EP2316291B1 - Helmet shell made from composite material - Google Patents

Helmet shell made from composite material Download PDF

Info

Publication number
EP2316291B1
EP2316291B1 EP10189124A EP10189124A EP2316291B1 EP 2316291 B1 EP2316291 B1 EP 2316291B1 EP 10189124 A EP10189124 A EP 10189124A EP 10189124 A EP10189124 A EP 10189124A EP 2316291 B1 EP2316291 B1 EP 2316291B1
Authority
EP
European Patent Office
Prior art keywords
resin
base
helmet shell
parts
impregnated
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.)
Active
Application number
EP10189124A
Other languages
German (de)
French (fr)
Other versions
EP2316291A1 (en
Inventor
Jean-Noël Perbet
Christophe Coupeaud
Laurent Laluque
Jean-Noël Baudou
Philippe Viot
Sébastien Denneulin
Virginie Rejsek
Matthieu Gervais
Alain Soum
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.)
Thales SA
Original Assignee
Thales SA
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 Thales SA filed Critical Thales SA
Publication of EP2316291A1 publication Critical patent/EP2316291A1/en
Application granted granted Critical
Publication of EP2316291B1 publication Critical patent/EP2316291B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • A—HUMAN NECESSITIES
    • A42—HEADWEAR
    • A42C—MANUFACTURING OR TRIMMING HEAD COVERINGS, e.g. HATS
    • A42C2/00—Manufacturing helmets by processes not otherwise provided for
    • A—HUMAN NECESSITIES
    • A42—HEADWEAR
    • A42B—HATS; HEAD COVERINGS
    • A42B3/00—Helmets; Helmet covers ; Other protective head coverings
    • A42B3/04—Parts, details or accessories of helmets
    • A42B3/06—Impact-absorbing shells, e.g. of crash helmets
    • A42B3/062—Impact-absorbing shells, e.g. of crash helmets with reinforcing means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]
    • Y10T428/1352—Polymer or resin containing [i.e., natural or synthetic]
    • Y10T428/1362—Textile, fabric, cloth, or pile containing [e.g., web, net, woven, knitted, mesh, nonwoven, matted, etc.]

Definitions

  • EP 1 300 089 describes a method for decorating and reinforcing a high-strength protective helmet and a helmet obtained thereby.
  • the structure according to the invention makes it possible either to improve the impact and penetration resistance for a given thickness of composite, or to reduce the composite thickness for a given impact and penetration resistance.
  • the technical solution is to add particular polymers to the resin of the composite in order to increase impact and penetration resistance at equivalent weight. This addition is very simple industrially, since particles are dispersed in the base of a resin, then the resin is prepared, drapes and coats the composite according to the same process as a conventional preparation. In order to simplify the realization of the composite, the use of this solution is limited to the most sensitive areas of the head. It has been shown that the regions of the top of the head and ears support lower energies than the rest of the skull before injury. We will refer to the study of J. McEntire, in Helmet Mounted Displays: Design Issues for Rotary-Wing Aircraft, edited by CE Rash for all the details on this subject.
  • the invention firstly relates to a helmet shell of composite material comprising at least one "armor” fabric impregnated with a resin matrix, characterized in that certain parts of the "armor” are impregnated with a resin matrix comprising an adjuvant capable of reinforcing the mechanical strength of the shell, said parts corresponding to the most fragile zones of a human head, the rest of the "armor” being impregnated with a resin matrix not containing said adjuvant.
  • the invention also has for its second object a pilot's helmet comprising at least one helmet shell according to one of the preceding characteristics.
  • a helmet shell of composite material according to the invention comprises at least one "armor" of fabrics, some parts of which are impregnated with a resin matrix comprising an adjuvant capable of reinforcing the mechanical strength of the shell, said portions corresponding to the most fragile areas of a human head.
  • a conventional resin is retained for the other areas of the shell.
  • Such a shell is represented in figure 3 .
  • the Z N parts of the shell C comprising the adjuvant comprises a dotted pattern, the Z parts not comprising the adjuvant are blank in this figure.
  • the head H is shown in dotted lines.
  • An epoxy-type resin is more particularly used and the adjuvant chosen is based on acrylic block copolymers.
  • the polymers added have a so-called "triblock” structure, which once formulated with an epoxy resin makes it possible to obtain a structuring of the matrix at the nanoscale. This structuring makes it possible to significantly modify the mechanical properties of the composite.
  • a composite "armor” consisting of three plies of poly-para-phenylene terephthalamide, better known under the trademark "Kevlar”.
  • Kevlar poly-para-phenylene terephthalamide
  • the reinforced parts being made of the same number of plies, the same reinforcing fabric but with an epoxy matrix loaded with "Nanostrength M22N”.
  • the percentage of "Nanostrength M22N” can be between 5% and 15%. Mechanical impact resistance tests on control plates show that the deformation of the "Nanostrength®" reinforced parts is approximately ten times lower than that of the unreinforced parts.
  • the method of preparation of the polymer-free composite "Nanostrength®" is identical except that no adjuvant is added to the epoxy base. Press parameters such as pressure or time and polymerization such as temperature, pressure or time are the same as those mentioned above for uncharged resin.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Helmets And Other Head Coverings (AREA)

