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WO2024252315A1 - Matériau composite renforcé par des fibres, comprenant des couches de préimprégné de fibres avec des nanotubes de carbone conducteurs ou des couches intermédiaires de nanofibres - Google Patents

Matériau composite renforcé par des fibres, comprenant des couches de préimprégné de fibres avec des nanotubes de carbone conducteurs ou des couches intermédiaires de nanofibres Download PDF

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Publication number
WO2024252315A1
WO2024252315A1 PCT/IB2024/055531 IB2024055531W WO2024252315A1 WO 2024252315 A1 WO2024252315 A1 WO 2024252315A1 IB 2024055531 W IB2024055531 W IB 2024055531W WO 2024252315 A1 WO2024252315 A1 WO 2024252315A1
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WO
WIPO (PCT)
Prior art keywords
vacnt
composite panel
layers
panel according
height
Prior art date
Legal status (The legal status 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 status listed.)
Pending
Application number
PCT/IB2024/055531
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English (en)
Inventor
Pascal Boulanger
Thomas GOISLARD DE MONTSABERT
Kevin Retz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Kouros Lab
Original Assignee
Kouros Lab
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 Kouros Lab filed Critical Kouros Lab
Publication of WO2024252315A1 publication Critical patent/WO2024252315A1/fr
Anticipated expiration legal-status Critical
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B1/00—Layered products having a non-planar shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/024—Woven fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B32B5/262—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary characterised by one fibrous or filamentary layer being a woven fabric layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/05—5 or more layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/20—All layers being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/42—Alternating layers, e.g. ABAB(C), AABBAABB(C)
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/202—Conductive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B82—NANOTECHNOLOGY
    • B82Y—SPECIFIC USES OR APPLICATIONS OF NANOSTRUCTURES; MEASUREMENT OR ANALYSIS OF NANOSTRUCTURES; MANUFACTURE OR TREATMENT OF NANOSTRUCTURES
    • B82Y30/00—Nanotechnology for materials or surface science, e.g. nanocomposites

