WO2012080830A2 - Systèmes et procédés de dégivrage pour avions - Google Patents

Systèmes et procédés de dégivrage pour avions Download PDF

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Publication number
WO2012080830A2
WO2012080830A2 PCT/IB2011/003082 IB2011003082W WO2012080830A2 WO 2012080830 A2 WO2012080830 A2 WO 2012080830A2 IB 2011003082 W IB2011003082 W IB 2011003082W WO 2012080830 A2 WO2012080830 A2 WO 2012080830A2
Authority
WO
WIPO (PCT)
Prior art keywords
boot
icer
aircraft
icing
sensitive adhesive
Prior art date
Application number
PCT/IB2011/003082
Other languages
English (en)
Other versions
WO2012080830A3 (fr
Inventor
Hichem Amara
Original Assignee
Aerazur S.A.
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 Aerazur S.A. filed Critical Aerazur S.A.
Publication of WO2012080830A2 publication Critical patent/WO2012080830A2/fr
Publication of WO2012080830A3 publication Critical patent/WO2012080830A3/fr

Links

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
    • B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means
    • B64D15/166—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means using pneumatic boots

Definitions

  • Embodiments of the present invention relate generally to de-icers that are used for inhibiting ice accumulation on aircraft structures.
  • Particular structures that experience atmospheric ice accumulation are the wings, tail, and engine intake, although other aircraft structures are considered within the scope of this invention.
  • Ice accumulation on aircraft structures is recognized as a serious hazard, both in flight and when the aircraft is parked on the ground.
  • solutions one is to provide anti-icing equipment, which prevents the ice from forming (and is turned on before the aircraft enters icy conditions), and second solution is to provide de-icing equipment, which is designed to remove ice after is has accumulated on the aircraft.
  • Embodiments of this invention will be described with respect to de-icing equipment, but it should be understood that it is possible to use embodiments described herein with anti-icing equipment as well.
  • a de-icing boot is an ice protection system that is installed on one or more aircraft surfaces to permit a mechanical de-icing. These boots are generally installed on the leading edges of wings because these are the areas on the aircraft that are the most likely to accumulate ice, which can severely affect the aircraft's performance in icy conditions.
  • de-icing boots may be positioned on other structures of the aircraft, and the embodiments described herein may be used on any aircraft surface.
  • one type of de-icer is a pneumatic de-icer boot that is used to safely remove ice accumulation on the external surfaces of the aircraft wing, tail, and engine intake.
  • This type of de-icer is designed with expandable layers of rubber or fabric, and as atmospheric icing occurs and ice builds up, a pneumatic system inflates the boot with compressed air. This expansion in size cracks any ice that has accumulated, and the cracked ice is then blown away by the airflow current over the wing.
  • Other de-icing systems include, but are not limited to, electrothermal heating systems and bleed air systems. Electrothermal heating usually include a heating element that uses electrical power to generate heat to cause the ice to melt or to prevent its formation. Other electrically-powered systems are known. Bleed air systems use hot air from the engine exhaust manifolds, which is routed to the leading edge of the wings, and/or horizontal and vertical tail stabilizers.
  • This system uses a PSA (pressure sensitive adhesive) technology that requires a primer to be applied over a solvent.
  • PSA pressure sensitive adhesive
  • the surface is cleaned with a cleaning solvent.
  • a coating of primer is then applied to the area that will receive the boot.
  • the release backing of the boot is removed and it is applied to the wing, typically using a roller.
  • Edge sealer or edge filler is then applied.
  • Embodiments of the invention described herein thus provide improved adhesives and methods for securing de-icer boots to an aircraft surface with safety and efficiency, without the use of a primer.
  • a device for de-icing an aircraft structure comprising a de-icing boot and a pressure-sensitive adhesive pre-applied to the de-icing boot, the pressure sensitive adhesive comprising a high-tack adhesive that can adhere the de-icing boot to the aircraft structure without use of a primer.
  • a method of applying a de-icing boot to an aircraft structure comprising (a) providing a de-icing boot having a pressure sensitive adhesive pre-applied to a lower surface thereof; (b) preparing the aircraft structure to receive the de-icing boot; (c) removing a backing covering the pressure sensitive adhesive from the de-icing boot; and (d) applying the de-icing boot directly to the aircraft structure without first applying a primer to the structure.
  • FIG. 1 shows a top plan view of one embodiment of a de-icer boot application system according to embodiments of the invention.
  • FIG. 2 shows a prior art cement de-icer boot application.
  • FIG. 3 shows a prior art primer/adhesive de-icer boot application.
  • FIG. 4 shows a first step of the prior art system of FIG. 3.
  • FIG. 5 shows a second step of the prior art system of FIG. 3.
  • FIG. 6 shows more detail of the improved embodiments provided herein.
  • FIG. 7 shows the single step of the system of FIG. 6.
  • FIG. 8 shows a schematic of the application of a pressure sensitive adhesive to a de-icer boot.
  • Embodiments of the present invention provide a pressure sensitive adhesive system that eliminates some of the above-described problems. There is provided a de- icer system that can be installed without cements or primers.
  • the de-icer system 10 includes a de-icer boot 12 that has a pressure sensitive adhesive applied thereto.
  • the de-icer boot has a lower surface 14 that may be formed of polychloroprene or any other appropriate material that forms the de-icer boot 12.
  • the polychloroprene may be combined with other materials to improve adhesive performance.
  • the polychloroprene may be mixed with a rubber component.
  • the rubber component may be a natural rubber.
  • any combination percentage is possible and within the scope of this invention, potential ranges including but not limited to about 75% polychloroprene/25% natural rubber; about 85% polychloroprene/ 15% natural rubber; about 65% polychloroprene/35% natural rubber; or about 60% polychloroprene/40% natural rubber. Generally, more polychloroprene is used than rubber, but that is not a requirement. This mixture helps the adhesive applied to the de-icer boot to obtain an excellent adherence to the boot.
  • the lower surface 14 is a portion of the de-icer boot that is in contact with a pressure sensitive adhesive (PSA) 16 that is directly pre-applied to the surface 14.
  • PSA pressure sensitive adhesive
  • the pressure sensitive adhesive 16 used in connection with this application allows the de-icer boot 12 to be installed directly to the aircraft surface, without the need for primer or any other adhesive-assisting material.
  • the system is provided with the PSA pre-applied, so the user does not have to obtain, mix, or apply adhesive.
  • the PSA used is a high performance, transfer tape made of modified adhesive based on acrylate. It should be designed or acceptable for use for heavy duty applications on smooth or textured surfaces, and on flat or curved surface.
  • the PSA should have good tack and be able to withstand and maintain its effectiveness in extreme temperature changes and other extreme conditions, such as ice, sleet, snow, high velocity wind, and rain. Desired service temperatures range from about -40°C to about +70°C, and possibly even up to +120°C or +150°C.
  • the PSA used should also exhibit good tack and immediate adhesion on aluminum and composite materials. In a particular embodiment, the PSA has a coating weight of about 350 g/m 2 .
  • the PSA is provided as a transfer tape in a roll, that can be applied directly to the de-icer boot during manufacturing, so that the boot is provided with the adhesive pre-applied.
  • the PSA has a tape thickness of less than about 0.64 mm, and in an even more particular embodiment, a thickness of about 0.35 mm (generally excluding the liner).
  • PSA One specific example of a PSA that is suitable for use in embodiments of this invention is ProLINK 350 LE, manufactured and sold my Biolink Tape Solutions. Other potential adhesives are manufactured and sold by Biolink, as well as 3M or Tesa Company. It is preferable that the PSA selected for use with the de-icer boot embodiments described herein be useable with the application of a first primer layer.
  • the PSA should have good and immediate tack to the aircraft surface.
  • the boot is first manufactured according to standard process (but there may be a mixture of the polychloroprene and natural rubber described above), providing one side as having a grained surface.
  • the de-icer boot is positioned with the grained side upward and cleaned, e.g., with isopropyl alcohol or any appropriate cleaning solvent or solution.
  • the PSA is applied to lower grained surface of the boot.
  • a protective backing on the back of the PSA layer remains in place and a steam roller may be used to ensure securement of the PSA to the boot.
  • An example of this process is shown in Figure 8.
  • the protective backing may be replaced with a branded protective backing to evidence the de-icer boot supplier, rather than the adhesive supplier.
  • the de-icer system 10 described eliminates the time consuming and environmental impact during de-icer boot installation due to leading edge priming. Instead of using a potentially long dry time primer on the leading edge surface of the aircraft in order to install the de-icer, the flash boot allows installation of the de-icer without the extra labor required to apply a primer.
  • the installation of system 10 includes first buffing and otherwise cleaning the aircraft surface to which the de-icer boot is to be applied. The de-icer boot is then applied by simply removing the backing and rolling it onto the leading edge.
  • the use of a high-tack adhesive eliminates the need for a primer required to bond the de-icer boot to the aircraft surface.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Diaphragms And Bellows (AREA)
  • Adhesives Or Adhesive Processes (AREA)

