WO2024033345A1 - Artefact avec film chauffant - Google Patents

Artefact avec film chauffant Download PDF

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Publication number
WO2024033345A1
WO2024033345A1 PCT/EP2023/071907 EP2023071907W WO2024033345A1 WO 2024033345 A1 WO2024033345 A1 WO 2024033345A1 EP 2023071907 W EP2023071907 W EP 2023071907W WO 2024033345 A1 WO2024033345 A1 WO 2024033345A1
Authority
WO
WIPO (PCT)
Prior art keywords
heater film
fiber reinforced
reinforced composites
group
artefact
Prior art date
Application number
PCT/EP2023/071907
Other languages
English (en)
Inventor
Liberata Guadagno
Luigi Vertuccio
Raffaele Longo
Roberto PANTANI
Giuseppe Stefano Gallo
Generoso Iannuzzo
Salvatore Russo
Augusto Albolino
Diego De Luca
Original Assignee
Leonardo S.P.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 Leonardo S.P.A. filed Critical Leonardo S.P.A.
Publication of WO2024033345A1 publication Critical patent/WO2024033345A1/fr

Links

Classifications

    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/10—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor
    • H05B3/12—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
    • H05B3/14—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
    • H05B3/146—Conductive polymers, e.g. polyethylene, thermoplastics
    • 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
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
    • H05B3/34—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2203/00—Aspects relating to Ohmic resistive heating covered by group H05B3/00
    • H05B2203/013—Heaters using resistive films or coatings
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2214/00—Aspects relating to resistive heating, induction heating and heating using microwaves, covered by groups H05B3/00, H05B6/00
    • H05B2214/02—Heaters specially designed for de-icing or protection against icing
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2214/00—Aspects relating to resistive heating, induction heating and heating using microwaves, covered by groups H05B3/00, H05B6/00
    • H05B2214/04—Heating means manufactured by using nanotechnology

