircraft
Wheel hub class formation on, and its second end is free.
Except defrosting system is that heat is generated at the leading edge locus of air force component to cause the inner arc at the leading edge locus
Frost on face and extrados it is at least local melting occur therewith water except defrosting system.Preferably, it should be removed except defrosting system for electric heating
Defrosting system.
Electric defrosting system can be powered continually-there.In this case, leading edge is heated continuously, and thus prevents the shape of frost
Into.In addition, water is subsequently formed and is flowed through in the leading edge.The electric defrosting system more properly forms anti-defrosting system.
The electric defrosting system can also be formed by the component of multiple interleaved powers in a periodic manner.In this case, air
The up-front different zones of dynamic component are heated successively.Frost may be locally formed in the leading edge, once the then region quilt
Heating, the frost are just removed, which melts at least partly.Water is subsequently formed in frost and can be flowed through in leading edge.
Once arrival can shape by removing the region of defrosting system heating for flowing water on the region of air force component
Into icing barrier as previously mentioned.
Each emissions groove of anti-icing equipment according to the present invention is located at the side string along the air force component for removing defrosting system
Positive downstream at, i.e., the intrados of the air force component and extrados can no longer be heated by this except defrosting system (at this).As a result,
Water can flow into each emissions groove to be discharged rather than continue to flow on intrados and extrados and be subsequently formed frost and/or ice.
Advantageously, therefore which can limit or even eliminate the formation of the icing barrier, and avoid air therewith
The performance of dynamic component declines.
According to the preferred embodiment of the present invention, which is used for rotary air dynamic component, particularly for
The rotor blade of rotary aircraft.The air force component is rotation, be from the first end of the air force component to
The center of the centrifugal force of the second end orientation of the air force component.Advantageously, which can make accumulation in each emissions groove
Interior water is discharged into the second end discharge of the air force component.Each emissions groove is open-minded at second end position, thus makes water drive
It is scattered to except emissions groove, so as to be discharged to except the air force component.
When assembling the blade of rotor of rotary aircraft, the preferred embodiment is especially effective.In fact, for packet
The spademan between 5 meters and 13 meters (5 and 13m) is included, the blade of the main rotor of this aircraft is usually per minute with being included in
The speed of rotation between 150 turns and 450 turns (150 arrive 450trs/mn).Moreover, the spademan of the magnitude for 0.8 meter to 3 meters, this
The blade of the rear rotor of kind aircraft usually has the speed of rotation more than 1000trs/mn.These spademans and these speeds of rotation
Combination effect allow to obtain larger centrifugal acceleration, can for example corresponding at the second end of blade be more than terrestrial gravitation
100 times of acceleration.This centrifugation that can be obtained and can be used in the case of any other function of not damaging aircraft adds
Speed allows easily and efficiently disperses the water being present in emissions groove.
Moreover, the centrifugal acceleration increases along the first end from the air force component to the spademan of second end.Favorably
Ground causes the centrifugal force of the increase centrifugal acceleration therefore to increase with the amount for the water to be discharged.In fact, in the centrifugal force
Under the action of, flow is to the second end of the air force component.In fact, the amount for the water to be discharged is also along the air force structure
The spademan of part increases to its second end.Therefore, according to the preferred embodiment for the present invention, the amount for the water to be discharged is bigger, allows this
The centrifugal force of discharge is bigger.
In addition, the air force component is rotation, generate the air flow rate of aerodynamic lift and aerodynamic drag according to
The spademan of the air force component is different.More precisely, these aerodynamic lifts and resistance are in the rotation positioned at blade
(i.e. towards the first end of the air force component and utmostly towards the air force component in interior zone near the heart
Second end) it is weaker.Therefore, the presence of the icing barrier in the interior zone will not reduce or pianissimo reduce the air and move
The aerodynamic quality of power component.Thus, without removing the icing barrier that may be formed in such interior zone.
Therefore, each emissions groove of anti-icing equipment can be located at air force component from its first end until its second end
On entire spademan.Preferably, each emissions groove of anti-icing equipment be located at the spademan of the air force component in addition to being located towards
On other regions of the interior zone of the first end of the air force component.For example, the interior zone is from the air force component
Rotation center extend to 50% distance of the entire spademan for representing the air force component.It should be by the air force component
" entire spademan " is interpreted as the of the rotation center of the air force component and the air force component along the spademan direction
The distance between two ends.
Another embodiment according to the present invention, anti-icing equipment, which has along the spademan of the air force component, to be extended extremely
Few one is collected interior conduit and suction passage.Each collection interior conduit is located in the air force component, these suction passages will
Each emissions groove is connected to collection interior conduit.Secondary depression is formed in these suction passages, to promote by drawing in intrados
With the flow that is flowed on extrados to each emissions groove.These suction passages can on all emissions grooves genesis analysis, water to be promoted to exist
Each emissions groove is flowed on the entire spademan of the air force component.
