CN102431650B - Aircraft wing ultrasonic assistant hot gas associating de-icing device - Google Patents
Aircraft wing ultrasonic assistant hot gas associating de-icing device Download PDFInfo
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Abstract
The invention discloses a kind of aircraft wing ultrasonic assistant hot gas associating de-icing device, comprise aerofoil profile exterior skin, the anti-ice removal system of hot gas, super sonic HF oscillation auxiliary device, programming controller, for detecting the atmosphere temperature transducer of outer atmospheric temperature and the icing intensity signal head for detecting aerofoil profile exterior skin outside face ice layer thickness; The anti-ice removal system of hot gas comprises engine compressor, wing anti-ice chamber, the anti-icing chamber of empennage and anti-deicing hot gas feedway; The ultrasonic transducer unit that super sonic HF oscillation auxiliary device is comprised ultrasonic generator and is connected with ultrasonic generator mouth by connecting cable, programming controller controls the anti-break-make of deicing hot gas feedway and the start and stop of ultrasonic generator automatically according to temperature signal and icing intensity signal.Therefore, the present invention can remove the ice sheet of machine in aircraft flight, empennage leading edge in real time effectively, and de-icing time is short, and energy ezpenditure is low, and simultaneity factor is safe and reliable, and deicing is thorough.
Description
Technical field
The present invention relates to a kind of de-icing device, it is mainly used in the anti-deicing of the wing/empennage leading edge of aircraft, belongs to that aircraft is anti-icing, deicing field.
Background technology
Freezing is the one of the main reasons causing aircraft flight accident, especially aircraft wing, empennage leading edge freeze, profile drag can be caused to increase, lift declines, critical angle of attack reduces, and the deterioration of road-holding property and stability, the aircraft controllability under take-off and landing state can be caused especially out of control, thus cause serious aircraft accident.
For the anti-deicing of the wing in flight course, empennage, extensively adopt the anti-clearing ice technology of hot gas at present: namely refer in flight course, utilize the hot air ice-melt that aero-engine air compressor is drawn.Although the anti-clearing ice technology of this hot gas can be prevented to a certain extent, deicing, its de-icing time is long, and consumed energy is large, simultaneously because its thermal inertia is large, easily after heating zone, forms ice knurl.Therefore the aircraft anti-icing that Development of Novel is quick, efficient, energy-conservation, clearing ice technology has important using value.
Super sonic is as a kind of form of energy, when propagating in solid dielectric, compression or the extension of medium particle can be caused, cause the change of solid interior pressure, cause mechanical effect, although displacement and the speed of solid dielectric are little, but the acceleration/accel of particle is very large, and even can reach tens thousand of times of acceleration due to gravity, so large HF oscillation can produce lasting huge shearing force instantaneously at the bonding interface place of different material, make coherent substance broken, be separated.
Summary of the invention
The present invention is mainly for the deficiency of the anti-clearing ice technology of the hot gas adopted in existing aircraft flight, super sonic is utilized to have the particular characteristics of mechanical effect, in conjunction with the practical structures of aircraft wing (comprising wing, empennage), a kind of ultrasonic assistant hot gas for aircraft wing associating de-icing device is proposed.Associating deicer of the present invention is on the basis of the anti-clearing ice technology of existing hot gas, and an auxiliary super sonic high frequency oscillating apparatus, can remove the ice sheet of machine in aircraft flight, empennage leading edge in real time effectively, de-icing time is short, energy ezpenditure is low, and simultaneity factor is safe and reliable, and deicing is thorough.While ensure that the safe flight of aircraft, decrease de-icing time, greatly reduce the consumption of energy.
For realizing above technical purpose, the present invention will take following technical scheme:
A kind of aircraft wing ultrasonic assistant hot gas associating de-icing device, comprise the aerofoil profile exterior skin corresponding with aerofoil profile outer rim, the anti-ice removal system of hot gas, super sonic HF oscillation auxiliary device, programming controller, for detecting the atmosphere temperature transducer of outer atmospheric temperature and the icing intensity signal head for detecting aerofoil profile exterior skin outside face ice layer thickness; Wherein: the anti-ice removal system of described hot gas comprises engine compressor, wing anti-ice chamber, 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 arranged on flow-controlling gate on this anti-deicing hot gas delivery duct, wing anti-ice valve, empennage frost valve respectively, wing anti-ice valve is arranged between the air extractor duct of flow-controlling gate and the admission port in wing anti-ice chamber, empennage frost valve is arranged between the air extractor duct of flow-controlling gate and the admission port in the anti-icing chamber of empennage, and the admission port of flow-controlling gate is connected with the air extractor duct of engine compressor by anti-deicing hot gas delivery duct; The ultrasonic transducer unit that described super sonic HF oscillation auxiliary device is comprised ultrasonic generator and is connected with ultrasonic generator mouth by connecting cable, described ultrasonic transducer unit comprises a plurality of piezoelectric ceramic transducer, and each piezoelectric ceramic transducer is fixedly mounted on the inside face of aerofoil profile exterior skin; The temperature signal that programming controller feeds back according to atmosphere temperature transducer and the folding of ice layer thickness information automatic control flow control cock that icing intensity signal head feeds back and the start and stop of ultrasonic generator, simultaneously programming controller feed back according to icing intensity signal head ice layer thickness information robot brain wing frost valve, empennage frost valve opening.