Definitions

  • the present invention relates to artefacts provided with anti-icing means, and intended in particular, but not exclusively, for aeronautical applications.
  • meteorological and/or aerodynamic factors are factors that contribute to ice formation on an aircraft, among which are meteorological and/or aerodynamic factors.
  • the ice on these components may cause changes in their shape, negatively affecting airflow across the surface and hindering the ability to create lift or maintain the aircraft control.
  • An object of the present invention consists in the development of new ice protection systems of artefacts, such as flat and curved Carbon Fiber Reinforced Composites (CFRCs) and Glass Fiber Reinforced Composites (GFRCs)panels.
  • CFRCs Carbon Fiber Reinforced Composites
  • GFRCs Glass Fiber Reinforced Composites
  • Figure 1 illustrates the chemical formulae of exemplary thermoplastic polymers usable in a heater film of an artefact of the invention
  • Figure 2 illustrates on the top optical images of film heaters (the first two films differ from each other in the number of graphene layers in the graphitic layers, the thermoplastic matrix is the same (PVA)), and on the bottom optical images of film heaters showing the film flexibility;
  • Figure 3 is a schematic representation of a functionalization process in the film heater preparation
  • Figure 4 illustrates - a) the electrical conductivity of the composite PVA (50% filler) for different molecular weight: 30-70 kDa (Low Molecular Weight (LMW)), 89-98 kDa (Medium Molecular Weight (MMW)), 146-186 kDa (High Molecular Weight (HWM)); b) the Electrical Conductivity of LMW composite of PVA at different amounts of conductive filler;
  • LMW Low Molecular Weight
  • MMW Medium Molecular Weight
  • HWM High Molecular Weight
  • Figure 5 illustrates the temperature profiles, as a function of time, for 3, 4 different values of applied constant voltage (Figs. 5a, 5b) and temperature variation (AT) as a function of the applied power (Fig. 5c), for the heating films obtained with two different molecular weight loaded with 60% of filler;
  • Figure 6 illustrates the temperature profiles, as a function of time, for 4 different values of applied constant voltage (Figs, a, b and c) and Temperature variation (AT), for the heating films obtained with two different molecular weight loaded with 50% of filler;
  • Figure 7 shows optical images of panel 1 and panel 2
  • Figure 9 refers to the temperature detected in the center and at the edges of the sample, at the copper contacts and the evolution of the electrical resistance as a function of the heating time for an applied voltage of 3.0 volt;
  • Figure 10 refers to the temperature detected in the center and at the edges at the copper contacts and the evolution of the electrical resistance as a function of the heating time for an applied voltage of 4.0 volt;
  • Figure 11 refers to a summary table of the electrical and thermal parameters related to the tests carried out and the AT vs. the applied power;
  • Figure 13 refers to the temperature detected in the center and at the edges of the sample, at the copper contacts and the evolution of the electrical resistance as a function of the heating time for an applied voltage of 5.0 volt;
  • Figure 14 refers to the temperature detected in the center and at the edges at the copper contacts and the evolution of the electrical resistance as a function of the heating time for an applied voltage of 6.0 volt;
  • Figure 15 refers to the temperature curves vs applied voltage related to the tests carried out on Panel 2 (on the left side); table of the electrical parameters and thermal parameters (on the right side). The table shows the maximum temperatures reached at 90 s (first region of the linear section) and at 5 minutes (second region - at the origin of the "almost" plateau);
  • Figure 16 is a summary table of electrical and thermal parameters related to the tests carried out and the AT vs. the applied power;
  • Figure 17 illustrates a possible configuration of a leading edge divided in different sectors, each having a different thickness of the film heater
  • Figure 18 relates to photos showing the consistent damages where repair actions involve the replacement of CFs or GFs fabric (impregnated with resin) on aircraft under stopping conditions;
  • Figure 19 illustrates the execution of the repairs mentioned with regard to figure 18
  • Figure 20 illustrates the bonding procedure of two edges of a heating film in PVA LMW loaded with 60% of filler
  • Figure 21 refers to the heating performance of a repaired heating film
  • Figure 22 illustrates the film heater repaired and drilled again after the first repair (on the top) and the results of the heating test (on the bottom);
  • Figure 23 relates to images showing the adaptability of the film heater to the curvature radius of the leading edge.
  • the flexible film heater is a very thin and light film composed in some embodiments of: a) a polymeric matrix such as a thermoplastic polymeric matrix containing polar groups (compatible with the thermosetting resin used for aeronautical panels), or a thermosetting polymeric matrix optionally functionalized with elastomeric nanodomains.
  • a thermoplastic polymeric matrix containing polar groups are polyvinyl alcohol, vinyl alcohol-based thermoplastic resins, vinyl alcohol copolymers, copolymer of vinyl alcohol and butanediol, alcohol/vinyl- acetate copolymer, polymeric derivatives of cellulose (such as for example carboxymethyl cellulose) and any combinations thereof.
