CN102431650A - Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device - Google Patents
Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device Download PDFInfo
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- CN102431650A CN102431650A CN2011104438261A CN201110443826A CN102431650A CN 102431650 A CN102431650 A CN 102431650A CN 2011104438261 A CN2011104438261 A CN 2011104438261A CN 201110443826 A CN201110443826 A CN 201110443826A CN 102431650 A CN102431650 A CN 102431650A
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Abstract
The invention discloses an airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device which comprises an airfoil outer skin, a hot air ice preventing and removing system, an ultrasonic high-frequency oscillating auxiliary device, a program controller, an atmosphere temperature sensor and an icing strength annunciator, wherein the atmosphere temperature sensor is used for detecting external atmosphere temperature; the icing strength annunciator is used for detecting the outer surface ice layer thickness of the airfoil outer skin; the hot air ice preventing and removing system comprises an engine gas compressor, an airfoil ice preventing cavity, an empennage ice preventing cavity and an ice preventing and removing hot air delivery device; the ultrasonic high-frequency oscillating auxiliary device comprises an ultrasonic generator and an ultrasonic energy converter unit which is connected with the output end of the ultrasonic generator by a connecting cable; and the program controller is used for automatically controlling connection and disconnection of the ice preventing and removing hot air delivery device and starting and closing of the ultrasonic generator according to a temperature signal and an icing strength signal. Accordingly, the airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device can be used for effectively removing the ice layers of middle airplane body and empennage front edges of an airplane during flight in real time and has the advantages of short ice removing time, low energy consumption, safe and reliable system and thorough ice removal.
Description
Technical field
The present invention relates to a kind of de-icing device, the anti-deicing that it is mainly used in the wing/empennage leading edge of aircraft belongs to that aircraft is anti-icing, the deicing field.
Background technology
Freezing is the one of the main reasons that causes the aircraft flight accident; Especially freezing of aircraft wing, empennage leading edge can cause profile drag to increase, and lift descends; Critical angle of attack reduces; And the deterioration of road-holding property and stability, can cause that especially the aircraft controllability under the take-off and landing state is out of control, thereby cause serious aircraft accident.
For the anti-deicing of the wing in the flight course, empennage, extensively adopt the anti-deicing technology of hot gas at present: promptly refer in flight course the hot air ice-melt that utilizes the aero-engine air compressor to draw.Though the anti-deicing technology of this hot gas can be prevented to a certain extent, deicing, its deicing time is long, and consumed energy is big, because its thermal inertia is big, forms the ice knurl easily at the back in the heating zone simultaneously.Therefore develop novel quick, efficient, energy-conservation aircraft anti-icing, the deicing technology has important use and is worth.
Super sonic when in solid dielectric, propagating, can cause the compression or the extension of medium particle as a kind of form of energy; Cause the variation of solid interior pressure, cause mechanical effect, though the displacement of solid dielectric and speed are little; But the acceleration/accel of particle is very big, even can reach tens thousand of times of acceleration due to gravity, and so big HF oscillation can produce at the bonding interface place of different material and continue great shear forces moment; Make coherent substance broken, separate.
Summary of the invention
The present invention is primarily aimed at the deficiency of the anti-deicing technology of the hot gas that adopts in the existing aircraft flight process; Utilize super sonic to have the particular characteristics of mechanical effect; In conjunction with the aircraft aerofoil profile practical structures of (comprising wing, empennage), a kind of auxiliary hot gas associating of super sonic de-icing device that is used for the aircraft aerofoil profile is proposed.Associating deicer of the present invention is on the basis of the anti-deicing technology of existing hot gas, and auxiliary super sonic high frequency oscillating apparatus can be removed the ice sheet of machine in the aircraft flight, empennage leading edge in real time effectively; The deicing time is short; Expenditure of energy is low, and simultaneity factor is safe and reliable, and deicing is thorough.In the safe flight that has guaranteed aircraft, reduced the deicing time, greatly reduce the consumption of energy.
