WO2009040864A1 - Panneau ignifuge pour avions, bateaux, véhicules terrestres et systèmes de verrouillage associés - Google Patents

Panneau ignifuge pour avions, bateaux, véhicules terrestres et systèmes de verrouillage associés Download PDF

Info

Publication number
WO2009040864A1
WO2009040864A1 PCT/IT2008/000598 IT2008000598W WO2009040864A1 WO 2009040864 A1 WO2009040864 A1 WO 2009040864A1 IT 2008000598 W IT2008000598 W IT 2008000598W WO 2009040864 A1 WO2009040864 A1 WO 2009040864A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
composite materials
structure according
sandwich structure
panel
Prior art date
Application number
PCT/IT2008/000598
Other languages
English (en)
Inventor
Cristiano Bordignon
Original Assignee
Aeronautical Service S.R.L.
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 Aeronautical Service S.R.L. filed Critical Aeronautical Service S.R.L.
Publication of WO2009040864A1 publication Critical patent/WO2009040864A1/fr

Links

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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/12—Layered products comprising a layer of synthetic resin next to 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
    • B32B5/22—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
    • 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
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • 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
    • B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
    • 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
    • B32B2255/00—Coating on the layer surface
    • B32B2255/02—Coating on the layer surface on 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
    • B32B2255/00—Coating on the layer surface
    • B32B2255/10—Coating on the layer surface on synthetic resin layer or on natural or synthetic rubber 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • 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
    • B32B2262/02—Synthetic macromolecular fibres
    • B32B2262/0276—Polyester 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
    • 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
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/302—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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat
    • B32B2307/3065—Flame resistant or retardant, fire resistant or retardant
    • 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
    • B32B2307/70—Other properties
    • B32B2307/718—Weight, e.g. weight per square meter
    • 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