  • thermosetting polymeric matrix examples include epoxy, polyurethane, polyimide, polyester, phenolic, bismaleimides, vinyl esters, and polyamides, optionally functionalized with elastomeric nanodomains.
  • Non-limiting examples of electrically conductive carbon-based nanoparticles are electrically conductive carbon-based nanoparticles of the heater film are selected from the group consisting of carbon nanotubes, carbon nanofibers, exfoliated graphite nanoparticles, expanded graphite nanoparticles, graphene-based nanoparticles and mixtures thereof.
  • a preferred embodiment of the polymer matrix of the flexible film heater is a thermoplastic polymer matrix.
  • thermoplastic polymers can be used having the characteristic above mentioned. Some examples of chemical structures are shown in Figure 1.
  • the thermoplastic matrix can be composed of polyvinyl alcohol, here named with the acronym PVA.
  • PVA polyvinyl alcohol
  • Polymer matrices such as the highly biodegradable, hydrophilic, amorphous Butendiol/Vinyl Alcohol/Vinyl-Acetate copolymer (Nichigo G-Polymer - grade OKS 8049), commercially available (provided from Nippon Gohsei Synthetic Chemical Industry, Europe GmbH, Dusseldorf, Germany) and here named with the acronym HAVOH can be also used.
  • Useful polymeric matrices can also be characterized by groups such as carbonyl groups or ester groups and/or polar groups such as -NH (see Figure 1c).
  • the electrically conductive nanofiller is made of carbon-based nanoparticles, preferably graphene-based nanoparticles or very thin graphitic layers of nanometric thickness with an average value preferably not higher than 25 nm, and a large surface area, for which the optimized value of the aspect ratio is preferably higher than 1200.
  • Optical images of some of these films are shown in Figure 2. In particular, it is possible to observe the film flexibility in the images on the bottom of figure 2.
  • the crosslinking agent is among Urea derivatives and is more preferably characterized by at least two carbonyl groups in order to crosslink the polymer chains (es. 1,3 DBA, uric acid, barbituric acid, murexide, etc).
  • Examples 1-2 refer to the preparation of highly flexible film heaters.
  • the crosslinking agent "barbituric acid” has been used.
  • the polymer is dissolved in hot water (60- 100 °C) for 1-2 hours under magnetic stirring till the solution is completely clear.
  • the resulting polymeric solution is around 0.4% in weight of polymer to solvent.
  • a percentage of the graphitic layers is added to the polymeric solution, which is ultra-sonicated for one hour at room temperature.
  • the crosslinking agent is added to the solution (generally 20% in weight with respect to polymer amount) and stirred at room temperature for 30 minutes.
  • the film is directly obtained by the evaporation of water via solvent casting.
  • the evaporation time can be tuned by increasing, on the exposed surface the temperature value, or removing the humidity of the room.
  • the film is annealed at 1-3 bar around 140 °C for one hour. This step is done to remove voids due to evaporation and to allow the crosslinking reactions of the urea- based agent with the matrix, that is thermally activated during the annealing process.
  • the same procedure used in the previous examples can be used using as polymeric matrix HOVOH with 50 or 60% by weight of graphitic layers.
  • the films obtained by the casting process are flexible and highly homogeneous as the unfunctionalized ones.
  • the electrical conductivity of the functionalized systems, compared to the unfunctionalized one, is similar, proving that the crosslinking does not limit the applicability of the film heater.
  • the values of electrical conductivity are shown in Table 1 with an amount of graphitic layers of 50% by weight.
  • the amount by weight of graphitic layers can be between 20% and 80% and more preferably between 30% and 60%.
  • adding conductive filler in the composite affects also the mechanical properties of the materials, that are crucial for having a flexible system.
  • the electrical conductivity of the composite is sensitively affected by the molecular weight of the polymeric matrix. For this reason, lower molecular weight polymers guarantee higher electrical conductivities (that are favorable if limited voltages are available), whereas it is possible to choose higher molecular weights if higher voltages are available.
  • Figure 5 shows the Temperature Profiles, as a function of time, for 3, 4 different values of the constant applied voltage (Figs, a and b) and the Variation in temperature (AT) as a function of the applied power (Fig. c), for the heating films obtained with the two different molecular weights.
  • the heating measurements were conducted by applying increasing constant voltages.
  • the voltage increase causes an increase in the temperature of plateau. If we consider, not the temperature reached, but the variation in temperature with respect to the initial one (AT), with the same power, the heat obtained for the different samples are similar. As expected, the dissipative effect is a function of the applied power.
  • the two film heaters (based on PVA 30-70 kDa and PVA 89-98 kDa) were also tested, through electrical measurements in direct current (DC), with the aim of evaluating the voltage values and the powers necessary to perform a heating up to about 100 ° C.
  • the heating measurements were conducted by applying constant and increasing voltages. The temperature and current profiles during heating are shown in Figure 6.