Description

Le domaine de l'invention est celui des matériaux composites de structure ayant pour fonction la résistance aux chocs et la protection à la perforation. Le domaine d'application privilégié est celui des casques de protection pour pilotes d'aéronefs. Les structures selon l'invention peuvent cependant s'appliquer à tous domaines nécessitant des structures de protections très résistantes et légères.The field of the invention is that of structural composite materials whose function is impact resistance and protection against perforation. The preferred field of application is the protective helmets for aircraft pilots. The structures according to the invention can however be applied to all areas requiring very strong and lightweight protective structures.

Dans le domaine des casques de pilote d'avion d'arme ou d'hélicoptère, on cherche à réaliser des coques ayant la masse le plus faible possible, afin de minimiser les efforts sur les vertèbres cervicales du pilote, lors des accélérations de l'aéronef. Cependant, le casque doit apporter une protection suffisante, décrite par exemple dans des normes militaires comme la norme intitulée « Military Aircrew Helmet Impact Standard »,issue du « UK Ministry of Defence ».In the field of helicopter or helicopter pilot helmets, it is sought to make shells with the lowest mass possible, in order to minimize the efforts on the cervical vertebrae of the pilot, during the accelerations of the aircraft. However, the helmet must provide sufficient protection, as described, for example, in military standards such as the "Military Aircrew Helmet Impact Standard" issued by the "UK Ministry of Defense".

Les solutions technologiques mises en oeuvre pour réaliser les coques de casque doivent rester simples industriellement. Les solutions classiques pour résoudre ce problème sont :

  • L'emploi de matériaux thermoplastiques seuls, injectés selon la forme voulue ;
  • La superposition d'une coque composite et d'une mousse absorbant l'énergie des chocs ;
  • l'emploi de matériaux composites classiques. Ces derniers sont composés d'au moins deux matériaux différents : une matrice qui est une résine et un tissu tissé selon une « armure » judicieusement choisie selon l'application visée. La figure 1 représente un exemple de matériau composite comprenant trois couches de tissus T avant enrobage par la résine R. Le procédé de fabrication est représenté en figure 2. Il comprend trois étapes principales qui sont la préparation de la base en résine, l'imprégnation de l'armure par la base et la polymérisation de la structure imprégnée. On sait que ce type de matériau a des propriétés mécaniques bien supérieures aux éléments de base pris indépendamment. La matrice peut être thermoplastique ou thermodure. Le cas le plus classique de composite est le composite carbone epoxy ;
The technological solutions implemented to make the helmet shells must remain simple industrially. The classic solutions to solve this problem are:
  • The use of thermoplastic materials alone, injected in the desired form;
  • The superposition of a composite shell and a shock absorbing foam;
  • the use of conventional composite materials. The latter are composed of at least two different materials: a matrix which is a resin and a woven fabric according to a "weave" judiciously chosen according to the intended application. The figure 1 represents an example of composite material comprising three layers of fabric T before coating with resin R. The manufacturing process is represented in FIG. figure 2 . It comprises three main stages which are the preparation of the resin base, the impregnation of the armor by the base and the polymerization of the impregnated structure. It is known that this type of material has mechanical properties much higher than the basic elements taken independently. The matrix can be thermoplastic or thermodure. The most classic case of composite is the epoxy carbon composite;