In fact, the secondary depression being present in these suction passages can generate absorption flowing in the air force component
Intrados and extrados on water the phenomenon that.As a result, due to the absorption phenomenon, which is easier from intrados and outer arc surface current
To emissions groove.Thus, the secondary depression being present in these suction passages from each emissions groove extract water and can direct it towards collection
Interior conduit, to be discharged to except the air force component.
Another embodiment according to the present invention, each emissions groove can be located on the entire spademan of air force component.However,
When this another embodiment of the present invention is used for the rotary type air force structure of the rotor blade of such as rotary aircraft etc
During part, each emissions groove (as previously mentioned, can be moved positioned at the spademan of the air force component in addition to interior zone positioned at the air
Near the first end of power component) except other parts.
According to the first version of this another embodiment, each collection internal pipeline is coupled to pump arrangement.It should
Pump arrangement generates secondary depression in each collection interior conduit, which forms in suction passage and reverberate, and is inhaled so as to generate
Flowing is taken the water on the intrados and extrados of the air force component the phenomenon that.
Each collection interior conduit is opened near first end from the air force component, to be coupled to the pumping
Device.On the contrary, each collection interior conduit is not opened at the second end position, so as to make the secondary depression of generation logical only in absorption
It is reverberated in road.
In addition, in order to draw water of the flowing on air force component intrados and extrados well, suction should be made
The number distribution of channel is taken on all emissions grooves.Collecting internal pipeline should also be maintained in temperature above freezing, be taken to avoid formation
The ice obstruction for the suction effect that disappears.For example, electric defrosting system can be used, water is remained liquid shape in interior conduit is collected
Shape.Water is arranged to pump arrangement followed by each collection interior conduit.
According to the second version of this another embodiment, the hot-air of pressurization is at a relatively high speed in each collection inner tube
Flowed in road, and secondary depression therefore generated in suction passage, be subsequently formed absorption flowing in air force component intrados and
The phenomenon that water on extrados.In order to discharge the forced air for gradually undertaking institute's extract water, each collection interior conduit is in freedom
The second end position at be opened.Each collection interior conduit is also opened near first end so that this it is initially dry plus
Press air injection.The hot compressed air is for example in the Thermal Motor position for being equipped with the aircraft of the air force component
Place is especially extracted in the output of compressor.
On the other hand, forced air should flowing be without flowing in suction passage only in each collection interior conduit, so that secondary
Low pressure is appeared in these suction passages.In fact, the size of these draw lines is larger, and in particular according to forced air each
The speed flowed in a collection interior conduit.
Suction passage and collection interior conduit preferably have circular section.However, other section shape can be used, such as
Oval-shaped profile.
For example, the circular section of internal pipeline has the radius being included between 5 millimeters and 10 millimeters.
This other embodiment (no matter its which version) is without using centrifugal force come the row's of discharge trough inner water.This is in addition
Embodiment therefore can be applied to fixed air force component, such as aircraft wing or the empennage of all types of aircraft.
In addition, empty pneumatic mechanism should not be damaged by forming the presentation of each drainage network for collecting interior conduit and suction passage
The mechanical strength and aerodynamic characteristics of part.For example, if air force component has one or more structure cases, then the row
Water Network is positioned in unique and same structure case inside, and across the structure case working component suction passage in wing
Spademan length on be minimized.
In addition, no matter the present invention any embodiment, anti-icing equipment should have at each emissions groove position extremely
A few heater.In fact, in order to by anti-icing equipment draining according to the present invention, the water being present in emissions groove should not
Transformation frosts or ice.For this purpose, at least one heater is located at each emissions groove position, will be present in the water in emissions groove
It is maintained in emissions groove in liquid form.Each heater is, for example, electric heating component.Each heater can also arranged by coated lining
The enamelled coating or heating coating of trench bottom are formed.
Moreover, the heater allows (such as using the anti-caking before anti-icing equipment according to the present invention operation
Before the aircraft of ice production apparatus starts), it would be possible to the frost or ice formed in emissions groove is transformed into water.
Preferably, once weather conditions are conducive to that frost is made to be formed in emissions groove, each at each emissions groove position plus
Hot component is powered with continuous fashion.Therefore, eliminating the water that is present in emissions groove, completely or partially transformation frosts or the wind of ice
Danger.
If in fact, powering by alternately or in a manner of the period to heater, water may be temporarily and partly in emissions groove
In be locally changed into frost or ice, obstruction can be manufactured in the emissions groove therewith.Water cannot temporarily flow to the emissions groove again, then exist again
It is flowed on intrados and extrados, so as to form icing barrier.
In addition, each emissions groove should not destroy the structure feature of air force component.Each emissions groove is therefore positioned at operation air
Except the groundwork structure of dynamic component, for example, allowing using centrifugal force and/or the spar of shear bending or twisting resistance and
In surface region except rib.