  • Table 3 Electrical parameters and thermal measurements of the film heater based on the molecular weight between 30-70 kDa loaded with 50% wt/wt of filler.
  • Table 4 Electrical parameters and thermal measurements of the film heater based on the molecular weight between 89-98 kDa loaded with 50% wt/wt of filler.
  • Tables 3-4 allow observing that efficient heating is reached for both samples in a very short time (also less than a minute).
  • the film heaters here described have been tested using a two-stage curing cycle (typically of aeronautical structures), for which the second stage can be also carried out up to 180 °C for 3 hours.
  • the film heaters manifest high thermal stability and a melting temperature which can reach the value of 268 °C (depending on the molecular weight of the polymeric matrix and the amount of nanofiller)
  • CFRCs and GFRCs panels having integrated the film heater are specifically designed for application in aeronautics (aircraft’s wings - leading edges-, engine cowlings, fuselage, etc).
  • aeronautics aircraft’s wings - leading edges-, engine cowlings, fuselage, etc.
  • transport sectors automotive, rail, etc.
  • wind energy wind turbines
  • offshore structures and the civil engineering sector (assembled structures for bridges, footbridges, etc.).
  • aircraft are designed to have anti/de-icing facilities activable in-flight.
  • the invention here proposed can be applied both before (aircraft ground de/anti Icing procedures) and after take-off (aircraft in flight).
  • the present invention proposes smart high-efficient anti-icing/de-icing composites, which can also be characterized by feature ice-tailored power output performance. It is well known that ice accretion on fast-moving complex surfaces like aircraft wings (with more severe conditions on the shorter radius parts) is generally uneven and varies with the variable flow field. The possibility to apply a new approach adaptive to uneven and variable ice accretion, compared to current pneumatic or thermal metal resistance systems (current wire heating pad systems, etc.), leads to further energy savings.
  • the new anti/de-icing technology allows manufacturing CFRPs or GFRPs capable to combine concomitant and/or consequential benefits, with respect current Anti/de-icing solutions, as described hereafter for different panels configurations.
  • the insulation can be performed with a suitable conventional insulating spray or through the use of insulated electrodes (on the opposite side to the part that comes into contact with the film heater).
  • Figure 7 shows optical images of Panel 1 and Panel 2.
  • Panel 1 (belonging to the type of mixed panels composed of both carbon fiber fabrics and glass fiber fabrics) was made by isolating the "heater film” through its interposition between two glass fiber fabrics so as to isolate the entire heating film from the carbon fiber fabrics.
  • Panel 2 (belonging to the type of panels composed only of fiberglass fabrics) was manufactured by positioning the film heater in the center of the fiberglass cloths. In this case, the insolation of the electrode adhered to the film heater is not necessary.
  • Panels 1 and 2 have been cured through the typical curing cycle applied by Leonardo to loadbearing components of primary structures.
  • thermocouples were carried out at room temperature, applying different voltage values for a time of 30 minutes.
  • a survey was carried out on the temperature values reached in correspondence with the different applied voltages and the positioning of the thermocouples.
  • thermo-chamber Furthermore, the heating of the analysed panels, monitored through a thermo-chamber, evidenced a satisfying homogeneity of the temperature over the entire sample surfaces.
  • Figure 11 is a summary table of the electrical and thermal parameters related to the tests carried out; AT vs applied power. The value of AT has been determined considering the difference of temperature detected by the thermocouple at the center of the sample.
  • Figure 16 is a summary table of the electrical and thermal parameters related to the tests carried out and the AT vs. the applied power.
  • panel 2 exhibits a fairly fast response when considering the applied power densities. If we consider the temperature profiles in the linear section, it can be seen that about 70-80% of the maximum temperature value is reached for times less than 3 minutes. For example, for an applied voltage of 8 Volts (2676.1 W/m 2 ), a temperature of 90° C is reached in 90 seconds with a heating rate of approximately 84 °C/min.
  • thermo-chamber Furthermore, the heating of the analyzed panels, monitored through a thermo-chamber, evidence a satisfying homogeneity of the temperature over the entire sample surfaces.
  • Table 5 are shown the electrical and thermal parameters detected for Panel 2 applying an alternate current (The AC measurements have been led at 400 Hz)
  • Table 5 Electrical parameters and thermal measurements detected for panel 2. Tests performed in A.C. b) Ability to obtain panels with high homogeneity in the temperature of the panels (see examples) without applying wire resistors. Furthermore, unlike wire resistors, the proposed solution preserves the resin from the criticality of the thermal degradation in the areas of the interface between resin and wire. c) Possibility of applying modulated solutions. For example, on the leading edges, it is possible to make adaptative the heating performance by choosing a modular solution with film heaters of different thicknesses suitably placed in the layers of curved panels (or directly applied as treated coatings).