For realizing above technical purpose, the present invention will take following technical scheme:
The auxiliary hot gas associating of a kind of aircraft aerofoil profile super sonic de-icing device comprises with the corresponding aerofoil profile exterior skin of aerofoil profile outer rim, hot gas anti-deicing system, super sonic HF oscillation auxiliary device, programming controller, is used to the icing intensity signal head that detects the atmosphere temperature transducer of outer atmospheric temperature and be used to detect aerofoil profile exterior skin outside face ice layer thickness; Wherein: the anti-deicing system of said hot gas comprises engine compressor, the anti-icing chamber of wing, the anti-icing chamber of empennage and anti-deicing hot gas feedway; Anti-deicing hot gas feedway comprises anti-deicing hot gas delivery duct and is installed in flow-controlling gate, wing frost valve, the empennage frost valve on this anti-deicing hot gas delivery duct respectively; The wing frost valve is arranged between the admission port in air extractor duct and the anti-icing chamber of wing of flow-controlling gate; The empennage frost valve is arranged between the admission port in air extractor duct and the anti-icing chamber of empennage of flow-controlling gate, and the admission port of flow-controlling gate is connected with the air extractor duct of engine compressor through anti-deicing hot gas delivery duct; Said super sonic HF oscillation auxiliary device comprises ultrasonic generator and passes through connecting cable and ultrasonic generator mouth bonded assembly ultrasonic transducer unit; Said ultrasonic transducer unit comprises a plurality of piezoelectric ceramic transducers, and each piezoelectric ceramic transducer is fixedly mounted on the inside face of aerofoil profile exterior skin; The folding of the ice layer thickness information automatic control flow control cock that programming controller is fed back according to temperature signal that atmosphere temperature transducer fed back and icing intensity signal head and the start and stop of ultrasonic generator, the ice layer thickness information automatic guidance wing frost valve that fed back according to the icing intensity signal head of programming controller, the opening of empennage frost valve simultaneously.
Said aerofoil profile exterior skin comprise with the corresponding wing exterior skin of wing outer rim and with the corresponding empennage exterior skin of empennage outer rim; Said icing intensity signal head, atmosphere temperature transducer are installed in the outside face of wing exterior skin, and piezoelectric ceramic transducer is fixedly mounted on the inside face of wing exterior skin.
The ultrasonic transducer unit is symmetry arrangement up and down along the length direction of aircraft wing exterior skin leading edge.
Said piezoelectric ceramic transducer be shaped as rectangular strip or discoid.
The number of piezoelectric ceramic transducer is between 10-20.
The oscillation frequency of piezoelectric ceramic transducer is consistent with the natural frequency of aerofoil profile exterior skin.
Said ultrasonic transducer unit is at least one; Each rectangular array in ultrasonic transducer unit is uniformly distributed with, and each separate setting in ultrasonic transducer unit.
According to above technical scheme, compared with prior art, the present invention has following advantage:
1, the present invention produces HF oscillation through adding the super sonic of certain intensity and frequency on the surface of aerofoil profile exterior skin, and auxiliary hot gas is prevented and kill off the ice technology, can remove the ice sheet of skin-surface apace.Compare with the anti-deicing method of simple employing hot gas, can avoid too much too high quantity of hot air to flow into anti-icing chamber,, guaranteed the stable performance of driving engine.
2, the present invention adopts the auxiliary hot gas of super sonic HF oscillation to prevent and kill off ice, and anti-deicing system compares with simple employing hot gas, and time of heat significantly reduces.
3, the present invention adopts the auxiliary hot gas of super sonic HF oscillation to prevent and kill off ice, and anti-deicing system compares with simple employing hot gas, and institute's energy requirement significantly reduces, and institute's energy requirement is merely 1/tens of the anti-deicing system of hot gas.Egress of heat reduces greatly.
4, the present invention adopts the auxiliary hot gas of super sonic HF oscillation to prevent and kill off ice, can prevent to ice outside the ice formation generation of knurl effectively.
5, present device is simple, and compact conformation is in light weight.Only need to add many group ultrasonic transducers, can not influence the aerodynamic configuration of aircraft at the inside face of aerofoil profile exterior skin, can the too much weight of additive incrementation aircraft yet.
Description of drawings
Fig. 1 aircraft need be prevented the position view of deicing, and wherein: W is for needing the leading edge of a wing of anti-deicing; T is for needing the fixed fin of anti-deicing; S is for needing the empennage leading edge of anti-deicing;
Fig. 2 is the auxiliary hot gas associating of an aircraft aerofoil profile super sonic according to the invention de-icing device scheme drawing;
Ultrasonic transducer arrangements of cells figure in the leading edge of Fig. 3 aircraft aerofoil profile, wherein: (a) be lateral plan; (b) be birds-eye view
The structural representation of Fig. 4 super sonic HF oscillation auxiliary device;
Wherein:
1, aerofoil profile exterior skin, 2, the aerofoil profile inside panel, 3, flow-controlling gate, 4, check valve; 5, the anti-icing chamber of wing, 6, the wing frost valve, 7, the anti-icing chamber of empennage, 8, the empennage frost valve; 9, engine compressor, 10, programming controller, 11, atmosphere temperature transducer, 12, the icing intensity signal head; 13, ultrasonic generator, 14, connecting cable, 15, the ultrasonic transducer unit.