Described aerofoil profile exterior skin comprises the wing exterior skin corresponding with wing outer rim and the empennage exterior skin corresponding with empennage outer rim, described 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.
Ultrasonic transducer unit is upper and lower symmetry arrangement along the length direction of aircraft wing exterior skin leading edge.
The shape of described piezoelectric ceramic transducer is 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.
Described ultrasonic transducer unit is at least one; The rectangular array of each ultrasonic transducer unit is uniform, and the separate setting of each ultrasonic transducer unit.
According to above technical scheme, compared with prior art, the present invention has following advantage:
1, the present invention is by adding the super sonic of some strength and frequency, and produce HF oscillation on the surface of aerofoil profile exterior skin, auxiliary hot gas prevents and kill off ice technology, can remove the ice sheet of skin-surface rapidly.With adopt merely compared with the anti-de-icing method of hot gas, too high quantity of hot air can be avoided too much to flow into anti-icing chamber, ensure that the stable performance of driving engine.
2, the present invention adopts super sonic HF oscillation to assist hot gas to prevent and kill off ice, and adopts merely compared with the anti-ice removal system of hot gas, and time of heat significantly reduces.
3, the present invention adopts super sonic HF oscillation to assist hot gas to prevent and kill off ice, and adopts merely compared with the anti-ice removal system of hot gas, and institute's energy requirement significantly reduces, and institute's energy requirement is only 1/tens of the anti-ice removal system of hot gas.Egress of heat reduces greatly.
4, the present invention adopts super sonic HF oscillation to assist hot gas to prevent and kill off ice, effectively can prevent the generation of ice knurl outside anti-ice formation.
5, present device is simple, and compact conformation is lightweight.Only need add at the inside face of aerofoil profile exterior skin and organize ultrasonic transducer more, the aerodynamic configuration of aircraft can not be affected, also additionally can not increase the too much weight of aircraft.
Accompanying drawing explanation
Fig. 1 aircraft needs the position view of anti-deicing, wherein: W is the leading edge of a wing needing anti-deicing; T is the fixed fin needing anti-deicing; S is the empennage leading edge needing anti-deicing;
Fig. 2 is aircraft wing ultrasonic assistant hot gas of the present invention associating de-icing device schematic diagram;
Ultrasonic transducer cell layout figure in the leading edge of Fig. 3 aircraft wing, wherein: (a) is lateral plan; B () is birds-eye view
The structural representation of Fig. 4 super sonic HF oscillation auxiliary device;
Wherein:
1, aerofoil profile exterior skin, 2, aerofoil profile inside panel, 3, flow-controlling gate, 4, check valve, 5, wing anti-ice chamber, 6, wing anti-ice valve, 7, the anti-icing chamber of empennage, 8, empennage frost valve, 9, engine compressor, 10, programming controller, 11, atmosphere temperature transducer, 12, icing intensity signal head, 13, ultrasonic generator, 14, connecting cable, 15, ultrasonic transducer unit.
Detailed description of the invention
Accompanying drawing discloses the structural representation of preferred embodiment involved in the present invention without limitation; Technical scheme of the present invention is explained below with reference to accompanying drawing.
As shown in Figure 1, for existing aircraft, the position of anti-deicing is generally needed to comprise leading edge of a wing W, empennage leading edge S and fixed fin T.