  • Figure 17 highlights that using the same power supply voltage (the same type of current), it is possible to reach different temperatures (for example on different parts of a leading edge) only by choosing the suitable thicknesses and a modular configuration.
  • the film heater can be placed between different layers or directly as a coating.
  • the layers are among CF woven, GF woven, hybrid materials, metallic or metal alloy materials, etc.
  • a generic example, where it is possible to have layers of different materials that integrate the film heater is shown in figure 17.
  • Fig. 17 is merely exemplificative and does not exclude further possible suitable configuration designs.
  • Figure 17 highlights the possibility to apply an adaptative, modular solution. It is possible to electrically power the heated profile with the same type of current; hence the heating element are divided into different sectors with different thermal power densities. The thickness of the film should allow managing the different power densities. This allows reducing part of electrical components that increase the aircraft weight and push towards aircraft profiles conditioned by the need for weight balance. d) Weight savings associated with the absence of metal resistors or pneumatic systems (deicing boot systems), different consequential benefits are expected. benefits
  • the integration of the green flexible film heater in CFRCs and GFRCs panels is advantageous in order to confer them the function of being able to activate anti-deicing or de-icing through electrical power.
  • This film can be placed between the plies of carbon fibers or glass fiber fabrics.
  • the film heater can be placed under the last CF or GF ply (the ply exposed to the elements). There is no need to use adhesive layers to bind it to the Carbon Fiber (CF) or Glass fiber (GF) fabrics impregnated with thermosetting resin. This last occurrence greatly facilitates the manufacturing process.
  • the heating element film heater
  • the active layer film heater
  • the curing process which can be carried out in autoclave or out of autoclave
  • the current repair processes can be implemented to add to the restoration of structural properties also the restoration of functional properties (anti/de-icing properties) (see Example 1 in Section 2 - Maintenance operations)
  • the flexible film heater can be applied as a ply, in the current repair techniques, to also restore the functional property (anti/de-icing).
  • Figure 18 illustrates consistent damages requiring repair actions involving the replacement of CFs or GFs fabric (impregnated with resin) on aircraft under stopping conditions.
  • Figure 19 illustrates the execution of the repairs: removal of the damaged material layer by layer and replacement thereof. If the panel is the anti/de-icing panel of the present invention, the functional properties can be restored (together with the structural one) through the replacement of the film heater between the plies (as in the original configuration).
  • the film contacted with copper electrodes was initially cut into two distinct parts, subsequently, after the superposition of two edges (see Figure 20), the system was subjected to 10 minute of heating at 160 ° C followed by further heating for 10 minutes at 160 ° C at a pressure of about 2 bar.
  • the outcome of the repair is shown in Figure 20 in which the two overlapping flaps are fully adhered and compacted.
  • the repaired sample has an electrical conductivity higher than 200 S/m. This conductivity made it possible to perform heating tests with low applied voltages.
  • Figure 21 shows the heating test carried out at a voltage of 6 V, the relative electrical and thermal parameters and the distribution of temperature by means of an image acquired by an infrared camera.
  • thermocouple positioned in the center of the sample, in the sheltered area, recorded a rapid increase of the temperature up to 75 °C with an increase of about 53 °C compared to the ambient temperature in equilibrium conditions.
  • the film heater exhibits high efficiency, in fact, most of the temperature variation occurs in the first 30 seconds, after which the film has a homogeneous or almost homogeneous distribution of the temperature over the entire surface, including the repaired area.
  • the applied power density is more efficient than the requirements established by point 12 of table 1 of Annex A: EWPS 65- EW-0000-N352-200181 Issue 1 dated 24/08/2020. According to such requirements, in order to attain a power density in the range between 8 - 50 kW/m 2 for a heating between 7 °C and 21 °C, a DT of 14 °C is required.
  • the repair can be carried out through heating activated directly by the application of electric current (joule effect) on the coating.
  • the film heaters here proposed manifest greater resistance to damage (also consistent damages) because the damage does not break the metal connections or wires.
  • the film heater may have a nanometric conductive network on the entire surface.
  • Example N°1 of Section 3 refers to the assessment of the heating performance of the film heater after permanent damage.
  • MALLS Molecular Weight
  • the system After the permanent damage, the system has almost the same efficiency both in terms of heating and in terms of applied power density.
  • the thermal images show that the area surrounding the hole is characterized by homogeneous heating, very similar to that detected over the entire surface of the sample.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Surface Heating Bodies (AREA)