Abstract

La présente invention concerne, dans ses différents modes de réalisation, des adhésifs améliorés destinés à fixer des boudins de dégivrage à une surface d'avion de manière sûre et efficiente sans utiliser de couche primaire.
PCT/IB2011/003082 2010-12-17 2011-12-16 Systèmes et procédés de dégivrage pour avions WO2012080830A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201061459718P 2010-12-17 2010-12-17
US61/459,718 2010-12-17

Publications (2)

Publication Number Publication Date
WO2012080830A2 true WO2012080830A2 (fr) 2012-06-21
WO2012080830A3 WO2012080830A3 (fr) 2012-08-23

Family

ID=45540896

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2011/003082 WO2012080830A2 (fr) 2010-12-17 2011-12-16 Systèmes et procédés de dégivrage pour avions

Country Status (1)

Country Link
WO (1) WO2012080830A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3511384A1 (fr) * 2018-01-16 2019-07-17 Goodrich Corporation Superposition d'adhésif améliorée et procédé de fixation de dégivreurs pneumatiques

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6250587B1 (en) 1998-08-19 2001-06-26 The B. F. Goodrich Company Pressure sensitive adhesive for mounting a deicer and method for mounting thereof

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5314145A (en) * 1992-12-30 1994-05-24 The B.F. Goodrich Company Compressible nose dynamic de-icer
US6352601B1 (en) * 1994-12-27 2002-03-05 The B. F. Goodrich Company Self-adhering ice protector
US6520452B1 (en) * 2000-08-18 2003-02-18 The B. F. Goodrich Company Deicer for aircraft
US8096508B2 (en) * 2007-08-10 2012-01-17 3M Innovative Properties Company Erosion resistant films for use on heated aerodynamic surfaces

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6250587B1 (en) 1998-08-19 2001-06-26 The B. F. Goodrich Company Pressure sensitive adhesive for mounting a deicer and method for mounting thereof

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3511384A1 (fr) * 2018-01-16 2019-07-17 Goodrich Corporation Superposition d'adhésif améliorée et procédé de fixation de dégivreurs pneumatiques
US10703492B2 (en) 2018-01-16 2020-07-07 Goodrich Corporation Adhesive lay-up and method for attaching pneumatic de-icers

Also Published As

Publication number Publication date
WO2012080830A3 (fr) 2012-08-23

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