The specific embodiment
Accompanying drawing discloses the structural representation of preferred embodiment involved in the present invention without limitation; Below will combine accompanying drawing that technical scheme of the present invention at length is described.
As shown in Figure 1, for existing aircraft, generally need the position of anti-deicing to comprise leading edge of a wing W, empennage leading edge S and fixed fin T.
Shown in Fig. 2 to 4; The auxiliary hot gas associating of aircraft aerofoil profile super sonic according to the invention de-icing device comprises with the corresponding aerofoil profile exterior skin of aerofoil profile leading edge, hot gas anti-deicing system, super sonic HF oscillation auxiliary device, programming controller, is used to the icing intensity signal head that detects the atmosphere temperature transducer of outer atmospheric temperature and be used to detect aerofoil profile exterior skin outside face ice layer thickness; Wherein: the anti-deicing system of said hot gas comprises engine compressor, the anti-icing chamber of wing, the anti-icing chamber of empennage and anti-deicing hot gas feedway; Anti-deicing hot gas feedway comprises anti-deicing hot gas delivery duct and is installed in flow-controlling gate, wing frost valve, the empennage frost valve on this anti-deicing hot gas delivery duct respectively; The wing frost valve is arranged between the admission port in air extractor duct and the anti-icing chamber of wing of flow-controlling gate; The empennage frost valve is arranged between the admission port in air extractor duct and the anti-icing chamber of empennage of flow-controlling gate, and the admission port of flow-controlling gate is connected with the air extractor duct of engine compressor through anti-deicing hot gas delivery duct; Said super sonic HF oscillation auxiliary device comprises ultrasonic generator and passes through connecting cable and ultrasonic generator mouth bonded assembly ultrasonic transducer unit; Said ultrasonic transducer unit comprises a plurality of piezoelectric ceramic transducers, and each piezoelectric ceramic transducer is fixedly mounted on the inside face of aerofoil profile exterior skin; The folding of the ice layer thickness information automatic control flow control cock that programming controller is fed back according to temperature signal that atmosphere temperature transducer fed back and icing intensity signal head and the start and stop of ultrasonic generator, the ice layer thickness information automatic guidance wing frost valve that fed back according to the icing intensity signal head of programming controller, the opening of empennage frost valve simultaneously.Said aerofoil profile exterior skin comprise with the corresponding wing exterior skin of the leading edge of a wing and with the corresponding empennage exterior skin of empennage leading edge; In the accompanying drawing; Said icing intensity signal head, atmosphere temperature transducer are installed in the outside face of wing exterior skin, and piezoelectric ceramic transducer is fixedly mounted on the inside face of wing exterior skin.The ultrasonic transducer unit is symmetry arrangement up and down along the length direction of aircraft wing exterior skin leading edge.Said piezoelectric ceramic transducer be shaped as rectangular strip or discoid.The number of piezoelectric ceramic transducer is between 10-20 in each ultrasonic transducer unit.The oscillation frequency of piezoelectric ceramic transducer is consistent with the natural frequency of aerofoil profile exterior skin.Said ultrasonic transducer unit is at least one; Each rectangular array in ultrasonic transducer unit is uniformly distributed with, and each separate setting in ultrasonic transducer unit.The anti-icing chamber of wing by with the corresponding wing in leading edge of a wing position in the outer frisket of frisket and wing constitute, the anti-icing chamber of empennage by with the corresponding empennage in empennage leading edge position in frisket and empennage outward frisket constitute.In addition, be not limited to aerofoil profile outer rim position with the corresponding aerofoil profile exterior skin of aerofoil profile outer rim, it should suitably expand to the field of aerofoil profile outer rim and aerofoil profile outer rim.
Although only adopt super sonic HF oscillation auxiliary device in the accompanying drawing, in fact,, then need super sonic HF oscillation auxiliary device be installed in the empennage leading edge for obtaining anti-preferably deicing effect at the leading edge of a wing.