Abstract

L'invention concerne un artéfact comprenant un corps plat ou incurvé sensiblement constitué d'un métal ou d'un alliage métallique ou d'un matériau composite et comprenant un ou plusieurs panneaux de protection contre la glace. Le ou les panneaux de protection contre la glace comprennent un film chauffant et au moins une couche constituée de CFRC et/ou de GFRC. Le film chauffant comprend une matrice polymère thermoplastique contenant des groupes polaires, et au moins une couche de graphène ou graphitique qui est électriquement conductrice, ou une résine thermodurcissable, et fonctionnalisée avec des nanodomaines élastomères contenant des nanoparticules à base de carbone conducteur électrique dispersées. Le film chauffant est également pourvu d'électrodes et est placé entre ladite au moins une couche en CFRC et/ou GFRC et un revêtement de protection externe, ou est placé entre deux couches indépendamment constituées de CFRC et/ou de GFRC.
PCT/EP2023/071907 2022-08-09 2023-08-08 Artefact avec film chauffant WO2024033345A1 (fr)

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IT102022000017019 2022-08-09

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999015405A1 (fr) * 1997-09-22 1999-04-01 Northcoast Technologies Systeme degivreur et anti-givre et procede pour surfaces d'avions
US6330986B1 (en) * 1997-09-22 2001-12-18 Northcoast Technologies Aircraft de-icing system
EP3419381A2 (fr) * 2017-06-22 2018-12-26 Goodrich Corporation Systèmes électromécaniques de protection contre la glace comportant des éléments chauffants thermoplastiques chargés d'additifs de carbone
US20190390037A1 (en) * 2018-06-20 2019-12-26 The Boeing Company Conductive compositions of conductive polymer and metal coated fiber
KR20220108859A (ko) * 2021-01-27 2022-08-04 주식회사 파루인쇄전자 면상발열체를 포함하는 발열 패드 및 이의 제조방법

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999015405A1 (fr) * 1997-09-22 1999-04-01 Northcoast Technologies Systeme degivreur et anti-givre et procede pour surfaces d'avions
US6330986B1 (en) * 1997-09-22 2001-12-18 Northcoast Technologies Aircraft de-icing system
EP3419381A2 (fr) * 2017-06-22 2018-12-26 Goodrich Corporation Systèmes électromécaniques de protection contre la glace comportant des éléments chauffants thermoplastiques chargés d'additifs de carbone
US20190390037A1 (en) * 2018-06-20 2019-12-26 The Boeing Company Conductive compositions of conductive polymer and metal coated fiber
KR20220108859A (ko) * 2021-01-27 2022-08-04 주식회사 파루인쇄전자 면상발열체를 포함하는 발열 패드 및 이의 제조방법

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