CN202449211U - Novel anti-icing and de-icing device for airplane airfoil - Google Patents
Novel anti-icing and de-icing device for airplane airfoil Download PDFInfo
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- CN202449211U CN202449211U CN2011205540224U CN201120554022U CN202449211U CN 202449211 U CN202449211 U CN 202449211U CN 2011205540224 U CN2011205540224 U CN 2011205540224U CN 201120554022 U CN201120554022 U CN 201120554022U CN 202449211 U CN202449211 U CN 202449211U
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- ultrasonic generator
- piezoelectric ceramic
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Abstract
The utility model discloses a novel anti-icing and de-icing device for an airplane airfoil. The novel anti-icing and de-icing device comprises skin, a programmable controller, an atmosphere temperature sensor, and an icing intensity announciator; ultrasonic de-icing unit modules are fixedly arranged on the inner surface of the skin; each ultrasonic de-icing unit module comprises a plurality of piezoelectric ceramic transducer; each piezoelectric ceramic transducer is connected with an ultrasonic generator through a connecting cable; the ultrasonic generator is connected with a power supply; and the programmable controller controls the starting/stopping of the ultrasonic generator according to a temperature signal fed back by the atmosphere temperature sensor, and also controls the power of the ultrasonic generator and the running number of the ultrasonic de-icing unit modules according to the thickness signal of ice layers, which is fed back by the ice intensity announciator. Therefore, the novel anti-icing and de-icing device can effectively remove the ice layers on the surfaces of aerofoils and the front edge of an empennage during running process of an airplane in real time, is high in efficiency and saves energy, and is safe and reliable, can remove ice completely and guarantee the flying safety of the airplane.
Description
Technical field
The utility model relates to a kind of anti-icing and de-icing device, and especially a kind of anti-icing, deicer that is used for aircraft aerofoil profile (wing/empennage) leading edge belongs to aircraft deicing, anti-icing field.
Background technology
It is the one of the main reasons that causes the aircraft flight accident that ice and snow weather causes aircraft to freeze, and nearly according to statistics 9% aircraft accident causes by freezing.When aircraft flies under the state of freezing, flight quality and airworthiness will receive very big influence.Freezing not only to increase the weight of aircraft, and reduce the efficient of screw propeller, and then cause the driving engine thrust available to reduce, and the meeting disturbing flow, cause resistance to increase lift divergence.Icing meeting on wing, empennage and the controlsurface destroys the flow pattern on the aerofoil, causes stalling speed to increase, thereby causes aircraft accident.
For reducing the influence of freezing, increase the margin of safety of aircraft, for the anti-deicing of aircraft wing, empennage to aircraft flight; What extensively adopt at present is the anti-deicing technology of hot gas, and promptly in the aircraft flight process, the hot air that utilizes the aero-engine air compressor to draw carries out ice-melt; Though this anti-deicing technology can be prevented to a certain extent, deicing, its deicing time is long, and consumed energy is big; Because its thermal inertia is big, form the ice knurl easily at the back in the heating zone simultaneously.Therefore, for the flight safety of aircraft, in-depth study aircraft anti-icing, deicing technology seem particularly important further.
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.
The utility model content
The utility model is primarily aimed in the existing aircraft flight process online anti-icing, and the deficiency of deicing technology utilizes super sonic to have the particular characteristics of mechanical effect, in conjunction with the practical structures of aircraft aerofoil profile, proposes a kind of novel anti-icing and de-icing device that is used for the aircraft aerofoil profile.This device adopts super sonic HF oscillation anti-icing and deicing, can remove the ice sheet of the leading edge of a wing in the aircraft flight process in real time effectively, and energy-efficient, safe and reliable, deicing is thorough, has guaranteed the flight safety of aircraft effectively.
