WO2010006946A1 - Dispositif et procédé destiné à empêcher la formation de givre sur des aéronefs et/ou à dégivrer des aéronefs - Google Patents

Dispositif et procédé destiné à empêcher la formation de givre sur des aéronefs et/ou à dégivrer des aéronefs Download PDF

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Publication number
WO2010006946A1
WO2010006946A1 PCT/EP2009/058483 EP2009058483W WO2010006946A1 WO 2010006946 A1 WO2010006946 A1 WO 2010006946A1 EP 2009058483 W EP2009058483 W EP 2009058483W WO 2010006946 A1 WO2010006946 A1 WO 2010006946A1
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WO
WIPO (PCT)
Prior art keywords
aircraft
laser
ice
surface region
laser beam
Prior art date
Application number
PCT/EP2009/058483
Other languages
German (de)
English (en)
Inventor
Peter Peuser
Christian Wolff
Original Assignee
Eads Deutschland Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Eads Deutschland Gmbh filed Critical Eads Deutschland Gmbh
Publication of WO2010006946A1 publication Critical patent/WO2010006946A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft

Definitions

  • the invention relates to an apparatus and a method for preventing ice formation on aircraft and / or for de-icing of aircraft.
  • Ice forms on leading edges of wings, tail units, and horizontal stabilizers when an aircraft, such as an airplane or helicopter, is flying through a cloud containing supercooled water droplets.
  • the ice forms as the supercooled water droplets of clouds touch the aircraft. This contact brings energy into the droplets and causes them to change from the liquid state to the solid state and thus to ice.
  • Ice accumulation at the leading edge (air intake area) of an engine intake causes flow problems and can lead to ice pickup.
  • Turbofan engines require a laminar flow of air at the front of the fan.
  • ice protection systems are already in use on aircraft to avoid such ice formation.
  • Most ice protection systems are designed as anti-ice systems to prevent ice formation. These are usually integrated heaters provided, which are operated with hot engine bleed air or electrically.
  • aircraft are de-iced, especially before take-off.
  • the deicing of aircraft wings both on the ground (before the flight) and during the flight is highly safety-relevant, since otherwise ice formation can lead to stalling during the flight and the aircraft is at risk of falling.
  • Such problems occur not only in aircraft, but also in other aircraft, such as helicopters.
  • De-icing means actively removing ice and snow from the wing. On the ground, this is usually done by spraying with 70 - 80 0 C hot de-icing liquids. During flight, blade edges are heated with hot bleed air or bleed air or by electric heaters in the blade edges.
  • de-icing and anti-icing measures either mean a considerable amount of work on the ground or an enormous amount of energy during the flight.
  • the use of special deicing vehicles is necessary.
  • a corresponding logistics must be established including maintenance of the deicing vehicles, duty rosters for the operators, etc.
  • the use of these de-icing vehicles is also of concern for environmental reasons.
  • the deicing fluids are usually based on ethylene glycol or propylene glycol, which are of environmental concern.
  • the corresponding conventional devices are particularly energy-consuming and require great constructive measures in the construction of the aircraft.
  • the object of the present invention is to provide an apparatus and a method with which an avoidance of ice formation as well as a removal of ice from surface regions of an aircraft with a high overall efficiency can be achieved. In particular, this should be achieved with less design effort on the aircraft than in previous de-icing / anti-icing measures.
  • a laser is used for deicing, which is designed for radiating a for heating a surface region of the aircraft, which is to be freed or kept free of ice and / or for deicing the surface area suitable laser beam.
  • This laser beam is directed at the surface area so as to heat this or water thereon for the purpose of preventing ice formation and / or to melt ice located thereon.
  • water located on the surface area is heated by absorption of the laser beam in order to avoid ice formation.
  • This can be achieved by selecting a suitable wavelength in the IR range.
  • the laser beam is optimized for absorption in ice, so that targeted the ice is heated to melting.
  • laser radiation optimized for water droplet heating, surface heating and / or ice melting can be used in a targeted manner.
  • floor-mounted and / or mobile devices for use on the ground or on special vehicles.
  • the laser is mounted on the aircraft itself, so that the device can be used to prevent ice formation and / or de-icing during operation and in particular during the flight operation of the aircraft.
  • a compact laser mounted in the exterior of any aircraft emits laser radiation directed at those surface areas of the aircraft which are critical to ice formation.
  • the laser radiation is preferably characterized by a wavelength and a power which are suitable for avoiding ice formation by deliberate heating of the surface and / or water thereon or, due to a high absorption of the laser radiation in ice, effectively melting this without damaging the surface ,
  • the invention finds particular use in aircraft such as airplanes or helicopters and can be provided by the manufacturers of such aircraft already during manufacture.
  • the device can be integrated without any great effort on any aircraft. A subsequent attachment to existing aircraft designs is easily possible.
  • Advantages of the invention and / or its advantageous embodiments are an energy-saving arrangement, a simpler construction of surface structures, a reduced weight, increased redundancy and reduced costs.
  • surface structures no special measures are needed to te branching air for the purpose of heating the surface structures provided. Also, the provision of electric heaters is unnecessary.
  • Figure 1 is a front view of a portion of an aircraft with a device for preventing ice formation and for removing ice on the example of an aircraft structure.
  • Fig. 2 is a plan view of the structure of Fig. 1;
  • Fig. 3 is a graph as a function of wavelength, measured at different temperatures in an interval of the absorption coefficient of 2 ⁇ H ice cream of 50 K, showing;
  • Fig. 4 is a graph showing the relative laser intensity I (L) as a function of the depth of penetration L (in cm) in ice;