Principle of work of the present invention is:
Programming controller 10 is according to the unlatching of the outer atmospheric temperature control engine compressor rate of discharge control cock 3 of atmosphere temperature transducer 11 monitoring in real time and the start and stop of ultrasonic generator 13, in case outer atmospheric temperature surpasses freezing point, engine compressor rate of discharge control cock 3 is opened; At this moment, under the control of programming controller, wing frost valve 5 is selected the Open valve opening with empennage frost valve 7 according to the icing intensity signal that icing intensity signal head 12 provides; Hot air flows to the anti-icing chamber of wing 5, the anti-icing chamber 7 of empennage along the direction of arrow; Along the channel flow of tail nose of wing, hot air is along passing to exterior skin 1 to heat in the flow process of passage, and meanwhile ultrasonic generator 13 is opened; Auxiliary hot gas is prevented and kill off ice; For ultrasonic transducer unit 15 high-frequency alternating current that is complementary with it signal excitation is provided through connecting cable 14, under the excitation of ultrasonic generator, fastening ultrasonic transducer unit with the exterior skin inside face produces HF oscillation; Make exterior skin inside that little distortion take place; Thereby,, thereby effectively overcome the bond strength between ice sheet and the exterior skin fast in conjunction with the thawing effect of hot gas to ice sheet in the instantaneous at the interface generation great shear forces of exterior skin and ice sheet; Pulverize ice sheet, make ice sheet come off.Adopt the method for the auxiliary anti-deicing of super sonic; Only need engine compressor to introduce small amount of hot air; Melt one deck ice sheet at ice sheet and exterior skin interface, even need not melt, only ice sheet and masked bond strength are outward dropped to below the bond strength that super sonic can overcome; Utilize ultrasonic HF oscillation, can reach the purpose of effectively anti-deicing.In addition; The opening degree of the icing thickness signal real-time regulated flow-controlling gate 3 that programming controller 10 can also provide according to icing intensity signal head 12 and the power of ultrasonic generator 13 can periodically change the unlatching quantity of ultrasonic transducer unit 15 simultaneously.
As shown in Figure 3, each ultrasonic transducer unit 15 all adopts the mode that is threaded to be anchored on said exterior skin 1 inside face, and along aircraft wing leading edge length direction up and down symmetrical array type arrange.
Shown in Fig. 4, super sonic HF oscillation auxiliary device is made up of ultrasonic generator 13, connecting cable 14, ultrasonic transducer unit 15.Wherein the number of piezoelectric ceramic transducer according to Airfoil Design between the 10-20.
Claims (7)
1. the auxiliary hot gas associating of aircraft aerofoil profile super sonic de-icing device is characterized in that: comprise with the corresponding aerofoil profile exterior skin of aerofoil profile outer rim, hot gas anti-deicing system, super sonic HF oscillation auxiliary device, programming controller, be used to the icing intensity signal head that detects the atmosphere temperature transducer of outer atmospheric temperature and be used to detect aerofoil profile exterior skin outside face ice layer thickness; Wherein:
The anti-deicing system of said hot gas comprises engine compressor, the anti-icing chamber of wing, the anti-icing chamber of empennage and anti-deicing hot gas feedway; Anti-deicing hot gas feedway comprises anti-deicing hot gas delivery duct and is installed in flow-controlling gate, wing frost valve, the empennage frost valve on this anti-deicing hot gas delivery duct respectively; The wing frost valve is arranged between the admission port in air extractor duct and the anti-icing chamber of wing of flow-controlling gate; The empennage frost valve is arranged between the admission port in air extractor duct and the anti-icing chamber of empennage of flow-controlling gate, and the admission port of flow-controlling gate is connected with the air extractor duct of engine compressor through anti-deicing hot gas delivery duct;
Said super sonic HF oscillation auxiliary device comprises ultrasonic generator and passes through connecting cable and ultrasonic generator mouth bonded assembly ultrasonic transducer unit; Said ultrasonic transducer unit comprises a plurality of piezoelectric ceramic transducers, and each piezoelectric ceramic transducer is fixedly mounted on the inside face of aerofoil profile exterior skin;
The folding of the ice layer thickness information automatic control flow control cock that programming controller is fed back according to temperature signal that atmosphere temperature transducer fed back and icing intensity signal head and the start and stop of ultrasonic generator, the ice layer thickness information automatic guidance wing frost valve that fed back according to the icing intensity signal head of programming controller, the opening of empennage frost valve simultaneously.
2. according to the auxiliary hot gas associating of the said aircraft aerofoil profile of claim 1 super sonic de-icing device; It is characterized in that: said aerofoil profile exterior skin comprise with the corresponding wing exterior skin of wing outer rim and with the corresponding empennage exterior skin of empennage outer rim; Said icing intensity signal head, atmosphere temperature transducer are installed in the outside face of wing exterior skin, and piezoelectric ceramic transducer is fixedly mounted on the inside face of wing exterior skin.