As shown in Figures 2 to 4, aircraft wing ultrasonic assistant hot gas of the present invention associating de-icing device, comprise the aerofoil profile exterior skin corresponding with aerofoil profile leading edge, the anti-ice removal system of hot gas, super sonic HF oscillation auxiliary device, programming controller, for detecting the atmosphere temperature transducer of outer atmospheric temperature and the icing intensity signal head for detecting aerofoil profile exterior skin outside face ice layer thickness; Wherein: the anti-ice removal system of described hot gas comprises engine compressor, wing anti-ice chamber, 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 arranged on flow-controlling gate on this anti-deicing hot gas delivery duct, wing anti-ice valve, empennage frost valve respectively, wing anti-ice valve is arranged between the air extractor duct of flow-controlling gate and the admission port in wing anti-ice chamber, empennage frost valve is arranged between the air extractor duct of flow-controlling gate and the admission port in the anti-icing chamber of empennage, and the admission port of flow-controlling gate is connected with the air extractor duct of engine compressor by anti-deicing hot gas delivery duct; The ultrasonic transducer unit that described super sonic HF oscillation auxiliary device is comprised ultrasonic generator and is connected with ultrasonic generator mouth by connecting cable, described ultrasonic transducer unit comprises a plurality of piezoelectric ceramic transducer, and each piezoelectric ceramic transducer is fixedly mounted on the inside face of aerofoil profile exterior skin; The temperature signal that programming controller feeds back according to atmosphere temperature transducer and the folding of ice layer thickness information automatic control flow control cock that icing intensity signal head feeds back and the start and stop of ultrasonic generator, simultaneously programming controller feed back according to icing intensity signal head ice layer thickness information robot brain wing frost valve, empennage frost valve opening.Described aerofoil profile exterior skin comprises the wing exterior skin corresponding with the leading edge of a wing and the empennage exterior skin corresponding with empennage leading edge, in accompanying drawing, described 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.Ultrasonic transducer unit is upper and lower symmetry arrangement along the length direction of aircraft wing exterior skin leading edge.The shape of described piezoelectric ceramic transducer is rectangular strip or discoid.In each ultrasonic transducer unit, 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.Described ultrasonic transducer unit is at least one; The rectangular array of each ultrasonic transducer unit is uniform, and the separate setting of each ultrasonic transducer unit.Wing anti-ice chamber is made up of frisket in the wing corresponding with leading edge of a wing position and the outer frisket of wing, and the anti-icing chamber of empennage is made up of frisket in the empennage corresponding with empennage leading edge position and the outer frisket of empennage.In addition, the aerofoil profile exterior skin corresponding with aerofoil profile outer rim is not limited to aerofoil profile outer rim position, and it suitably should expand to the field of aerofoil profile outer rim and aerofoil profile outer rim.
Although only adopt super sonic HF oscillation auxiliary device at the leading edge of a wing in accompanying drawing, in fact, for obtaining good anti-deicing effect, then need, in empennage leading edge, super sonic HF oscillation auxiliary device is installed.
Principle of work of the present invention is:
Programming controller 10 controls the unlatching of engine compressor outlet flow control valves 3 and the start and stop of ultrasonic generator 13 according to the outer atmospheric temperature of atmosphere temperature transducer 11 Real-Time Monitoring, once outer atmospheric temperature exceedes freezing point, engine compressor outlet flow control valves 3 is opened, now, under the control of programming controller, the icing intensity signal behavior Open valve opening that wing anti-ice valve 5 and empennage frost valve 7 provide according to icing intensity signal head 12, hot air flows to wing anti-ice chamber 5 along the direction of arrow, the anti-icing chamber 7 of empennage, along the channel flow of tail nose of wing, hot air is passing to exterior skin 1 along in the flow process of passage heat, meanwhile ultrasonic generator 13 is opened, auxiliary hot gas prevents and kill off ice, by connecting cable 14 for ultrasonic transducer unit 15 provides the high-frequency ac electric signal matched with it excitation, under the excitation of ultrasonic generator, fasteningly produce HF oscillation with the ultrasonic transducer unit of exterior skin inside face, make exterior skin inside that Light deformation occur, thus in the huge shearing force of the instantaneous generation in interface of exterior skin and ice sheet, in conjunction with the thawing effect of hot gas to ice sheet, thus the bond strength effectively overcome fast between ice sheet and exterior skin, pulverize ice sheet, ice sheet is come off.Adopt the method for the anti-deicing of ultrasonic assistant, engine compressor is only needed to introduce a small amount of hot air, melt one deck ice sheet at ice sheet and exterior skin interface, even do not need to melt, only ice sheet and outer masked bond strength are dropped to below bond strength that super sonic can overcome, utilize ultrasonic HF oscillation, the object of effective anti-deicing can be reached.In addition, the opening degree of the real-time adjust flux control cock 3 of icing thickness signal that programming controller 10 can also provide according to icing intensity signal head 12 and the power of ultrasonic generator 13, periodically can change the unlatching quantity of ultrasonic transducer unit 15 simultaneously.