Definitions

  • Fiber reinforced composite material comprising plies of fiber prepreg with conductive carbon nanotubes or nanofibers interlayers
  • the present invention belongs to the technical field of non-metallic composite materials based on organic or inorganic fiber prepreg sheets. More precisely, it relates to composite materials comprising interlayers of vertically aligned carbon nanotubes or nanofibers, which are provided with means for electrically connecting these interlayers to an external circuit.
  • Said fiber composite materials can be used to make composite materials with electrically conductive interlayers.
  • Such composite materials are multifunctional in the sense that besides their usual function of providing specific mechanical properties (such as strength, impact resistance) to a workpiece, they bring in at least one further function, such as electrical conductivity.
  • Composite materials with electrical conductivity have numerous applications for heating (such as in de-icing and anti-icing devices), auto-curing, thermal control, protection against lightning, in situ monitoring of the internal state of a composite material, and can be used for instance in cars, energies devices and in aircraft or aerospace construction.
  • interlayers of conductive material are insert interlayers of conductive material in between fiber plies.
  • Most interlayers which have been used in prior art do not have sufficient conductivity in both the X- Y plane and at the same time but independently along the Z-axis to meet technical requirements of specific applications such as de-icing and anti-lightning devices.
  • Most of those electrically conductive interlayers are manufactured by electrospinning of polymeric fibers that are made conductive by appropriate additives. Some of them are also made of carbon nanotubes such as CNT mats that are only conductive in the X-Y plane and have no significant conduction in the Z-plane.
  • Chemical protection is achieved by distributing a liquid onto the surface that is to be protected, usually by a system of holes or channels within the structure.
  • the de-icing fluid or anti-icing fluid is held in a tank and is fed through a system of tubes, pipes and pumps to the surfaces that require de-icing or anti-icing protection.
  • the de-icing fluids can have a negative environmental impact and cause maintenance issues due to the nature of the fluid.
  • a VACNT layer is deposited onto a layer (“ply”) of fibers.
  • the fibers can be previously impregnated or (infiltrated) with a suitable resin.
  • a suitable resin is commonly called a “pre-preg” in the field of composite materials.
  • These pre-pregs can advantageously be unidirectional prep-pregs, or can be woven or fabric.
  • the resin can in particular be a thermoplastic resin, a thermoset resin or an elastomeric resin.
  • the VACNT layer can be deposited onto one face of the pre-preg ply or on both faces according to certain embodiments of the invention.
  • a unitary sheet of fibers covered with VACNT is called here a “mono ply”.
  • mono plies can be superposed.
  • a solid composite panel or a solid composite shaped part is obtained.
  • Said panel or said shaped part can be rigid, semi-rigid or even flexible, depending on the nature of the resin and/or on the number of plies.
  • the mechanical properties of such panels or parts depend mainly on the choice and structure of the fiber layer, on the resin, and on the number of superimposed plies. Mechanical reinforcement of such structures is already well known and validated.
  • the deposition of the VACNT layer onto the fiber ply is carried out by known transfer techniques, such as lamination and calendering. It is not practical to grow VACNT layers directly from the gas phase onto pre-preg fiber layers, but direct growth is also possible for raw fabric for instance.
  • two or more VACNT layer are used in the composite panel, each sandwiched between two plies.
  • the use of two or more VACNT layers for heating purposes improves the thermal homogeneity of the composite panel devices incorporating said composite panel.
  • the use of two or more VACNT layers also allows to dedicate at least one of these layers to sensing purposes, which allows to monitor for example the structural health of the composite material.
  • the number of VACNT layers between plies can be greater than 2, for example 3, 4, 5, 6, 7, 8 and so on.
  • the specific power at 800 V is preferably at least 3 W/cm 2 , preferably at least 4 W/cm 2 , more preferably at least 4.5 W/cm 2 , still more preferably at least 5 W/cm 2 , and even more preferably at least 6 W/cm 2 .
  • the VACNT height is the same for all the VACNT layers.
  • the VACNT can be bent so that they are still aligned but not perpendicular to the fiber X-Y plane.
  • the VACNT height is not the same in the VACNT layers.
  • VACNT height may be different for heating layers and for measurement layers (here also called: sensing layers).
  • heating layers have a VACNT height comprised between about 1 pm and about 100 pm, preferably between about 5 pm and about 50 pm, and more preferably between about 15 pm and about 25 pm, while electrically conductive layers dedicated to measurement can have a smaller VACNT height, which is typically between about 1 pm and about 15 pm, preferably between about 1 pm and about 10 pm, and more preferably between about 1 pm and about 5 pm.
  • the VACNT height can be selected such as to adjust electrical resistance and heat generation of each ply. Each layer may have a different thickness according to the target performance. This also allows a better compatibility with a broader range of resin.
  • a particularly suitable VACNT height for thermoset resin is 15 pm to 25 pm. For thermoplastic or even elastomeric resins, the VACNT height can be above 25 pm.
  • the density of CNT (i.e. , their number per surface area) and/or the spacing of CNT within a VACNT array may also be adjusted.