Ces solutions offrent des résistances satisfaisantes aux chocs et à la pénétration pour des épaisseurs de quelques millimètres. Toutefois, si on veut alléger ces matériaux, les leviers techniques classiques ont tous déjà été explorés. On citera la diminution du taux de résine, le choix judicieux de l'armure des fibres et de l'orientation des plis successifs du tissu, l'optimisation de la post-cuisson du monolithique ou encore l'utilisation de mousses à épaisseurs variables.These solutions offer satisfactory resistance to shocks and penetration for thicknesses of a few millimeters. However, if we want to lighten these materials, the conventional technical levers have all already been explored. The reduction of the resin content, the judicious choice of the armor of the fibers and the orientation of the successive folds of the fabric, the optimization of the post-firing of the monolithic or the use of foams with variable thicknesses.

EP 1 300 089 décrit un procédé pour décorer et renforcer un casque de protection à haute résistance et un casque obtenu ainsi. EP 1 300 089 describes a method for decorating and reinforcing a high-strength protective helmet and a helmet obtained thereby.

La structure selon l'invention permet soit d'améliorer la résistance au choc et à la pénétration pour une épaisseur donnée de composite, soit de diminuer l'épaisseur de composite pour une résistance au choc et à la pénétration donnée. La solution technique consiste à ajouter des polymères particuliers dans la résine du composite afin d'augmenter la résistance au choc et à la pénétration, à masse équivalente. Cet ajout est très simple industriellement, puisqu'on disperse des particules dans la base d'une résine, puis on prépare la résine, drape et enduit le composite selon le même procédé qu'une préparation classique. Afin de simplifier la réalisation du composite, l'utilisation de cette solution se limite aux zones les plus sensibles de la tête. Il a en effet été montré que les régions du haut de la tête et des oreilles supportent des énergies plus faibles que le reste du crâne avant blessure. On se reportera à l'étude de J. McEntire, in Helmet Mounted Displays :Design Issues for Rotary-Wing Aircrafts, édité par C. E. Rash pour toutes précisions sur ce sujet.The structure according to the invention makes it possible either to improve the impact and penetration resistance for a given thickness of composite, or to reduce the composite thickness for a given impact and penetration resistance. The technical solution is to add particular polymers to the resin of the composite in order to increase impact and penetration resistance at equivalent weight. This addition is very simple industrially, since particles are dispersed in the base of a resin, then the resin is prepared, drapes and coats the composite according to the same process as a conventional preparation. In order to simplify the realization of the composite, the use of this solution is limited to the most sensitive areas of the head. It has been shown that the regions of the top of the head and ears support lower energies than the rest of the skull before injury. We will refer to the study of J. McEntire, in Helmet Mounted Displays: Design Issues for Rotary-Wing Aircraft, edited by CE Rash for all the details on this subject.

Plus précisément, l'invention a pour premier objet une coque de casque en matériau composite comprenant au moins une « armure » en tissus imprégnée d'une matrice en résine, caractérisé en ce que certaines parties de l' « armure » sont imprégnées d'une matrice en résine comportant un adjuvant apte à renforcer la résistance mécanique de la coque, lesdites parties correspondant aux zones les plus fragiles d'une tête humaine, le reste de l'« armure » étant imprégné d'une matrice en résine ne comportant pas ledit adjuvant.More specifically, the invention firstly relates to a helmet shell of composite material comprising at least one "armor" fabric impregnated with a resin matrix, characterized in that certain parts of the "armor" are impregnated with a resin matrix comprising an adjuvant capable of reinforcing the mechanical strength of the shell, said parts corresponding to the most fragile zones of a human head, the rest of the "armor" being impregnated with a resin matrix not containing said adjuvant.

Avantageusement, la résine est une résine de type époxy et l'adjuvant est à base de copolymères à blocs acryliques et plus précisément, les copolymères à blocs acryliques sont de marque « Nanostrength® » et commercialisés par la société Arkéma.Advantageously, the resin is an epoxy type resin and the adjuvant is based on acrylic block copolymers and more specifically, the acrylic block copolymers are branded "Nanostrength®" and marketed by Arkema.