Equally, each emissions groove should not significantly destroy the aerodynamic quality of air force component, so that in dry air
Break even balance between the reduction of performance under environment and the gain of the performance under the frozen environment with the attachment device is
Advantageous.
On extrados, anti-icing equipment according to the present invention is preferably positioned as being formed in the pneumatic pair on the extrados
After at least peak value of low pressure, it is preferably positioned as at least 5% of the side string after pneumatic secondary depression peak value.As a result, by
All air forces interference that emissions groove may introduce does not interfere with or is influenced in a manner of minimum the air force of air force component
Performance.As previously mentioned, except defrosting system ensure that the defrosting from extrados to emissions groove.For example, emissions groove is positioned along air
The side string of dynamic component is away from up-front a distance, corresponding to the 15% of the side string of the air force component.The emissions groove can be managed
It solves to be located in a region, more than the region, frost will not be formed on air force component.
On intrados, anti-icing equipment according to the present invention be preferably just located in the expected edge for forming frost it
Afterwards, so that air limiting layer is maintained at the laminar flow on the intrados for a long time as far as possible and therefore unobvious increase pneumatically
Resistance.As previously mentioned, except defrosting system ensures the defrosting from intrados to emissions groove.It is moved for example, emissions groove is located in along air
The side string of power component is in a distance since the leading edge, corresponding to the 25% of air force component side string.
The error of these positions of the emissions groove on each intrados and extrados is, for example, the side string of air force component
+/- 10%.
In addition, emissions groove has upstream lip, trench bottom and downstream lip.Emissions groove also has in upstream lip and each inner arc
The first blend radius R between face and extrados1And the second blend radius R between downstream lip and trench bottom2.Moreover,
First blend radius R1With the second blend radius R2Trench bottom can effectively be directed water towards.
In fact, it is preferable that these blend radius R1、R2It is larger, it can utilize and be made of herein water and inner arc or extrados
Two media between Laplce's surface tension phenomena, to guide flowing of the water in emissions groove.Moreover, these blend radius
R1、R2It can make to maximize close to the attachment pressure between 0 DEG C of each water droplet and emissions groove side wall.
First blend radius R1Such as it is included between 0 millimeter and 10 millimeters, the second blend radius R2Be included in 1 millimeter and
Between 10 millimeters.Preferably, the first blend radius is included between 1 millimeter and 2 millimeters, and the second blend radius R2 is included in 1 milli
Between rice and 2 millimeters.
Moreover, pass through trench bottom side wall PFTrench bottom is formed, passes through the second blend radius R2With downstream lip side wall PLBy slot
Bottom sidewall PFIt is connected to upstream lip.Pass through downstream lip side wall PLDownstream lip is formed with inner arc or extrados.Trench bottom side
Wall PFWith downstream lip side wall PLForm trench bottom angle beta.Equally, downstream lip side wall PLDownstream lip is formed with inner arc or extrados
Edge angle α.Therefore, trench bottom angle beta and downstream lip angle α can be effectively prevented from water flow back into except emissions groove and formed icing screen
Barrier.
In fact, trench bottom angle beta and downstream lip angle α are acute angle, i.e., less than 90 °, to avoid water due to capillarity and
It crosses downstream lip and flows back into emissions groove.Moreover, these angles are advantageously identical, trench bottom side wall base in geometrical construction
Originally the outer surface of air force component is parallel to, that is, is parallel to intrados or extrados.
In addition, when there is a large amount of water in emissions groove, trench bottom angle beta and downstream lip angle α are sufficiently large, and are flowed through down to avoid water
Trip antelabium is simultaneously flowed back into except emissions groove.Trench bottom angle beta and downstream lip angle α are greater than 30 °.
The size of emissions groove is also larger, whole water of the flowing on intrados and extrados on the one hand to be made to be directed into the row
In slot and another aspect makes the water being present in the emissions groove be retained in emissions groove until being dispersed.
The thickness that the moisture film flowed on intrados and extrados usually has is included in 1 millimeter to 2 millimeters, and (1 arrives
Between 2mm).Therefore the height of collecting tank should be greater than 2mm, this of emissions groove is highly from inner arc or extrados along air force component
Thickness extends to trench bottom side wall PF。
Conversely, in the usual manner, it should avoid being formed height on the profile of air flowing is subjected to more than flowing limitation
One or more obstacles of the thickness of layer, to limit aerodynamic interference over the outline.These air forces are interfered mainly by this
The increase of the aerodynamic drag of profile causes.
In a preferred embodiment of the invention, i.e. the blade of rotary aircraft, at the emissions groove position on the blade
The thickness of air flow restriction layer for example change between about 0,4 millimeter and 3 millimeters.More properly, according to aircraft
Size, the thickness of limiting layer can change, and between about 0,4 millimeter to 0,6 millimeter surging in the case of laminar flow
Change between 1,3 millimeters to 3 millimeters in the case of flowing.