  • 5 shows a simplified schematic illustration of a beam shaping optics for distributing the laser beam on a surface to be irradiated
  • 6 shows a schematic representation of a scanning device as an alternative device for distributing the laser beam on the surface
  • Fig. 7 is a schematic illustration of a service vehicle for ground service for an aircraft with another embodiment of the apparatus for preventing ice formation and for removing ice;
  • FIG. 8 is a schematic representation of a ground service ground station for an aircraft with another embodiment of the ice formation prevention and ice removal apparatus.
  • FIGS. 1 and 2 an aircraft 10 with a fuselage 12, a wing 14 and an engine 16 is shown as an example of an aircraft.
  • the aircraft 10 is provided with an ice prevention and / or defrosting device 20 for freeing or clearing ice surface critical areas 22 of ice.
  • the device 20 has a laser 1, a control and power supply unit 6 and a beam distribution device 24.
  • the compact laser 1 is in the outer region 2 of the aircraft - here aircraft 10 - mounted.
  • the laser 1 emits a laser beam 3, which is directed to the surface regions 22 of the aircraft, which are critical in terms of ice formation and impairment of the flight characteristics or the safe operation of the aircraft. Examples of such surface regions 22 are the airfoil leading edges 4 of the aircraft 10 or the air intake region 5 of the engine 16.
  • the laser 1 may be 2 laser, for example a diode laser, a diode pumped solid state laser or a CO. Such lasers are characterized by a large electrical characterized by optical-to-optical efficiency.
  • the laser 1 is connected to the control and power supply unit 6 for control and power supply.
  • the beam distribution device 24 serves to direct and / or distribute the laser beam 3 onto the surface region 22.
  • the distribution of the laser radiation 3 on the critical surface regions 22 can be carried out in principle in two different ways, which are illustrated in FIGS. 5 and 6, which show exemplary embodiments of the beam distribution device 24.
  • the two distribution techniques can be provided alternatively or jointly.
  • the laser beam can be shaped by means of a beam shaping optics 26 such that at least a large part, preferably all, of the radiation is distributed to the desired corresponding surface area 22.
  • the distribution is preferably as uniform as possible.
  • the laser beam can also be deflected in a temporally and spatially changing manner by means of a so-called scanning device 28 shown in FIG. 6 as a further exemplary embodiment for the beam distribution device 24 such that the relevant surface region 22 is repeatedly swept by the radiation.
  • a controlled by the control power supply device 6 deflectable mirror 30 is provided.
  • both the beam shaping optics 26 for spreading / distributing the laser beam 3 and the scanning device 28 for scanning the surface region 22 with the laser radiation spread apart are provided.
  • the laser radiation causes heating of the surface at the surface region 22.
  • the laser radiation is optimized for absorption in the water, so that on the surface is heated water.
  • the emission wavelength of the laser 1 is preferably in the infrared range.
  • the choice of such an emission wavelength has the following advantages: a) high absorption of the laser radiation at the surface of the aircraft, b) high absorption of the laser radiation in ice c) high absorption in water droplets and d) high MPE value for the laser radiation ,
  • the MPE value (English for permissible exposure) refers to the maximum permissible radiation for human (in particular eyes) and possibly also material for reasons of protection.
  • Fig. 3 the absorption coefficient of H 2 O-ice is illustrated as a function of wavelength, measured at different temperatures at intervals of 50 K.
  • the absorption coefficient of H 2 O-EiS is about 100 cm -1 at a wavelength in the region of about 2 ⁇ m.
  • the laser energy is converted into heat H 2 O Ice has a specific heat of fusion of 335 J / g
  • a laser 1 with a Power of about 3 kW completely melt a 1 mm thick layer of ice on a 1 m 2 area in less than 100 s.
  • the maximum permissible irradiation in terms of eye safety (the MPE value) in this wavelength range has a high value of 1 kW / m 2 .
  • windows in a cabin of the aircraft could be made to shield the laser radiation from the cabin.
  • FIG. 7 shows, as an example of the arrangement on a vehicle, a service vehicle 32 (defroster vehicle) which, instead of the usual defroster vehicles at an airport or the like for defrosting an aircraft - as an example, the aircraft 10 is shown again.
  • the device 20 is arranged here on a telescopic arm 34 which is designed to be movable by means of a plurality of joints. Due to the possibilities of beam steering can also be dispensed with such a telescopic arm.
  • the service vehicle 32 is much easier and with less effort than the usual deicing vehicles.
  • no tank for de-icing is sungsdorfkeiten necessary and eliminates the previously common and associated with high performance and energy demand heating the de-icing liquid to about 70-80 0 C.
  • FIG. 8 shows two examples of a stationary arrangement of the device 20 at an airport. It is a first service station 36 for deicing an aircraft - here the aircraft 10 - shown with a protruding over the bottom 38 support means 40.
  • the carrying device 40 (shown here as a kind of tower) carries the device 20 and can be rotatable and also height-adjustable, so as to be able to irradiate the upper surface of the support surface 14, for example.
  • the first service station 36 is particularly suitable for arrangement at the access routes to runways.
  • a second service station 42 shown as a second example, for deicing aircraft - e.g. Airplane 10 - the device 20 is placed sunk in the bottom 38.
  • the laser 1 radiates through a window 44 in the floor 38.
  • This second service station 42 can be arranged in or at the access paths or even at stands for aircraft at airports or the like. In the case of the latter, e.g. during the entire ground service, the formation of new ice is avoided.
  • the device 20 is embodied analogously to the aircraft-supported embodiment both in the embodiment shown in FIG. 7 and in the embodiment shown in FIG. 8, which has been described in detail above. Reference is therefore made to the above disclosure for further details.
  • Carrying device eg rotatable and height-adjustable tower