Avantageusement, les parties de l' « armure » comportant l'adjuvant sont la partie supérieure de la coque correspondant au sommet du crâne et les parties latérales gauche et droite correspondant aux oreilles.Advantageously, the parts of the "armor" comprising the adjuvant are the upper part of the shell corresponding to the top of the skull and the left and right side parts corresponding to the ears.

L'invention a également pour second objet un casque de pilote comportant au moins une coque de casque selon l'une des caractéristiques précédentes.The invention also has for its second object a pilot's helmet comprising at least one helmet shell according to one of the preceding characteristics.

Elle a enfin pour troisième objet un procédé de réalisation d'une coque de casque en matériau composite comprenant au moins une « armure » en tissus imprégnée d'une matrice en résine, ledit procédé comportant les étapes suivantes :

  • Préparation d'une première base comportant uniquement de la résine époxy ;
  • Préparation d'une seconde base comportant de la résine époxy et un adjuvant apte à renforcer la résistance mécanique ;
  • Imprégnation des tissus au moyen de la seconde base dans les parties correspondant aux zones les plus fragiles d'une tête humaine ;
  • Imprégnation des tissus au moyen de la première base en dehors desdites parties ;
  • Polymérisation des tissus imprégnés.
Finally, it has for its third object a method of producing a helmet shell of composite material comprising at least one fabric "armor" impregnated with a resin matrix, said method comprising the following steps:
  • Preparing a first base comprising only epoxy resin;
  • Preparation of a second base comprising epoxy resin and an adjuvant capable of reinforcing the mechanical strength;
  • Impregnation of the tissues by means of the second base in the parts corresponding to the most fragile zones of a human head;
  • Impregnation of the tissues by means of the first base outside said parts;
  • Polymerization of impregnated fabrics.

L'invention sera mieux comprise et d'autres avantages apparaîtront à la lecture de la description qui va suivre donnée à titre non limitatif et grâce aux figures annexées parmi lesquelles :

  • La figure 1 représente un matériau composite avant imprégnation ;
  • La figure 2 représente les principales étapes de fabrication d'un matériau composite selon l'art antérieur ;
  • La figure 3 représente une coque de casque selon l'invention ;
  • La figure 4 représente les principales étapes de fabrication d'un matériau composite selon l'invention.
The invention will be better understood and other advantages will become apparent on reading the description which follows given by way of non-limiting example and by virtue of the appended figures among which:
  • The figure 1 represents a composite material before impregnation;
  • The figure 2 represents the main steps of manufacturing a composite material according to the prior art;
  • The figure 3 represents a helmet shell according to the invention;
  • The figure 4 represents the main steps of manufacturing a composite material according to the invention.

Comme il a été dit, une coque de casque en matériau composite selon l'invention comprend au moins une « armure » en tissus dont certaines parties sont imprégnées d'une matrice en résine comportant un adjuvant apte à renforcer la résistance mécanique de la coque, lesdites parties correspondant aux zones les plus fragiles d'une tête humaine. On conserve une résine classique pour les autres zones de la coque. Une telle coque est représentée en figure 3. Les parties ZN de la coque C comportant l'adjuvant comporte un motif en pointillés, les parties Z ne comprenant pas l'adjuvant sont en blanc sur cette figure. La tête H est représentée en pointillés. Ces parties de l'« armure » comportant l'adjuvant sont essentiellement la partie supérieure de la coque correspondant au sommet du crâne et les parties latérales gauche et droite correspondant aux oreilles.As has been said, a helmet shell of composite material according to the invention comprises at least one "armor" of fabrics, some parts of which are impregnated with a resin matrix comprising an adjuvant capable of reinforcing the mechanical strength of the shell, said portions corresponding to the most fragile areas of a human head. A conventional resin is retained for the other areas of the shell. Such a shell is represented in figure 3 . The Z N parts of the shell C comprising the adjuvant comprises a dotted pattern, the Z parts not comprising the adjuvant are blank in this figure. The head H is shown in dotted lines. These parts of the "armor" comprising the adjuvant are essentially the upper part of the shell corresponding to the top of the skull and the left and right side parts corresponding to the ears.