For realizing above technical purpose, the utility model will be taked following technical scheme:
A kind of novel anti-icing and de-icing device that is used for the aircraft aerofoil profile; Comprise with the corresponding covering in leading edge of a wing position, programming controller, be used to the icing intensity signal head that detects the atmosphere temperature transducer of ambient atmosphere ambient temperature and be used to detect covering outside face ice layer thickness; The inside face fixed installation super sonic deicing unit module of said covering; This super sonic deicing unit module comprises a plurality of piezoelectric ceramic transducers; And each piezoelectric ceramic transducer is connected with ultrasonic generator after all being connected in parallel through connecting cable, and ultrasonic generator then is connected with power supply; Said programming controller is according to the unlatching/stop of temperature signal that atmosphere temperature transducer fed back control ultrasonic generator, and the power of the ice layer thickness signal control ultrasonic generator that fed back according to the icing intensity signal head of programming controller and the operation quantity of super sonic deicing unit module.
Each piezoelectric ceramic transducer is uniformly distributed with along the rectangular array of the length direction of covering.
Said piezoelectric ceramic transducer is the rectangular strip PZT (piezoelectric transducer) or is discoid PZT (piezoelectric transducer).
According to above technical scheme, compared with prior art, the utility model can be realized following beneficial effect:
1, the utility model can carry out the actv. deicing in real time: through adding the super sonic of certain intensity and frequency, produce HF oscillation on the aircraft outer skin surface, moment is in the very high power density of the local generation of covering; The instantaneous adhesion strength that overcomes ice sheet at skin-surface; Destroy the ice sheet structure, ice sheet is come off, thereby effectively remove the skin-surface ice sheet; Compare with electro-thermal deicing; Need not to melt ice sheet, institute's energy requirement significantly reduces, and institute's energy requirement approximately is merely 1/tens of electric ice removal system and arrives one of percentage.
2, the utility model equipment is simple, and compact conformation is in light weight, only adds many group ultrasonic transducers at the covering inside face, can not influence the aerodynamic configuration of aircraft, also can the too much weight of additive incrementation aircraft.
3, the utility model utilizes the broken ice sheet of mode of super sonic HF oscillation, makes ice sheet separate with skin-surface, need not to melt ice sheet, de-icing method such as electric deicing therefore can not occur and outside preventing the ice formation, form and stay the situation of icing knurl.
Description of drawings
Fig. 1 is the novel anti-icing and de-icing device scheme drawing that the utility model is used for the aircraft aerofoil profile;
Fig. 2 is the novel anti-icing and de-icing device operational system figure that the utility model is used for the aircraft aerofoil profile;
Fig. 3 is the structural representation of the utility model super sonic deicing unit module, among Fig. 3: (a) rectangular strip PZT (piezoelectric transducer) deicing unit module, (b) discoid PZT (piezoelectric transducer) deicing unit module;
Among Fig. 1-3,1, covering, 2, ultrasonic generator, 3, connecting cable, 4, super sonic deicing unit module, 5, programming controller, 6, atmosphere temperature transducer, 7, the icing intensity signal head, 8, ice sheet.
The specific embodiment
Accompanying drawing discloses the structural representation of the related preferred embodiment of the utility model without limitation; Below will combine accompanying drawing that the technical scheme of the utility model at length is described.