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Lasers (AREA)

Abstract

L’invention concerne un dispositif (20) et un procédé destiné à empêcher la formation de givre sur une zone superficielle (22) d’un aéronef (10) et/ou à dégivrer cette zone superficielle (22). Pour ce faire, on utilise un laser (1) qui est conçu pour envoyer sur la zone superficielle (22) un faisceau laser (3) destiné à réchauffer et/ou dégivrer la zone superficielle (22).
PCT/EP2009/058483 2008-07-14 2009-07-06 Dispositif et procédé destiné à empêcher la formation de givre sur des aéronefs et/ou à dégivrer des aéronefs WO2010006946A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008033025.6 2008-07-14
DE200810033025 DE102008033025A1 (de) 2008-07-14 2008-07-14 Vorrichtung und Verfahren zur Vermeidung von Eisbildung an Luftfahrzeugen und/oder zur Enteisung von Luftfahrzeugen

Publications (1)

Publication Number Publication Date
WO2010006946A1 true WO2010006946A1 (fr) 2010-01-21

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DE (1) DE102008033025A1 (fr)
WO (1) WO2010006946A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012010125A3 (fr) * 2010-06-23 2012-04-12 Eads Deutschland Gmbh Procédé, dispositif et ensemble pour éliminer des impuretés organiques de zones d'écoulement d'air
FR2986779A1 (fr) * 2012-10-30 2013-08-16 Aircelle Sa Ensemble d'entree d'air a degivrage infrarouge
CN105882998A (zh) * 2016-04-26 2016-08-24 郭玉 热风式快速除霜车
RU2671069C1 (ru) * 2017-12-18 2018-10-29 Публичное акционерное общество (ПАО) "Туполев" Способ предотвращения обледенения крыла летательного аппарата с использованием лазерной противообледенительной системы
US11623754B2 (en) 2017-07-31 2023-04-11 Israel Aerospace Industries Ltd. Icing detector

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010045450B4 (de) 2010-09-15 2013-04-25 Eads Deutschland Gmbh Anordnung zur Enteisung eines Oberflächenbereichs eines Luftfahrzeugs
DE102011102804A1 (de) * 2011-05-30 2012-12-06 Airbus Operations Gmbh Bordgestütztes Enteisungssystem für Luftfahrzeuge sowie Enteisungsverfahren
FR3010190B1 (fr) * 2013-08-30 2016-12-02 Thales Sa Sonde de mesure aerodynamique pour aeronef

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4900891A (en) * 1988-06-20 1990-02-13 Roger Vega Laser ice removal system
US5823474A (en) * 1996-09-05 1998-10-20 Sunlase, Inc. Aircraft ice detection and de-icing using lasers
US6206325B1 (en) * 1998-09-18 2001-03-27 Sunlase, Inc. Onboard aircraft de-icing using lasers

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4900891A (en) * 1988-06-20 1990-02-13 Roger Vega Laser ice removal system
US5823474A (en) * 1996-09-05 1998-10-20 Sunlase, Inc. Aircraft ice detection and de-icing using lasers
US6206325B1 (en) * 1998-09-18 2001-03-27 Sunlase, Inc. Onboard aircraft de-icing using lasers

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012010125A3 (fr) * 2010-06-23 2012-04-12 Eads Deutschland Gmbh Procédé, dispositif et ensemble pour éliminer des impuretés organiques de zones d'écoulement d'air
FR2986779A1 (fr) * 2012-10-30 2013-08-16 Aircelle Sa Ensemble d'entree d'air a degivrage infrarouge
CN105882998A (zh) * 2016-04-26 2016-08-24 郭玉 热风式快速除霜车
US11623754B2 (en) 2017-07-31 2023-04-11 Israel Aerospace Industries Ltd. Icing detector
RU2671069C1 (ru) * 2017-12-18 2018-10-29 Публичное акционерное общество (ПАО) "Туполев" Способ предотвращения обледенения крыла летательного аппарата с использованием лазерной противообледенительной системы

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DE102008033025A1 (de) 2010-05-06

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