Definitions

  • the present invention refers in general to the aeronautical industry, and specifically regards the fire protection structures on airplanes, ships and ground vehicles.
  • a typical example is the nacelles, that is, the containers of the motors when external or the areas where the motors are positioned inside modern jets, helicopters, and aircraft in general.
  • the materials which are more frequently suited for containing fires are generally metal alloys with high thickness or superalloys as in the case of SPF (super plastic forming) titanium.
  • the SPF titanium alloy is used.
  • such alloy requires extremely costly, uncommon equipment, and post-processing even more complex for the control of the thicknesses: to mention only one example, the manufacturing of one of the seven sub-components of the engine bays of a transonic jet in such material requires a pressure molding of a plate with an initial thickness of 2 mm, an electrical discharge post-machining for reaching the thickness of 1.2 mm (quantity necessary given the geometries for containing the fire and ensuring the integrity of the structure for three minutes) and the subsequent mounting with the other sub-components in order to then obtain the assembled figure.
  • the methods used for manufacturing fireproof bulkheads in the boats made of GRP is that of loading the high thickness GRP laminates with aluminum oxide, which acts as a retardant agent of the flame passage.
  • this method for ensuring the prevention of the flame passage through a GRP laminate in accordance with the law UNI EN ISO 2685 there must be a minimum weight of over 25/30 kg/m 2 , such that sheets of aluminum alloys with thicknesses close to 10 mm are often preferred by such laminates.
  • the advantage in favor of this technique (that of loading GRP laminates with aluminum oxide) is that of being able to form double curvature surfaces from a mold.
  • one object of the present invention is that of providing a sandwich-type panel adapted to contain the fires on aircraft, ships and possibly also in ground structures which has a very reduced weight, can be made in various shapes as desired and by means of materials which are not hard to find.
  • one such panel to aerodynamic surfaces in general, to fuel tanks, to engine nacelles of airplanes, as fireproof bulkheads, and if necessary containing a fire on an air, ground or sea vehicle, one ensures a very reduced weight and formability as desired, also significantly increasing the safety of the vehicle.
  • the sandwich panel of the present invention represents a significant step forward in the solution of such problem, contributing to an important increase in air safety without affecting the payload.
  • Another object of the present invention regards a panel of the aforesaid type, but which incorporates an innovative locking system.
  • the sandwich panel can then be locked to the generic structure which receives it, without giving rise to dangerous thermal bridges.
  • the innovative locking system of the panel ensures the effectiveness of the fixing to the support structure for a time period sufficient to ensure the safety of the passengers and/or crew of an airplane, ship, etc. in case of fire.
  • the present invention attains its objects by providing a fireproof panel made of composite materials and provided with sandwich structure, characterized in that it comprises the following layers in order:
  • oxide-based materials silicon oxide or zirconium oxide stabilized with yttria
  • a sixth layer (6) of long-fiber fabric skins, impregnated in resin matrix, or formed by a metal plate, arranged on the "cold side" of the panel and with thickness and characteristics as a function of the expected loads.
  • Other specific characteristics of the panel are indicated in the dependent claims 2 to 15, which define various alternative embodiments.
  • the present invention obtains its objects by providing a fireproof panel made of composite materials and provided with sandwich structure, with locking system incorporated in the same panel, for locking the panel to a generic support structure, wherein:
  • an enlargement or reinforcement (7) is provided of the thickness of the cold part, or sixth layer (6), situated on the cold side of the panel, the enlargement (7) being made at a locking screw (8); - said locking screw (8) being incorporated, with its head, in the fourth layer (4) of the panel, having honeycomb structure, wherein the threaded stem of the locking screw (8) projects from said cold side of the panel, so as to allow the fixing to a support structure, the head of the locking screw (8) remaining hidden inside the panel, inside the honeycomb structure, in order to avoid direct contact with the flames of a possible fire on the hot side of the panel.
  • the fireproof panel made of composite materials and provided with sandwich structure is such that said enlargement or reinforcement (7) is extended in the direction parallel to the sides of the panel for a distance substantially equal to the diameter of the head of the locking screw (8) or for a distance which is a function of the loads which are expected to act against the panel.
  • the thickness (9) of the honeycomb structure of said fourth layer (4) of the fireproof panel which covers said head of the locking screw (8) is substantially identical to the thickness of the same fourth layer (4) in another region of the fireproof panel where there is no locking screw (8), such that the amount of heat which reaches the head of the locking screw (8) remains below that which would cause a size increase such to slot the hole in which the same screw (8) is screwed.
  • FIGURE 1 is a schematic section view of the various layers of the sandwich panel, subject of the present invention, before their mutual assembly;
  • FIGURE 2 is a section view of the sandwich panel of Figure 1, but which according to the second aspect of the invention also incorporates the innovative locking system.
  • the panel comprises (see Fig. 1):
  • honeycomb (4) of material with melting temperature greater than 1000°C with cell size as desired, cell of Nomex type and minimum thickness of 6 mm or steel alloy; - powder of oxide-based materials, with thermal conductivity at 1000°C equal to 0.09 W/mK, for filling the honeycomb cells;
  • - structural adhesive (5) in film or paste form with vitreous transition temperature after its polymerization > 120°C;
  • - cold part (6) formed by: two fabric skins made of carbon fiber or alternatively long-fiber fabric of the following type: S glass, E glass, Kevlar with 29 or 49 count, Twaron, basalt, and more generally long-fiber fabric with melting temperature greater than 1100° made with a weft and warp, or unidirectional fabric made of such fibers with crossed skins, with minimum weight of 120 g/m 2 per single skin (it is noted that these fibers are also impregnated with resin, as in the case of the layer (2)).
  • the panel sequentially described in its main materials starting from the part exposed to fire (1) ensures, with a reduced weight of only 3.5 kg/m 2 , the prevention of the flame passage according to UNI EN ISO 2685 and maintains the cold part (6) fully intact in case of the engine bays of the transonic Jet Trainer M346.
  • non- woven ceramic fiber fabric of 70 g/m 2 weight * two fabric skins made of carbon fiber or alternatively long-fiber fabric of the following type: S glass, E glass, Kevlar with 29 or 49 count, Twaron, basalt, and more generally long-fiber fabric with melting temperature greater than 1100°C and with weft and warp, or unidirectional fabric made of such fibers with crossed skins, with minimum weight of 120 g/m 2 per single skin; * structural adhesive in film or paste form with vitreous transition temperature after its polymerization > 120°C;
  • the final missing point with regard to the preceding table that, as an example, could be represented by 3 carbon fabric skins (of the type 8552S37%/AGP280 wherein 8552S is the employed epoxy resin system, 37% is the resin quantity present in the laminate and AGP 280 is the basis weight equal to 280 g/m 2 ), was suitably tested for its application in substitution of the SPF Ti alloy in the manufacture of the engine bays of the transonic jet called M346.
  • the final missing point with regard to the preceding table being the temperature encountered on the cold skin after 15 minutes exposure to 300°C, could also be represented by a plate of metal alloy of one's choice - as long as it has a melting temperature greater than or equal to 300°C.
  • the present invention regards - in a preferred embodiment thereof- the same panel described above with reference to Fig. 1, in any one of its above-indicated possible preferred embodiments, but with a locking system integrated therein as clearly represented in section in Fig. 2. As shown in Fig.
  • the amount of heat which arrives on the head of the screw is > 300°C, which does not lead to a size increase for specific metal alloys which would slot the passage hole, rendering ineffective the locking of the panel on its support structure.
  • the temperature taken as reference of 300°C is the maximum temperature which the cold part reaches after 15 minutes of fire exposure, according to the UNI EN ISO 2685 test procedure. It is noted that in Fig. 2, for the sole purpose of simplifying the drawing, the various layers 1, 2, 3 and 5, 6 of Fig. 1 were only represented by two relative layers whose faces 1 and 6 respectively correspond to the side exposed to the fire
  • refractory material 1 is joined (on the left in Fig. 2) to the cold part (at the edge of the panel), protecting the honeycomb 4 found inside.
  • the formability of the panel of the present invention signifies that the flat panel form, shown in Figures 1 and 2, is of course illustrated only as an example and that any form could be used according to the shape of the support structure and the installation and application conditions.