  • Another object of the present invention is a composite panel device, comprising a composite panel according to any of the embodiments of the invention, and further comprising electrical connection elements connecting at least two of said VACNT layers in parallel or in series, and at least one electrical apparatus connected such as to form an electrical circuit with said at least two VACNT layers, wherein said electrical apparatus is a power generator.
  • a further object of the present invention is a de-icing system or anti-icing system for mechanical construction elements such as aircrafts, terrestrial vehicles, stairs, using a composite panel according to any of the embodiments of the present invention, or a shaped part according to the invention.
  • a further object of the invention is a method for making a composite panel or a shaped part according to any of the embodiments of the present invention, comprising the steps of:
  • a further object of the invention is a method for making a composite panel or a shaped part according to any of the embodiments of the present invention, comprising the steps of:
  • Figure 1 schematically shows a transversal cross section of a composite panel according to a first embodiment of the invention.
  • Figure 2 schematically shows a transversal cross section of a composite panel according to a second embodiment of the invention.
  • Figure 3 schematically shows a transversal cross section of a composite panel according to a third embodiment of the invention.
  • Figure 6 schematically shows a transversal cross section of a composite panel according to a sixth embodiment of the invention.
  • Figure 7 schematically shows perspective view of a shaped part according to the invention.
  • Figure 8 shows a micrograph obtained by scanning electron microscopy, representing a top view of an array of vertically aligned carbon nanotubes (VACNT) used in the composite panels according to the invention.
  • VACNT vertically aligned carbon nanotubes
  • Figure 9 schematically shows different steps which form part of the method for manufacturing a flat composite panel according to the invention.
  • the step shown here relate to the transfer of a VACNT array from its growth substrate onto a prepreg sheet.
  • Figure 10 shows a scanning electron microscopic image of a cross section of a ply used for making NawaStitchTM panels.
  • the letter “F” designated the fiber
  • the letter “R” designated the resin which impregnates the fiber structure
  • VACNT indicates the location of the VACNT array.
  • each ply may have a thickness of the order of several hundreds of micrometres, the diameter of the individual fibers being of the order of about 5 pm to about 50 pm.
  • the pre-preg sheets can be identical or different, in particular with respect to their thickness, with respect to the nature and/or thickness of the fibers, with respect to the density of the fiber textile, with respect to nature and thickness of the resin.
  • the VACNT layers can be identical or different, in particular with respect to the height of the nanotubes forming the VACNT sheet, and/or with respect to their surface density.
  • the composite panel can be shaped during its manufacture or after its manufacture. Shaping during manufacture can be achieved typically when lamination is carried out as compression molding, in an autoclave or by hand. After its manufacture, the composite panels can be curved or otherwise shaped. Shaping after manufacture will normally require a thermoplastic resin to be selected for the pre-preg sheets; it can be carried out in as compression molding at a temperature that is sufficiently high such that the thermoplastic resin will soften.
  • VACNT interlayer between certain adjacent fiber layers 14,15.
  • the upper face 2 will normally be the external face (i.e., the face on which ice may form when the de-icing device is not heating), and the lower face 3 will the internal face, i.e., the face in contact with a structural element of the aircraft.
  • FIG. 2 schematically shows a first embodiment of a composite panel device 100 according to the invention. All reference numbers corresponding to those of figure 1 are increased by 100.
  • the structure of the different layers forming said composite is the same as in figure 1.
  • This figure shows in addition an external electrical circuit to which the device is connected.
  • This external electrical circuit alloys for example to pass a current through each of the VACNT arrays, said current leading to resistive heating of said VACNT interlayers 121 ,122,123,124.
  • the reference number 150 would not necessarily be a power generator, but an electrical apparatus configured to inject a current, possibly as a pulse, into the composite panel device 100, and configured to measure a response.
  • this sensing (monitoring) function can be used intermittently, that is to say from time to time, and the electrical apparatus 150 can be configured such as to pass a current through the composite panel device 100 sufficient for heating.
  • the composite panel device 100 is in fact a multifunction device: it can serve as a heating device and as a sensing or monitoring device, too.
  • FIG. 5 schematically shows such an embodiment of a composite panel device 400 according to the invention, with a composite comprising a plurality of groups of VACNT interlayers.
  • two interlayers 421 ,424; 422,423 are connected in series and can be connected to a common electrical apparatus 451 ,461 .
  • This heating device can be carried out in two different variants.
  • both electrical apparatuses 451 ,461 are power generators, and can be used and tuned independently from each other.
  • one of the electrical apparatuses 451 ,461 is a power generator (or a channel of a power generator) and the other one is a sensing or monitoring device.