3. according to the auxiliary hot gas associating of the said aircraft aerofoil profile of claim 2 super sonic de-icing device, it is characterized in that: the ultrasonic transducer unit is symmetry arrangement up and down along the length direction of aircraft wing exterior skin leading edge.
4. according to the auxiliary hot gas associating of the said aircraft aerofoil profile of claim 1 super sonic de-icing device, it is characterized in that: said piezoelectric ceramic transducer be shaped as rectangular strip or discoid.
5. according to the auxiliary hot gas associating of the said aircraft aerofoil profile of claim 1 super sonic de-icing device, it is characterized in that: the number of piezoelectric ceramic transducer is between 10-20 in the ultrasonic transducer unit.
6. according to the auxiliary hot gas associating of the said aircraft aerofoil profile of claim 1 super sonic de-icing device, it is characterized in that: the oscillation frequency of piezoelectric ceramic transducer is consistent with the natural frequency of aerofoil profile exterior skin.
7. according to the auxiliary hot gas associating of the said aircraft aerofoil profile of claim 1 super sonic de-icing device, it is characterized in that: said ultrasonic transducer unit is at least one; Each rectangular array in ultrasonic transducer unit is uniformly distributed with, and each separate setting in ultrasonic transducer unit.
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|---|---|---|---|---|
| CN102644559A (en) * | 2012-05-15 | 2012-08-22 | 南京风电科技有限公司 | Wind driven generator with de-icing device and de-icing method thereof |
| CN103600845A (en) * | 2013-08-23 | 2014-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Heat channel area adjustable slat anti-icing design method |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102004060675A1 (en) * | 2004-12-15 | 2006-06-22 | Eads Deutschland Gmbh | Procedure for deicing of component in aircraft involves using electromechanical piezoelectric transducer wherein deformation of component is done by suitable electrical control of piezoelectric transducer |
| WO2007095935A2 (en) * | 2006-02-27 | 2007-08-30 | Eads Deutschland Gmbh | Aerodynamic profile for aircraft and wind energy plants and method for measuring ice thickness on an aerodynamic profile |
| WO2009077666A2 (en) * | 2007-10-22 | 2009-06-25 | Aircelle | Piezoelectric de-icing of an air inlet |
| CN101525053A (en) * | 2008-03-05 | 2009-09-09 | 哈特奇桑公司 | Anti-icing/de-icing system and method and plane using the same |
| US20100031972A1 (en) * | 2008-05-28 | 2010-02-11 | Fbs, Inc. | Ultrasonic vibration system and method for removing/avoiding unwanted build-up on structures |
| US20100096213A1 (en) * | 2007-02-20 | 2010-04-22 | Airbus France | Coating for acoustic treatment having a hot air icing processing function of frost treatment with hot air |
| CN201472669U (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 ice prevention hot air channel |
| CN202557799U (en) * | 2011-12-27 | 2012-11-28 | 东南大学 | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device |
-
2011
- 2011-12-27 CN CN201110443826.1A patent/CN102431650B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102004060675A1 (en) * | 2004-12-15 | 2006-06-22 | Eads Deutschland Gmbh | Procedure for deicing of component in aircraft involves using electromechanical piezoelectric transducer wherein deformation of component is done by suitable electrical control of piezoelectric transducer |
| WO2007095935A2 (en) * | 2006-02-27 | 2007-08-30 | Eads Deutschland Gmbh | Aerodynamic profile for aircraft and wind energy plants and method for measuring ice thickness on an aerodynamic profile |
| US20100096213A1 (en) * | 2007-02-20 | 2010-04-22 | Airbus France | Coating for acoustic treatment having a hot air icing processing function of frost treatment with hot air |
| WO2009077666A2 (en) * | 2007-10-22 | 2009-06-25 | Aircelle | Piezoelectric de-icing of an air inlet |
| CN101525053A (en) * | 2008-03-05 | 2009-09-09 | 哈特奇桑公司 | Anti-icing/de-icing system and method and plane using the same |
| US20100031972A1 (en) * | 2008-05-28 | 2010-02-11 | Fbs, Inc. | Ultrasonic vibration system and method for removing/avoiding unwanted build-up on structures |
| CN201472669U (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 ice prevention hot air channel |
| CN202557799U (en) * | 2011-12-27 | 2012-11-28 | 东南大学 | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device |
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| CN106828873B (en) * | 2017-02-15 | 2018-10-30 | 南京航空航天大学 | A kind of up-front forming method of aerofoil profile with piezoelectricity deicing function |
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