Abstract

L'invention concerne un panneau réalisé en un matériau composite ignifuge, comprenant une première couche réfractaire composée d'un tissu de fibre céramique non-tissé, une seconde couche de revêtements de tissu à fibre longue imprégnés d'une résine, une couche adhésive structurelle, une couche de matériau ayant une structure en nid d'abeilles remplie de matériaux à base d'oxyde ayant une conductivité thermique faible, une autre couche adhésive structurelle formée par des revêtements de tissu à longue fibre imprégnés par une résine, ou par une plaque. Un tel panneau est léger, améliorant significativement le rapport entre le poids global et le poids utile ou la charge utile d'un avion, par exemple ; de plus, le matériau le composant est aisément trouvé. Le panneau améliore également le paramètre de sécurité à l'air.
PCT/IT2008/000598 2007-09-27 2008-09-17 Panneau ignifuge pour avions, bateaux, véhicules terrestres et systèmes de verrouillage associés WO2009040864A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITRM20070501 ITRM20070501A1 (it) 2007-09-27 2007-09-27 Pannello in materiali compositi resistente alla fiamma passante per applicazioni aero, navali e terrestri e suoi sistemi di bloccaggio.
ITRM2007A000501 2007-09-27

Publications (1)

Publication Number Publication Date
WO2009040864A1 true WO2009040864A1 (fr) 2009-04-02

Family

ID=40265984

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IT2008/000598 WO2009040864A1 (fr) 2007-09-27 2008-09-17 Panneau ignifuge pour avions, bateaux, véhicules terrestres et systèmes de verrouillage associés

Country Status (2)