  • Said sensing or monitoring device is configured to measure at least one electrical parameter of at least one of the VACNT interlayers.
  • said sensing or monitoring device can be connected to any of the VACNT interlayers, by using an appropriate switching circuit (not shown on the figures).
  • Various measurement methods can be used to detect a change in a physical property or characteristics of the composite panel device, using at least one of the conductive VACNT interlayers.
  • this physical property or characteristics can be related to the structural health of said composite panel, and can be used to monitor the state of health of a said composite panel.
  • the electrical resistance and I or the impedance can be measured, and its evolution in time can be monitored. This monitoring can be carried out in particular under solicitations, such as vibration. Electrical pulses can be injected, and their response can be monitored by time-of-flight techniques or wave analysis. Local temperature measurement can be carried out by measuring the electrical resistance, and/or by an external IR camera for instance. The acoustic and I or electric coupling of adjacent layers can be measured and I or monitored.
  • Some of these measurements can be carried out as static measurement, and/or periodically and/or as dynamic measurements. In some cases, these signals are analysed by the recognition of typical signatures.
  • each group of VACNT interlayers said interlayers are connected in parallel.
  • NawaStitchTM composites can be used with various numbers of plies.
  • a ply is defined as a complex comprising a fiber layer onto which a VANCT layer is provided (either by direct growth of VACNT onto said fiber layer, or by transfer from an intermediate substrate, which can be the growth substrate, onto said fiber layer).
  • the optimum structure of the composites depends on the electrical operating parameters.
  • FIG. 5 schematically shows an embodiment with six plies; in this example, the four VACNT layers are electrically connected in parallel.
  • a busbar 572,574 collects the electrical current and leads it to or from the electrical apparatus 550.
  • the composite panel be held inside an insulating envelope.
  • Said envelope should be flexible, and should be thin, so as not to impede thermal conduction.
  • Kapton films can be used for making this insulating envelope.
  • FIG. 7 shows a shaped part 600 representing, for example, a heating device for use with (or as) a leading edge of an aircraft wing, made from a bent composite panel according to the invention.
  • the upper face 602 is the external face (i.e. , the face on which ice may form when the de-icing device is not heating)
  • the lower face 603 is the internal face, i.e., the face in contact with a structural element of the aircraft.
  • the VACNT interlayers are concentrated in the region of thickness close to the upper face 603, as shown on figures 1 to 5.
  • Each extremity of the composite panel 600 has its busbar 672,674 connected to an electrical conductor 670,671 connecting the panel 600 to the electrical apparatus 650. Titanium vias 680 can be used to fix the busbar onto the panel surface.
  • the VACNT height is typically comprised between about 1 pm and about 100 pm, preferably between about 5 pm and about 50 pm, and more preferably between about 15 and about 25 pm.
  • VACNT layers dedicated to measurement can have a smaller height, typically between about 1 pm and about 25 pm, and preferably between about being 1 pm and about 10 pm, and more preferably between about 1 pm and about 5 pm.
  • the busbar can be a straight bar. In other embodiments the busbar can have another regular shape, or an irregular shape. As an example, the busbar can have an S shape, or a saw tooth shape.
  • the invention has numerous advantages compared to prior art composites.
  • the addition of VACNT increases the electrical and thermal conductivity in the z-direction. Such panels show a more uniform heat profile. By tailoring the height of the VACNT the electrical conductivity of the panel can be adjusted to a target value.
  • the addition of VACNT reduces the electrical power required to achieve a specific surface temperature.
  • VACNT interlayers do not increase the weight of the structure by more than few percent. In some cases, they improve specific mechanical properties of the composite panel or part.
  • the method according to the invention avoids VACNT growth directly onto the prepreg, which would not be practical, as VACNT growth requires high temperatures which are not compatible with a resin-impregnated growth substrate.
  • the method according to the invention also avoids VACNT growth directly onto the fibers or onto the fiber tissue, which would also impose certain boundary conditions to the growth process and/or to the choice of fiber material, and which would require to impregnate the growth substrate after VACNT growth with an appropriate resin.
  • Example 1 Flat plates The inventors have manufactured flat composite panels according to the invention, with different numbers of plies containing VACNT layers. The voltage was controlled until the panel maximum temperature was steady at 125 °F. Voltage and current were recorded at steady state. It can be seen that the sheet resistance decreases with the number of plies.
  • the panels with 6 and 7 plies had a specific power at 800 V above 4.5 W/cm 2 , which makes them particularly useful for de-icing.
  • test pieces according to the invention were cooled in a freezer to about -20 °F (about - 28.9 °C), and ice was allowed to build up.
  • the thickness of the ice layer was about 0.082 inches (about 2.08 mm); certain areas had a thicker layer, others a thinner layer.
  • the test pieces were removed from the freezer, and an electric current was supplied to the panel at ambient temperature. The test pieces were observed by a FUR thermography camera.