However, the moisture film for effective discharge flow on intrados and extrados, the height of collecting tank can be more than 2 millis
Rice, and therefore it is more than the height of the limiting layer.In view of the efficiency of emissions groove and anti-icing equipment, the presence by the emissions groove should be received
Caused by air force component aerodynamic quality decline.
In addition, by the opening of emissions groove formed in a distance between upstream lip and downstream lip be sufficiently large with
Water droplet of the flowing on air force component is collected, including recombinating the large water droplet formed by numerous smaller water droplets.If emissions groove
Opening length it is too small, then the emissions groove can continue to flow in air force component surface and can form the water of icing barrier
Drop is crossed.On the contrary, the Opening length is not sufficiently large the air flowing on interference intrados and extrados.
Moreover, can be approximately a diameter of 2 millimeters of sphere by the large water droplet being formed on intrados and extrados.Opening
Length minimum should then be equal to two drop diameters, i.e., 4 millimeters, emissions groove can be made to intercept and capture these water droplets, in upstream lip position
The first blend radius R at place1Also effectively it is easy to guide the water in emissions groove.Opening length can be limited in 20 millimeters, and air moves
The total length of power component side string is such as about 400 millimeters (aircraft for 5 tonnes) and about 600 millimeters (for 10 tons
The aircraft of grade).
For example, for the side string total length of its each blade is about 400 millimeters of 5 tonnes of aircraft, height
For 2 millimeters and emissions groove that Opening length is 4 millimeters makes the drag overall of each blade increase about 4%, and height for 3 millimeters and is opened
The emissions groove that mouth length is 15 millimeters can make the drag overall of each blade increase by 20%.
Equally, for the side string total length of its each blade is about 600 millimeters of 10 tons of aerodynes, highly it is
The emissions groove that 2 millimeters and Opening length are 4 millimeters makes the drag overall of each blade increase about 1%, and height for 3 millimeters and is open
The emissions groove that length is 15 millimeters can make the drag overall of each blade increase by 4%.
As a result, according to the size of air force component and the feature of aircraft, the Opening length of emissions groove size is included in 4
Between millimeter and 20 millimeters, its associated height is between 2 millimeters and 5 millimeters.The height of the emissions groove is from inner arc or upper cambered surface edge
The thickness of air force component extends to trench bottom side wall PF, and Opening length is from upstream lip along air force component side string
Extend to the downstream of downstream lip.
Finally, in order to discharge enough waters, the bottom lengths of emissions groove are (from the second blend radius R2 and trench bottom side
The side string of junction along air force component between wall extends to the downstream of trench bottom) at least equal to, preferably more than be open
Length.The bottom lengths of the emissions groove can be included between 4 millimeters and 30 millimeters.
These sizes of emissions groove can change along the spademan of air force component, such as to be adapted to the water being present in emissions groove
Amount, the water especially increased in a preferred embodiment of this invention.In a preferred embodiment of this invention, emissions groove is this
Change in size also is able to limitation and is contained therein in the smaller region of frosting effect (i.e. in air force component with the emissions groove
Portion) interference of associated air force.However, these sizes are preferably constant, so as on the one hand be conducive to manufacture air
On the other hand dynamic component makes the mechanical property of air force component not generate significant change with its span.Advantageously, emissions groove can
To be attached to the component of the structure for being exclusively used in its integration of air force component.Therefore the size of emissions groove should be taken into account and discharge
Maximum amount of water, the maximum amount of water that especially discharged near air force component second end, to avoid emissions groove overflow, water reflux
To intrados, so as to form icing barrier.
Preferably, emissions groove has 6 millimeters of Opening length, 3 millimeters of height and 9 millimeters of bottom lengths, with 45 °
Trench bottom angle beta and downstream lip angle α.
It is equally important that especially in the case where air force component operates in the environment for being covered with dust, it is impossible to portion
Divide or fully block the emissions groove of anti-icing equipment according to the present invention.This environment for being covered with dust is common in the big of relatively drying
Gas bar part, wherein the risk for forming frost is smaller or is zero.This environment for being covered with dust is more specifically by related to higher temperature
The presence of the grains of sand of connection is formed, therefore the invisible risk frosted.The use of the cover of such as plastic material to protect emissions groove is feasible
, to avoid the particle penetration of the dust when there is not frosting risk or sand.
The present invention also aims to provide a kind of air force component of aircraft, the air force component has edge
The first end of the spademan of the air force component from the air force component extends lengthwise into the air force component
The intrados and extrados of second end.The air force component also has to be longitudinally extended along the spademan of the air force component
And couple the leading edge of the intrados and extrados in the upstream of the air force component.The air force component dress
Defrosting system and previously described anti-icing equipment are removed equipped with being located at the leading edge locus.
The air force component is more specifically for rotary aircraft, and air force component turns for rotary aircraft
The blade of son.