Shown in Fig. 1 to 3; The said novel anti-icing and de-icing device that is used for the aircraft aerofoil profile of the utility model; Comprise with the corresponding covering in leading edge of a wing position, programming controller, be used to the icing intensity signal head that detects the atmosphere temperature transducer of ambient atmosphere ambient temperature and be used to detect covering outside face ice layer thickness, atmosphere temperature transducer, icing intensity signal head are installed in the outside face of covering; The inside face fixed installation super sonic deicing unit module of said covering; The utility model adopts the rivet ways of connecting to be anchored on the covering inside face; This super sonic deicing unit module comprises a plurality of piezoelectric ceramic transducers; And each piezoelectric ceramic transducer all is connected with ultrasonic generator through connecting cable, and each piezoelectric ceramic transducer is uniformly distributed with along the rectangular array of the length direction of covering simultaneously; Ultrasonic generator then is connected with power supply; Said programming controller is according to the unlatching/stop of temperature signal that atmosphere temperature transducer fed back control ultrasonic generator, and the power of the ice layer thickness signal control ultrasonic generator that fed back according to the icing intensity signal head of programming controller and the operation quantity of super sonic deicing unit module.The described anti-icing and de-icing device of the utility model mainly is the anti-deicing operation that is used for the leading edge of a wing; Therefore, piezoelectric ceramic transducer need be installed in wing/empennage leading edge position at least, simultaneously; Still piezoelectric ceramic transducer need be installed in the general leading edge of a wing neighborhood; Be the described and corresponding covering in leading edge of a wing position of the utility model, be not limited to wing outer rim position, it should suitably expand to the field of wing outer rim and wing outer rim.
The principle of work of the utility model is:
At first, programming controller 5 is according to the start and stop of the outer atmospheric temperature control ultrasonic generator 2 of atmosphere temperature transducer 6 monitoring in real time.In case outer atmospheric temperature surpasses freezing point; Programming controller 5 self-opening ultrasonic generators 2, the power of the icing thickness signal real-time regulated ultrasonic generator that provides according to icing intensity signal head 7 simultaneously and the working quantity of super sonic deicing unit module 4.Ultrasonic generator provides the high-frequency alternating current that is complementary with it signal excitation through connecting cable 3 for super sonic deicing unit module 4; Super sonic deicing unit module 4 is made up of a plurality of piezoelectric ceramic transducers, and under the excitation of ultrasonic generator 2, piezoelectric ceramic transducer produces HF oscillation; Make covering inside that little distortion take place; Thereby in the exterior skin 1 instantaneous at the interface generation great shear forces with ice sheet 8, and the piezoelectric ceramic transducer unit is converted into mechanical energy with electric energy in a short period of time, can be in anti-icing zone locally produces very big energy density; Its energy density substantially exceeds other mechanical deicing's methods; Thereby effectively overcome the bond strength between ice sheet and the exterior skin, pulverize ice sheet, make ice sheet come off.Thereby reach the purpose of effectively anti-deicing.
In addition, shown in Fig. 3 (a) and Fig. 3 (b), super sonic deicing unit module 4 is with respect to a shunt circuit, wherein each the shared excitation power supply of piezoelectric ceramic transducer, and each transducer service conditions is consistent; Super sonic deicing unit module 4 can be the rectangular strip PZT (piezoelectric transducer) deicing unit module shown in Fig. 3 (a), also can be the discoid PZT (piezoelectric transducer) deicing unit module shown in Fig. 3 (b).Be matrix form between the single piezoelectric ceramic transducer and arrange, transmitting frequency is fixed and is complementary with the natural frequency of covering, in addition, and single PZT (piezoelectric transducer) deicing unit module adjustable power.
Claims (3)
1. novel anti-icing and de-icing device that is used for the aircraft aerofoil profile; Comprise and the corresponding covering in aerofoil profile leading edge position; It is characterized in that: also comprise programming controller, be used to the icing intensity signal head that detects the atmosphere temperature transducer of ambient atmosphere ambient temperature and be used to detect covering outside face ice layer thickness; The inside face fixed installation super sonic deicing unit module of said covering; Said piezoelectric ceramic transducer unit module comprises a plurality of piezoelectric ceramic transducers, and each piezoelectric ceramic transducer is connected with ultrasonic generator after all being connected in parallel through connecting cable, and ultrasonic generator then is connected with power supply; Said programming controller is according to the unlatching/stop of temperature signal that atmosphere temperature transducer fed back control ultrasonic generator, and the power of the ice layer thickness signal control ultrasonic generator that fed back according to the icing intensity signal head of programming controller and the operation quantity of super sonic deicing unit module.