As shown in Figure 3, each ultrasonic transducer unit 15 all adopts the mode be threaded to be anchored on described exterior skin 1 inside face, and along the upper and lower symmetrical array type arrangement of aircraft wing leading edge length direction.
As 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 10-20.
Claims (5)
1.
a kind of aircraft wing ultrasonic assistant hot gas associating de-icing device, is characterized in that: comprise the aerofoil profile exterior skin corresponding with aerofoil profile outer rim, the anti-ice removal system of hot gas, super sonic HF oscillation auxiliary device, programming controller, for detecting the atmosphere temperature transducer of outer atmospheric temperature and the icing intensity signal head for detecting aerofoil profile exterior skin outside face ice layer thickness; Wherein:
the anti-ice removal system of described hot gas comprises engine compressor, wing anti-ice chamber, 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 arranged on flow-controlling gate on this anti-deicing hot gas delivery duct, wing anti-ice valve, empennage frost valve respectively, wing anti-ice valve is arranged between the air extractor duct of flow-controlling gate and the admission port in wing anti-ice chamber, empennage frost valve is arranged between the air extractor duct of flow-controlling gate and the admission port in the anti-icing chamber of empennage, and the admission port of flow-controlling gate is connected with the air extractor duct of engine compressor by anti-deicing hot gas delivery duct;
the ultrasonic transducer unit that described super sonic HF oscillation auxiliary device is comprised ultrasonic generator and is connected with ultrasonic generator mouth by connecting cable, described ultrasonic transducer unit comprises a plurality of piezoelectric ceramic transducer, and each piezoelectric ceramic transducer is fixedly mounted on the inside face of aerofoil profile exterior skin;
the temperature signal that programming controller feeds back according to atmosphere temperature transducer and the folding of ice layer thickness information automatic control flow control cock that icing intensity signal head feeds back and the start and stop of ultrasonic generator, simultaneously programming controller feed back according to icing intensity signal head ice layer thickness information robot brain wing frost valve, empennage frost valve opening; The shape of described piezoelectric ceramic transducer is rectangular strip or discoid; The oscillation frequency of piezoelectric ceramic transducer is consistent with the natural frequency of aerofoil profile exterior skin.
2.
aircraft wing ultrasonic assistant hot gas associating de-icing device according to claim 1, it is characterized in that: described aerofoil profile exterior skin comprises the wing exterior skin corresponding with wing outer rim and the empennage exterior skin corresponding with empennage outer rim, described 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 claim 2, aircraft wing ultrasonic assistant hot gas associating de-icing device, is characterized in that: ultrasonic transducer unit is upper and lower symmetry arrangement along the length direction of aircraft wing exterior skin leading edge.
4.
according to claim 1, aircraft wing ultrasonic assistant hot gas associating de-icing device, is characterized in that: in ultrasonic transducer unit, the number of piezoelectric ceramic transducer is between 10-20.
5.
according to claim 1, aircraft wing ultrasonic assistant hot gas associating de-icing device, is characterized in that: described ultrasonic transducer unit is at least one; The rectangular array of each ultrasonic transducer unit is uniform, and the separate setting of each ultrasonic transducer unit.
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| CN201110443826.1A CN102431650B (en) | 2011-12-27 | 2011-12-27 | Aircraft wing ultrasonic assistant hot gas associating de-icing device |
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| CN201110443826.1A CN102431650B (en) | 2011-12-27 | 2011-12-27 | Aircraft wing ultrasonic assistant hot gas associating de-icing device |
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| CN102431650B true CN102431650B (en) | 2015-08-19 |
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| CN103963978A (en) * | 2013-02-01 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Combined Ultrasonic and graphite deicing method |
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| CN116395140B (en) * | 2023-04-27 | 2023-12-12 | 成都流体动力创新中心 | Ice prevention and removal method based on ultrasonic cavitation principle |
| CN117602077B (en) * | 2023-11-09 | 2024-06-14 | 北京北航天宇长鹰无人机科技有限公司 | Wing ice preventing and removing structure, preparation method thereof, system using wing ice preventing and removing structure and unmanned aerial vehicle |
| CN117251942B (en) * | 2023-11-17 | 2024-03-08 | 成都凯天电子股份有限公司 | Method and system for estimating airspeed, attack angle and sideslip angle of aircraft |
| CN117302522B (en) * | 2023-11-28 | 2024-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-power-consumption ultrasonic deicing method and device for flight equipment |
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