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  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

L'invention concerne un panneau composite formé par un empilement de feuilles pré-imprégnées alternant avec des couches de nanotubes de carbone alignés verticalement (VACNT), un élément de connexion électrique étant disposé sur deux bords opposés de chaque couche de VACNT. Ladite couche de VACNT peut être utilisée à des fins de chauffage et/ou de détection. Ce panneau est utile pour des dispositifs de dégivrage et antigivrage sur des aéronefs.
PCT/IB2024/055531 2023-06-06 2024-06-06 Matériau composite renforcé par des fibres, comprenant des couches de préimprégné de fibres avec des nanotubes de carbone conducteurs ou des couches intermédiaires de nanofibres Pending WO2024252315A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US202363471303P 2023-06-06 2023-06-06
US63/471,303 2023-06-06

Publications (1)

Publication Number Publication Date
WO2024252315A1 true WO2024252315A1 (fr) 2024-12-12

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Country Status (1)

Country Link
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Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB505433A (en) 1937-11-05 1939-05-05 Rudolf Goldschmidt Improvements in and relating to de-icing equipment, for example for aircraft
US3779488A (en) 1968-06-24 1973-12-18 I Levin Electric system of a device for deicing the surface of thinwalled structures
US4678144A (en) 1984-10-26 1987-07-07 Simmonds Precision Electro-impulse de-icing system for aircraft
EP0376371A2 (fr) 1988-12-30 1990-07-04 The Boeing Company Dispositif thermique antigivre pour aéronef
US5114100A (en) 1989-12-29 1992-05-19 The Boeing Company Anti-icing system for aircraft
US20070128960A1 (en) 2005-11-28 2007-06-07 Ghasemi Nejhad Mohammad N Three-dimensionally reinforced multifunctional nanocomposites
US20090117363A1 (en) 2005-03-25 2009-05-07 Brian Lee Wardle Nano-engineered material architectures: ultra-tough hybrid nanocomposite system
WO2010129234A2 (fr) 2009-04-27 2010-11-11 Lockheed Martin Corporation Chauffage résistif à base de nanotubes de carbone pour dégivrer des structures composites
US20130028744A1 (en) * 2010-01-14 2013-01-31 Pontus Nordin Aerodynamic surface with improved properties
US20150290845A1 (en) * 2012-10-23 2015-10-15 Saab Ab Smooth surface forming tool and manufacture thereof
US20170019954A1 (en) 2010-01-26 2017-01-19 Metis Design Corporation Multifunctional cnt-engineered structures
US20170129207A1 (en) * 2014-07-03 2017-05-11 Saab Ab A composite article having multifunctional properties and method for its manufacture
WO2018027092A1 (fr) 2016-08-04 2018-02-08 General Nano Llc Structure formée d'un film de nanotubes de carbone et son procédé de fabrication

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB505433A (en) 1937-11-05 1939-05-05 Rudolf Goldschmidt Improvements in and relating to de-icing equipment, for example for aircraft
US3779488A (en) 1968-06-24 1973-12-18 I Levin Electric system of a device for deicing the surface of thinwalled structures
US4678144A (en) 1984-10-26 1987-07-07 Simmonds Precision Electro-impulse de-icing system for aircraft
EP0376371A2 (fr) 1988-12-30 1990-07-04 The Boeing Company Dispositif thermique antigivre pour aéronef
US5114100A (en) 1989-12-29 1992-05-19 The Boeing Company Anti-icing system for aircraft
US20090117363A1 (en) 2005-03-25 2009-05-07 Brian Lee Wardle Nano-engineered material architectures: ultra-tough hybrid nanocomposite system
US20070128960A1 (en) 2005-11-28 2007-06-07 Ghasemi Nejhad Mohammad N Three-dimensionally reinforced multifunctional nanocomposites
WO2010129234A2 (fr) 2009-04-27 2010-11-11 Lockheed Martin Corporation Chauffage résistif à base de nanotubes de carbone pour dégivrer des structures composites
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