2. according to the said novel anti-icing and de-icing device that is used for the aircraft aerofoil profile of claim 1, it is characterized in that: each piezoelectric ceramic transducer is uniformly distributed with along the rectangular array of the length direction of covering.
3. according to the said novel anti-icing and de-icing device that is used for the aircraft aerofoil profile of claim 1, it is characterized in that: said piezoelectric ceramic transducer is the rectangular strip PZT (piezoelectric transducer) or is discoid PZT (piezoelectric transducer).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205540224U CN202449211U (en) | 2011-12-27 | 2011-12-27 | Novel anti-icing and de-icing device for airplane airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205540224U CN202449211U (en) | 2011-12-27 | 2011-12-27 | Novel anti-icing and de-icing device for airplane airfoil |
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| Publication Number | Publication Date |
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| CN202449211U true CN202449211U (en) | 2012-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011205540224U Expired - Fee Related CN202449211U (en) | 2011-12-27 | 2011-12-27 | Novel anti-icing and de-icing device for airplane airfoil |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490905A (en) * | 2011-12-27 | 2012-06-13 | 东南大学 | Novel anti-icing and deicing device for airfoils of airplane |
| CN103806401A (en) * | 2014-02-25 | 2014-05-21 | 清华大学 | Road surface de-icing device for military airfield |
| CN110077600A (en) * | 2019-05-16 | 2019-08-02 | 山东大学 | A kind of Hydrodynamic cavitation wing de-icing device |
| CN110341965A (en) * | 2019-07-24 | 2019-10-18 | 山东大学 | A kind of device carrying out wing deicing based on cavitation |
| CN110450961A (en) * | 2019-08-01 | 2019-11-15 | 山东大学 | A kind of wing and flight instruments using the anti-deicing of ultrasonic Hydrodynamic cavitation |
| CN110654551A (en) * | 2019-09-30 | 2020-01-07 | 山东大学 | Aircraft deicing device and aircraft wing are prevented to aircraft based on hydrodynamic cavitation principle |
| CN110723294A (en) * | 2018-07-16 | 2020-01-24 | 波音公司 | Aircraft anti-icing system and method of making same |
| CN114616060A (en) * | 2019-09-25 | 2022-06-10 | 里尔大学 | Method for melting object by ultrasonic wave |
-
2011
- 2011-12-27 CN CN2011205540224U patent/CN202449211U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490905A (en) * | 2011-12-27 | 2012-06-13 | 东南大学 | Novel anti-icing and deicing device for airfoils of airplane |
| CN103806401A (en) * | 2014-02-25 | 2014-05-21 | 清华大学 | Road surface de-icing device for military airfield |
| CN110723294A (en) * | 2018-07-16 | 2020-01-24 | 波音公司 | Aircraft anti-icing system and method of making same |
| CN110077600A (en) * | 2019-05-16 | 2019-08-02 | 山东大学 | A kind of Hydrodynamic cavitation wing de-icing device |
| CN110077600B (en) * | 2019-05-16 | 2021-04-09 | 山东大学 | Deicing device is prevented to hydrodynamic cavitation wing |
| CN110341965A (en) * | 2019-07-24 | 2019-10-18 | 山东大学 | A kind of device carrying out wing deicing based on cavitation |
| CN110450961A (en) * | 2019-08-01 | 2019-11-15 | 山东大学 | A kind of wing and flight instruments using the anti-deicing of ultrasonic Hydrodynamic cavitation |
| CN114616060A (en) * | 2019-09-25 | 2022-06-10 | 里尔大学 | Method for melting object by ultrasonic wave |
| CN110654551A (en) * | 2019-09-30 | 2020-01-07 | 山东大学 | Aircraft deicing device and aircraft wing are prevented to aircraft based on hydrodynamic cavitation principle |
| CN110654551B (en) * | 2019-09-30 | 2021-01-26 | 山东大学 | Aircraft deicing device and aircraft wing are prevented to aircraft based on hydrodynamic cavitation principle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120926 Termination date: 20121227 |