On utilise plus particulièrement une résine de type époxy et l'adjuvant choisi est à base de copolymères à blocs acryliques.An epoxy-type resin is more particularly used and the adjuvant chosen is based on acrylic block copolymers.

Les polymères ajoutés ont une structure dite « tribloc », qui une fois formulé avec une résine époxy permet d'obtenir une structuration de la matrice à l'échelle nanométrique. Cette structuration permet de modifier de façon significative les propriétés mécaniques du composite.The polymers added have a so-called "triblock" structure, which once formulated with an epoxy resin makes it possible to obtain a structuring of the matrix at the nanoscale. This structuring makes it possible to significantly modify the mechanical properties of the composite.

Plus précisément, les copolymères à blocs acryliques sont de marque « Nanostrength® » et commercialisés par la société Arkéma. Les composés Nanostrength® se déclinent en deux familles qui sont:

  • les « SBM » : acronyme de polyStyrène-block-poly(1,4-Butadiène)-block poly(Méthylméthacrylate) ;
  • les « MAM »: poly(MéthylméthAcrylate)-block poly(butylacrylate)-block-poly(Méthylméthacrylate).
More specifically, the acrylic block copolymers are branded "Nanostrength®" and marketed by Arkema. Nanostrength® compounds come in two families which are:
  • "SBM": acronym for polyStyren-block-poly (1,4-butadiene) -block poly (methyl methacrylate);
  • "MAM": poly (methylmethylacrylate) -block poly (butylacrylate) -block-poly (methyl methacrylate).

On peut, bien entendu, pour simplifier la réalisation de la coque, utiliser une seule résine comportant l'adjuvant pour réaliser la totalité de la coque. Cependant, la réalisation d'une telle coque présente certains inconvénients. En effet, l'ajout de polymères de type « Nanostrength®» dans les résines époxy augmente la viscosité de la substance. Les conséquences sont une plus grande difficulté de mise en oeuvre et un taux de résine plus élevé du composite, qui le rend plus lourd et plus cassant.One can, of course, to simplify the realization of the hull, use a single resin comprising the adjuvant to achieve the entire hull. However, the realization of such a shell has certain disadvantages. Indeed, the addition of "Nanostrength®" polymers in epoxy resins increases the viscosity of the substance. The consequences are a greater difficulty of implementation and a higher resin content of the composite, which makes it heavier and more brittle.

A titre d'exemple de mise en oeuvre,on peut utiliser comme composite une « armure » constituée de trois plis de poly-para-phénylène téréphtalamide, plus connu sous la marque « Kevlar ». Plus précisément, on peut choisir du « Kevlar » 129 de marque Saatilarâ style 802 tissé Taffetas, de densité 190 g/m2et d'épaisseur 260 µm,enrobés d'une résine de référence « Epolam 2020 » commercialisée par la société Axson et représentant 40% de la masse du composite. Les parties renforcées étant constituées du même nombre de plis, du même tissu de renfort mais avec une matrice époxy chargée de « Nanostrength M22N ». Le pourcentage de « Nanostrength M22N » peut être compris entre 5% et 15%. Des essais de tenue aux chocs mécaniques sur des plaques témoin montrent que la déformation des parties renforcées au « Nanostrength®» est environ dix fois inférieure à celle des parties non renforcées.As an example of implementation, can be used as a composite "armor" consisting of three plies of poly-para-phenylene terephthalamide, better known under the trademark "Kevlar". Specifically, one can choose the "Kevlar" 129 brand Saatilara style 802 woven Taffeta, density 190 g / m 2 and thickness 260 microns, coated with a reference resin "Epolam 2020" marketed by the company Axson and representing 40% of the mass of the composite. The reinforced parts being made of the same number of plies, the same reinforcing fabric but with an epoxy matrix loaded with "Nanostrength M22N". The percentage of "Nanostrength M22N" can be between 5% and 15%. Mechanical impact resistance tests on control plates show that the deformation of the "Nanostrength®" reinforced parts is approximately ten times lower than that of the unreinforced parts.