Description of the drawings
With reference to attached drawing, in the detailed description of the following embodiment provided in a schematic way, the present invention and its advantage will
It can become more apparent upon, wherein：
Three-dimensional views of-the Fig. 1 for the air force component for being equipped with anti-icing equipment according to the present invention,
The transverse cross-sectional view of air force component that-Fig. 2 is assembled by the preferred embodiment for the present invention,
Two transverse cross-sectional views of air force component that-Fig. 3 and 4 is assembled for another embodiment of the present invention,
- Fig. 5 is the emissions groove detailed view according to anti-icing equipment of the present invention,
- Fig. 6 for rotary aircraft and
- Fig. 7 is the rotor for being equipped with the rotary aircraft according to anti-icing equipment of the present invention.
Specific embodiment
The component presented in multiple and different attached drawings is identified with unique and phase reference label.
It notices and orthogonal three directions X, Y and Z is represented in Fig. 1 to 5.
Direction X is longitudinal and is guided along the spademan of each air force component 2.
Direction Y is lateral and is guided along the side string of each air force component 2.
Finally, direction Z is ascent direction and corresponds to the size of the structure in height.Term " thickness " is associated with dress
The rising size along the ascent direction put.
Fig. 1 shows air force components 2, can be the blade or tail of such as rotor of aircraft wing, rotary aircraft
The wing.The air force component 2 has to be extended to along the spademan of air force component 2 from the first end 24 of the air force component 2
The intrados 22 of second end 25 and extrados 23.The air force component 2 extends transverse to rear 29 from leading edge 21.21 He of leading edge
The spademan of rear 29 along air force component 2 is longitudinally extended and couples intrados 22 and extrados 23.
Air force component 2, which is equipped with to be located at its 21 position of leading edge, removes defrosting system 3.Should be, for example, except defrosting system 3
Electric defrosting system.This defrosting system 3 that removes can avoid forming frost or ice at 21 position of leading edge or melting being formed in the leading edge
Frost or ice on 21.In both cases, the water of film or form of moisture drops can be flowed in the leading edge 21 of air force component 2 and
Except icing barrier is formed on the intrados 22 in the downstream of defrosting system 3 and extrados 23, make the air pertormance of air force component 2
It can decline.
The air force component 2 also has anti-icing equipment 1, to avoid icing barrier is formed.The anti-icing equipment 1 is collected
It flows the water on intrados and extrados 23 and discharges it.Fig. 2 to 4 represents corresponding to for this air force component 2
The different horizontal sections of the different embodiments of anti-icing equipment 1.
In a manner of sharing, which has in 23 upper edge air force structure of each intrados 22 and extrados
The emissions groove 10 that the spademan of part 2 is longitudinally extended.Each emissions groove 10 is laterally positioned except the positive downstream of defrosting system 10, to collect side by side
It is placed on intrados 22 and extrados 23 from upstream toward downstream flowing water.
Each emissions groove 10 has upstream lip 11, trench bottom 12 and downstream lip 13.Pass through the first blend radius R1It will be upper
Trip antelabium 11 is connected to intrados 22 or extrados 23.Pass through trench bottom side wall PFTrench bottom 12 is formed, passes through the second engagement half
Diameter R2With downstream lip side wall PLBy trench bottom side wall PFIt is connected to upstream lip 11.Pass through downstream lip side wall PLAnd intrados
22 or extrados 23 formed downstream lip 13.
Trench bottom side wall PFWith downstream lip side wall PLForm trench bottom angle beta, downstream lip side wall PLWith intrados 22 or outside
Cambered surface 23 forms downstream lip angle α.
Blend radius R1, R2It is preferably larger.For example, the first blend radius R1It is included between 0 millimeter and 10 millimeters,
And the second blend radius R2It is included between 1 millimeter and 10 millimeters.Preferably, the first blend radius is included in 1 millimeter
And between 2 millimeters, and the second blend radius R2It is included between 1 millimeter and 2 millimeters.
Moreover, trench bottom angle beta and downstream lip angle α are acute angle, i.e., less than 90 °.In addition, trench bottom side wall PFIn geometry structure
The outer surface for being basically parallel to air force component 2 is made, that is, is parallel to intrados 22 or extrados 23, the two angle betas and α etc.
In or more than 30 °.
In addition to angle [alpha], β and blend radius R1, R2, also pass through bottom lengths LF, height HRWith opening aperture LOCome the row of characterization
Slot 10.Bottom lengths LFFrom the second blend radius R2With trench bottom side wall PFBetween side string of the junction along air force component 2
Extend to the downstream of trench bottom 12, height HRFrom intrados 22 or extrados 23 slot is extended to along the thickness of air force component 2
Bottom sidewall PF.The aperture that is open LOCorresponding to the distance between upstream lip 11 and downstream lip 13.