Country Link
IT (1) ITRM20070501A1 (fr)
WO (1) WO2009040864A1 (fr)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110240165A1 (en) * 2008-11-03 2011-10-06 De Rovere Anne N Mounting mat and pollution control device with the same
RU2465145C1 (ru) * 2011-05-11 2012-10-27 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Огнестойкий слоистый звукотеплоизолирующий материал
FR3015431A1 (fr) * 2013-12-19 2015-06-26 Airbus Operations Sas Structure primaire de mat d'accrochage renforcee.
CN105128438A (zh) * 2015-09-18 2015-12-09 巢湖市南特精密制造有限公司 一种气缸盖板用复合板材及其制备方法
CN105253308A (zh) * 2015-11-10 2016-01-20 康福斯（苏州）航空工业有限公司 飞机发动机仓
EP3135472A1 (fr) * 2015-08-27 2017-03-01 The Boeing Company Procédés, systèmes et appareil pour le revêtement d'une soute d'aéronef
CN106515168A (zh) * 2016-12-16 2017-03-22 江苏科悦新材料有限公司 一种保温阻燃热塑性聚酯复合材料及其制备方法和应用
CN107161317A (zh) * 2017-05-23 2017-09-15 广州星晖智能科技有限公司 一种机身强度高的无人机
CN107226192A (zh) * 2017-05-28 2017-10-03 珠海磐磊智能科技有限公司 一种复合板材及飞行器
US9862497B2 (en) 2013-12-17 2018-01-09 Airbus Operations (S.A.S.) Assembly for an aircraft, comprising an engine attachment body partially produced in one piece with an internal stiffening rib of an attachment pylon box section
EP3126133A4 (fr) * 2014-03-30 2018-01-10 Ayithi, Veera Systèmes et procédés de production d'un panneau structurel et de panneaux homogènes composites hybrides non structurels, de préimprégnés, de panneaux à pose à la main avec une fibre "de basalte", de différents matériaux composites, et d'additifs
US9889943B2 (en) 2013-12-17 2018-02-13 Airbus Operations (S.A.S.) Assembly for an aircraft, comprising an engine attachment body equipped with at least one shackle support fitting that passes into the box section of the attachment pylon
US10336458B2 (en) 2013-12-23 2019-07-02 Airbus Operations (S.A.S.) Aircraft assembly comprising a mounting strut built into the nacelle and arranged at the rear section of the fuselage
CN109955502A (zh) * 2019-04-04 2019-07-02 北京卫星制造厂有限公司 返回式飞船防热与承载一体化侧壁结构的制备方法
CN110723275A (zh) * 2019-10-24 2020-01-24 湖北航天技术研究院总体设计所 一种高温防热口盖结构
EP3822073A1 (fr) * 2019-11-14 2021-05-19 Airbus Operations, S.L. Produit isolant résistant au feu et thermique
US11479305B2 (en) 2018-07-24 2022-10-25 Bridgestone Americas, Inc. Modular structural composites for automotive applications
IT202100027548A1 (it) * 2021-10-27 2023-04-27 Aeronautical Service S R L Pannello multistrato antifuoco e metodo di produzione.

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4767656A (en) * 1984-01-09 1988-08-30 The Boeing Company Composite material structure with integral fire protection
JP2002178425A (ja) * 2000-12-15 2002-06-26 Bio System Kk 航空機用耐火性内装材及びその製法
US20050224637A1 (en) * 2004-02-17 2005-10-13 Fabian Edward J Self extinguishing composite primary structure
EP1719698A1 (fr) * 2005-05-05 2006-11-08 Northrop Grumman Corporation Isolation thermique d'un joint d'une structure effilée

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4767656A (en) * 1984-01-09 1988-08-30 The Boeing Company Composite material structure with integral fire protection
JP2002178425A (ja) * 2000-12-15 2002-06-26 Bio System Kk 航空機用耐火性内装材及びその製法
US20050224637A1 (en) * 2004-02-17 2005-10-13 Fabian Edward J Self extinguishing composite primary structure
EP1719698A1 (fr) * 2005-05-05 2006-11-08 Northrop Grumman Corporation Isolation thermique d'un joint d'une structure effilée

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Week 200276, Derwent World Patents Index; AN 2002-700540, XP002512386 *