For example, Opening length LOIt is included between 4 millimeters and 20 millimeters, height HRBe included in 2 millimeters and 5 millimeters it
Between, and bottom lengths LFIt is included between 4 millimeters and 30 millimeters.Preferably, emissions groove 10 has 6 millimeters of Opening length LO, 3
The height H of millimeterRAnd 9 millimeters of bottom lengths LF.Trench bottom angle beta and downstream lip angle α are preferably equivalent to 45 °.
These sizes of emissions groove 10 are constant on the entire spademan of air force component, but these sizes can be with the exhibition
The wing changes.
The concrete shape of emissions groove 10 and its size can allow for collecting and collect flowing on intrados 22 and extrados 23
Water, it is entirely avoided water flow back to again and on intrados 22 and extrados 23 formed icing barrier.
Blend radius R1, R2Especially allow effectively to flow in intrados 22 or extrados 23 to the bottom-boot of emissions groove 10
On water, angle [alpha], β avoids water and flow back into again except emissions groove 10.
Moreover, these sizes can be limited on intrados 22 and extrados 23 air flowing interference, and limit due to
The presence of emissions groove 10 and occur air force interference.
Icing device 1 according to the present invention also has the heater 14 being located at each 10 position of emissions groove.The heating structure
The presence of part 14 avoid in emissions groove 10 or on its side wall water transformation frost or ice and cannot be discharged.Each heating structure
Part 14 is, for example, electric heating component.
Fig. 2 represent the present invention a kind of preferred embodiment, for rotation air force component 2 and more specifically with
In the blade 53,54 of the rotor 51,52 of rotary aircraft 50.This aircraft 50 is shown in Fig. 6.The rotor of the rotation
51,52 cause the centrifugal force oriented from first end 24 to second end 25 occurred in each blade 53,54.
As shown in Figure 1, each emissions groove 10 of icing device 1 can be located on the entire spademan of air force component 2, from its
One end 24 is until second end 25.
However, the rotor 51,52 is rotation, the air of aerodynamic lift and resistance is generated on each blade 53,54
The rate of flowing is different according to the spademan position on blade 53,54.Especially, these aerodynamic lifts and resistance are in rotor
Smaller in region near 51,52 rotation center, therefore, the presence of the icing barrier in the region only slightly influences air and moves
The aerodynamic quality of power component 2.
In fact, as indicated in fig 7, each emissions groove 10 can start from the distance D of the rotation center of the rotor 51,52,
It is and open-minded at the position of second end 25.For example, distance D corresponds to the entire spademan L of air force component 2E50%.
Moreover, in order not to decline the aerodynamic quality of air force component 2, each emissions groove 10 can be positioned in inner arc
On face 22 and extrados 23, there is air force interference with limitation, do not generate any air force interference even.
For example, on extrados 23, emissions groove 10 is laterally positioned corresponds to air force component 2 since leading edge 21
Side string lC50% distance on.
Equally, on intrados 22, emissions groove 10 is laterally positioned corresponds to air force component 2 since leading edge 21
Side string lC25% distance on.
The tolerance of these positions of emissions groove 10 is, for example, the side string l of air force component 2 on intrados 22 and extrados 23C
+/- 10%.
Fig. 3 and 4 represents two kinds of embodiments of the present invention, and operation logic is identical.
The tool of anti-icing equipment 1 of Fig. 3 is shown in be connected in a collection there are two collection interior conduit 15 and by emissions groove 10
The suction passage 16 of pipeline 15.It collects interior conduit 15 and suction passage 16 is located in air force component 2.Suction passage 16 is each
A emissions groove 10 on the whole along the spademan genesis analysis of air force component 2.
Being shown in the anti-icing equipment 1 of Fig. 4, there is only one to collect interior conduit 15 and emissions groove 10 is connected in collection
The suction passage 16 of pipeline 15.It collects interior conduit 15 and suction passage 16 is located on air force component 2, draw people having a common goal 16 each
A emissions groove 10 on the whole along the spademan genesis analysis of air force component 2.
Secondary depression is formed in suction passage 16 to promote to flow on intrados 22 and extrados 23 by drawing
Flow is to each emissions groove 10.
It is present in the secondary depression in suction passage 16 and also is able to draw water in each emissions groove 10 and by it into collection
Pipeline 15 guides, to be discharged to except air force component 2.Anti-freeze dress that can be in different ways, represented by independently of Fig. 3 and 4
It puts 1 ground and generates the secondary depression.
For example, each collection interior conduit 15 is coupled to pump arrangement.The pump arrangement is therefore in each collection interior conduit
Secondary depression is formed in 15, which is reverberating therefore generation absorption flowing in air force component 2 in suction passage 16
The phenomenon that water on intrados 22 and extrados 23.Each collection interior conduit 15 is only from the first end 24 of air force component 2
It is open-minded nearby, to be coupled to pump arrangement and water can be discharged.
According to another embodiment, forced air is flowed in each collection interior conduit 15 with higher rate, thus is being drawn
Secondary depression is formed in channel 16, generates draw flowing the water in interior cambered surface 22 and extrados 23 the phenomenon that therewith.Each collection
Interior conduit 15 is opened near first end 24, to spray the forced air.Each collection interior conduit 15 is also opened in free the
At two ends, 25 position, so as on the one hand discharge the forced air and on the other hand disperse the water from emissions groove 10.
Moreover, air motivation component 2 a can have multiple structure cases 26,27,28.In order not to destroy the air motivation component 2
Mechanical features, each interior conduit 15 and suction passage 16 of collecting be located at unique and same structure case 27 inside.
As previously mentioned, being shown in the anti-icing equipment 1 on Fig. 3 and 4 has at each 10 position of emissions groove extremely
A few heater 14, frosts or ice to avoid the water transformation being present in emissions groove 10.
Obviously, the present invention is limited by a variety of implementation versions.Even if numerous embodiments have been described, it will be understood that
It can not possibly be in a manner that exclusive mode determines to be possible to.Certainly it will be appreciated that retouched component can be replaced with equivalent elements and
Without departing from the scope of the present invention.
Claims (18)
1. one kind is used for the anti-icing equipment (1) of air force component (2), the air force component (2) have along described
The first end (24) of the spademan of air force component (2) from the air force component (2) extends lengthwise into the air force
It the intrados (22) and extrados (23) of the second end (25) of component (2) and is longitudinally extended along the spademan and in the sky
Couple the intrados (22) and extrados along the side string of the air force component (2) in the upstream of aerodynamic force component (2)
(23) leading edge (21), the air force component (2), which is equipped with to be located at the leading edge (21) position, removes defrosting system
(3),
It is suitable for it is characterized in that, the anti-icing equipment (1) has along the spademan in each intrados (22) and extrados
(23) emissions groove (10) being longitudinally extended on, each emissions groove (10) are removed suitable for being just located in transversely along described in the side string
The downstream of defrosting system (3), to collect water of the flowing on the air force component (2) and by it from the air force component
(2) upstream is to the downstream drain of the air force component (2), and each emissions groove (10) is with upstream lip (11), trench bottom
(12) and downstream lip (13) and on the one hand the upstream lip (11) and each intrados (22) and extrados (23) it
Between the first blend radius R1And on the other hand the second engagement between the upstream lip (11) and the trench bottom (12)
Radius R2, the first blend radius R1With the second blend radius R2The water can be guided into the trench bottom (12).
2. anti-icing equipment (1) according to claim 1, which is characterized in that the trench bottom (12) is by trench bottom side wall PF
It is formed, the trench bottom side wall PFPass through the first blend radius R1With downstream lip side wall PLIt is connected to the upstream lip
(11), the downstream lip (13) is by the downstream lip side wall PLIt is formed with the intrados (22) or extrados (23),
The trench bottom side wall PFWith the downstream lip side wall PLFormation slot bottom angle beta, and the downstream lip side wall PLWith it is described interior
Cambered surface (22) or extrados (23) form downstream lip angle [alpha], and the slot bottom angle beta and the downstream lip angle [alpha] can be kept away
Exempt from the water to flow back into except the emissions groove (10).
3. the anti-icing equipment (1) according to claim 1 to 2 wherein any one, which is characterized in that the emissions groove (10)
Length be included between 4 millimeters and 20 millimeters, the length is determined according to the side string of the air force component (2)
It is fixed.
4. the anti-icing equipment (1) according to claim 1 to 2 wherein any one, which is characterized in that the emissions groove (10)
Height be included between 2 millimeters and 10 millimeters, the height is determined according to the thickness of the air force component (2).
5. anti-icing equipment (1) according to claim 1, which is characterized in that the first blend radius R1It is included in 0
Between millimeter and 10 millimeters.
6. anti-icing equipment (1) according to claim 1, which is characterized in that the second blend radius R2It is included in 1
Between millimeter and 10 millimeters.
7. anti-icing equipment (1) according to claim 2, which is characterized in that the slot bottom angle beta is less than 90 °.
8. anti-icing equipment (1) according to claim 2, which is characterized in that the downstream lip angle [alpha] is less than 90 °.
9. anti-icing equipment (1) according to claim 1, which is characterized in that
The anti-icing equipment (1) has at least one heater (14) at the position of each emissions groove (10).
10. anti-icing equipment (1) according to claim 1, which is characterized in that the first end (24) is fixed on flight
On device (50), and the second end (25) is free, and the emissions groove (10) is opened at the second end (25) position.
11. anti-icing equipment (1) according to claim 1, which is characterized in that the anti-icing equipment (1) has along institute
State at least one collection interior conduit (15) and the suction passage (16) that the spademan of air force component (2) is longitudinally extended, Ge Geshou
Collect interior conduit (15) positioned at the inside of the air force component (2), and the suction passage (16) joins each emissions groove (10)
It is connected to and collects interior conduit (15), secondary depression is formed in the suction passage (16) to draw the water, and then to the slot bottom
Portion (12) guides the water.