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110240165A1 (en) * 2008-11-03 2011-10-06 De Rovere Anne N Mounting mat and pollution control device with the same
US9290866B2 (en) * 2008-11-03 2016-03-22 3M Innovative Properties Company Mounting mat and pollution control device with the same
RU2465145C1 (ru) * 2011-05-11 2012-10-27 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Огнестойкий слоистый звукотеплоизолирующий материал
US9862497B2 (en) 2013-12-17 2018-01-09 Airbus Operations (S.A.S.) Assembly for an aircraft, comprising an engine attachment body partially produced in one piece with an internal stiffening rib of an attachment pylon box section
US9889943B2 (en) 2013-12-17 2018-02-13 Airbus Operations (S.A.S.) Assembly for an aircraft, comprising an engine attachment body equipped with at least one shackle support fitting that passes into the box section of the attachment pylon
FR3015431A1 (fr) * 2013-12-19 2015-06-26 Airbus Operations Sas Structure primaire de mat d'accrochage renforcee.
US9868545B2 (en) 2013-12-19 2018-01-16 Airbus Operations (S.A.S.) Primary structure for an attachment pylon with firewall and thermal layers
US10336458B2 (en) 2013-12-23 2019-07-02 Airbus Operations (S.A.S.) Aircraft assembly comprising a mounting strut built into the nacelle and arranged at the rear section of the fuselage
EP3126133A4 (fr) * 2014-03-30 2018-01-10 Ayithi, Veera Systèmes et procédés de production d'un panneau structurel et de panneaux homogènes composites hybrides non structurels, de préimprégnés, de panneaux à pose à la main avec une fibre "de basalte", de différents matériaux composites, et d'additifs
RU2719096C2 (ru) * 2015-08-27 2020-04-17 Зе Боинг Компани Способ, система и облицовка грузового отсека летательного аппарата
JP2017104493A (ja) * 2015-08-27 2017-06-15 ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ 航空機の貨物室を裏打ちするための方法、システム及び装置
EP3135472A1 (fr) * 2015-08-27 2017-03-01 The Boeing Company Procédés, systèmes et appareil pour le revêtement d'une soute d'aéronef
CN105128438A (zh) * 2015-09-18 2015-12-09 巢湖市南特精密制造有限公司 一种气缸盖板用复合板材及其制备方法
CN105253308A (zh) * 2015-11-10 2016-01-20 康福斯（苏州）航空工业有限公司 飞机发动机仓
CN106515168A (zh) * 2016-12-16 2017-03-22 江苏科悦新材料有限公司 一种保温阻燃热塑性聚酯复合材料及其制备方法和应用
CN107161317A (zh) * 2017-05-23 2017-09-15 广州星晖智能科技有限公司 一种机身强度高的无人机
CN107226192A (zh) * 2017-05-28 2017-10-03 珠海磐磊智能科技有限公司 一种复合板材及飞行器
CN107226192B (zh) * 2017-05-28 2020-10-23 珠海磐磊智能科技有限公司 一种复合板材及飞行器
US11479305B2 (en) 2018-07-24 2022-10-25 Bridgestone Americas, Inc. Modular structural composites for automotive applications
CN109955502A (zh) * 2019-04-04 2019-07-02 北京卫星制造厂有限公司 返回式飞船防热与承载一体化侧壁结构的制备方法
CN110723275A (zh) * 2019-10-24 2020-01-24 湖北航天技术研究院总体设计所 一种高温防热口盖结构
EP3822073A1 (fr) * 2019-11-14 2021-05-19 Airbus Operations, S.L. Produit isolant résistant au feu et thermique
IT202100027548A1 (it) * 2021-10-27 2023-04-27 Aeronautical Service S R L Pannello multistrato antifuoco e metodo di produzione.

Also Published As

Publication number Publication date
ITRM20070501A1 (it) 2009-03-28

Similar Documents

Publication Publication Date Title
WO2009040864A1 (fr) Panneau ignifuge pour avions, bateaux, véhicules terrestres et systèmes de verrouillage associés
CA2326314C (fr) Systemes resistant au percement par le feu destines aux moyens de transport, notamment aux avions
CN100418850C (zh) 机身
EP0167533B1 (fr) Structure de materiau composite avec protection integrale contre l'incendie
EP1924491B1 (fr) Fuselage d'aeronef
CA2557594C (fr) Structure composite primaire a auto-extinction
US20070141927A1 (en) Method and system for exterior protection of an aircraft
EP1701881B1 (fr) Fuselage
EP3835052A1 (fr) Panneau balistique et procédé de fabrication d'un panneau balistique
US20060234007A1 (en) Device for the protection against and detection of impacts on the edges of a layered composite structure
US11845531B2 (en) Fireproof and thermal insulator product
CN101657235B (zh) 设置有纤维金属层压板机身外壳设备的航空器乘客防火空间
Dexter Long-term environmental effects and flight service evaluation of composite materials
US20240116264A1 (en) Layered composite comprising a fire-retardant composite material
US20210147063A1 (en) Fireproof and thermal insulator product
EP3756880A1 (fr) Dispositif de protection contre les incendies pour aéronef
Torres et al. A new approach to solve aging airplane problems using polyisocyanurate
Wykes Prototype rigid polyimide components

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08833190

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 08833190

Country of ref document: EP

Kind code of ref document: A1