12. anti-icing equipment (1) according to claim 11, which is characterized in that each collection interior conduit (15) is coupled
To pump arrangement (17), to form the secondary depression in the suction passage (16).
13. anti-icing equipment (1) according to claim 2, which is characterized in that the first end (24) is fixed on flight
On device (50), and the second end (25) is free, and forced air is in each collection interior conduit (15) with higher rate stream
Dynamic, to form secondary depression in suction passage (16), each collection interior conduit (15) is opened at the second end (25) position,
And the air is flowed to the second end (25).
14. anti-icing equipment (1) according to claim 1, which is characterized in that described except defrosting system (3) is thermoelectric defrosting
System.
15. anti-icing equipment (1) according to claim 1, which is characterized in that the air force component (2) is flight
The blade (53,54) of the rotor (51,52) of device (50).
16. anti-icing equipment (1) according to claim 15, which is characterized in that the emissions groove (10) is from the first end
(24) 35% distance of the entire spademan corresponding to the blade (53,54) starts and along the institute of the blade (53,54)
It states spademan and extends to the second end (25).
17. a kind of air force component (2) of aircraft (50), the air force component (2) has intrados (22), outer arc
Face (23) and leading edge (21) and second end (25), the air force component (2), which is equipped with, is located in the leading edge (21) position
That puts place removes defrosting system (3),
It is characterized in that, the air force component (2) has the anti-caking according to claim 1 to 16 wherein any one
Ice production apparatus (1).
18. air force component (2) according to claim 17, which is characterized in that the aircraft (50) is rotary wind type
Aircraft, and blade (53,54) of the air force component (2) for the rotor (51,52) of the rotary aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510175391.5A CN105882979B (en) | 2015-01-14 | 2015-01-14 | The anti-icing equipment of aircraft blade |
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|---|---|---|---|
| CN201510175391.5A CN105882979B (en) | 2015-01-14 | 2015-01-14 | The anti-icing equipment of aircraft blade |
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| CN105882979A CN105882979A (en) | 2016-08-24 |
| CN105882979B true CN105882979B (en) | 2018-06-15 |
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| CN201510175391.5A Active CN105882979B (en) | 2015-01-14 | 2015-01-14 | The anti-icing equipment of aircraft blade |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107117318B (en) * | 2017-03-22 | 2019-10-18 | 武汉航空仪表有限责任公司 | A kind of preparation method of anti-/ deicing composite material functional unit |
| US10870491B2 (en) * | 2017-07-20 | 2020-12-22 | The Boeing Company | Eductor driven anti-ice system |
| CN108327892B (en) * | 2017-12-30 | 2024-04-09 | 镇江同舟螺旋桨有限公司 | Tip flap type propeller blade tip shaping method |
| RU2768992C1 (en) * | 2021-05-19 | 2022-03-28 | федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" | Device for preventing the formation of barrier ice on the wing of an aircraft |
| CN114291281B (en) * | 2021-12-30 | 2023-12-26 | 浙江科比特科技有限公司 | Automatic correction channel unmanned aerial vehicle applying AI technology |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE709354C (en) * | 1938-12-11 | 1941-08-14 | Focke Wulf Flugzeugbau G M B H | Device for preventing ice formation on the wings or tail surfaces of aircraft |
| US3496331A (en) * | 1967-12-06 | 1970-02-17 | Sud Aviat Soc Nationale De Con | Electric defrosting facility for rotating blade systems |
| US5322246A (en) * | 1991-08-12 | 1994-06-21 | Mcdonnell Douglas Corporation | Ice prevention device for airfoils |
| CN201472666U (en) * | 2009-06-04 | 2010-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Airplane slat anti-icing extension tube supporting structure |
| CN102826228A (en) * | 2011-06-17 | 2012-12-19 | 空中客车运营简化股份公司 | Air intake of aircraft nacelle |
-
2015
- 2015-01-14 CN CN201510175391.5A patent/CN105882979B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE709354C (en) * | 1938-12-11 | 1941-08-14 | Focke Wulf Flugzeugbau G M B H | Device for preventing ice formation on the wings or tail surfaces of aircraft |
| US3496331A (en) * | 1967-12-06 | 1970-02-17 | Sud Aviat Soc Nationale De Con | Electric defrosting facility for rotating blade systems |
| US5322246A (en) * | 1991-08-12 | 1994-06-21 | Mcdonnell Douglas Corporation | Ice prevention device for airfoils |
| CN201472666U (en) * | 2009-06-04 | 2010-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Airplane slat anti-icing extension tube supporting structure |
| CN102826228A (en) * | 2011-06-17 | 2012-12-19 | 空中客车运营简化股份公司 | Air intake of aircraft nacelle |
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|---|---|
| CN105882979A (en) | 2016-08-24 |
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