Le procédé de réalisation de la coque est représenté schématiquement en figure 4 et comporte les étapes suivantes :

  • Préparation d'une première base comportant uniquement de la résine époxy ;
  • Préparation d'une seconde base comportant de la résine époxy et un adjuvant apte à renforcer la résistance mécanique ;
  • Imprégnation des tissus au moyen de la seconde base dans les parties correspondant aux zones les plus fragiles d'une tête humaine ;
  • Imprégnation des tissus au moyen de la première base en dehors desdites parties ;
  • Polymérisation des tissus imprégnés.
The method of producing the shell is shown schematically in figure 4 and has the following steps:
  • Preparing a first base comprising only epoxy resin;
  • Preparation of a second base comprising epoxy resin and an adjuvant capable of reinforcing the mechanical strength;
  • Impregnation of the tissues by means of the second base in the parts corresponding to the most fragile zones of a human head;
  • Impregnation of the tissues by means of the first base outside said parts;
  • Polymerization of impregnated fabrics.

Plus précisément, le mode de préparation de la seconde base avec dispersion de polymères « Nanostrength® » est le suivant :

  • Mise en température de la base époxy à une température comprise entre 80 °C et 130 °C ;
  • Ajout à la base époxy de 10% en masse de « Nanostrength® » ;
  • Mélange avec un agitateur magnétique pendant une durée comprise entre 1 heure à 4 heures à une vitesse de 300 tours par minute ;
  • Refroidissement de la formulation jusqu'à la température ambiante ;
  • Ajout du durcisseur et mélange à la main jusqu'à obtenir une préparation homogène.
More specifically, the method of preparation of the second base with polymer dispersion "Nanostrength®" is as follows:
  • Heating the epoxy base to a temperature between 80 ° C and 130 ° C;
  • Addition to the epoxy base of 10% by weight of "Nanostrength®";
  • Mixing with a magnetic stirrer for a period of between 1 hour to 4 hours at a speed of 300 rpm;
  • Cooling of the formulation to room temperature;
  • Add the hardener and mix by hand until a homogeneous preparation.

Le mode de préparation du composite sans polymère « Nanostrength® » est identique à la réserve près que l'on n'ajoute pas d'adjuvant dans la base époxy. Les paramètres de presse comme la pression ou la durée et de polymérisation comme la température, la pression ou la durée sont les mêmes que ceux cités plus haut pour la résine non chargée.The method of preparation of the polymer-free composite "Nanostrength®" is identical except that no adjuvant is added to the epoxy base. Press parameters such as pressure or time and polymerization such as temperature, pressure or time are the same as those mentioned above for uncharged resin.

On peut ensuite procéder aux imprégnations avec et sans « Nanostrength® » séquentiellement, puis presser et polymériser simultanément toutes les régions de la coque. L'imprégnation et la polymérisation des tissus comportent les étapes suivantes :

  • imprégner au pinceau les plis du renfort ;
  • Eliminer l'excédent de résine dans une presse à 1,5 bars à température ambiante pendant une durée de 5 minutes ;
  • Polymériser l'ensemble dans une presse chauffante à 1,5 bars à 90°C pendant une durée de 90 minutes ;
  • Laisser refroidir à température ambiante ;
  • Post cuisson pendant 2 heures à une température de 80°C.
Impregnations can then be performed with and without "Nanostrength®" sequentially, and then simultaneously squeeze and polymerize all regions of the shell. The impregnation and the polymerization of the tissues comprise the following steps:
  • impregnate with the brush the folds of the reinforcement;
  • Remove the excess resin in a press at 1.5 bar at room temperature for a period of 5 minutes;
  • Polymerize the assembly in a heating press at 1.5 bars at 90 ° C. for a duration of 90 minutes;
  • Cool to room temperature;
  • Post baking for 2 hours at a temperature of 80 ° C.

Lors de l'étape d'imprégnation, on applique la résine époxy avec ou sans « Nanostrength® » au pinceau pour imprégner les plis de renfort. On peut utiliser un gabarit pour délimiter les zones d'applications. Un premier gabarit masque le haut de la tête et les oreilles et permet d'appliquer la résine non chargée. Un second gabarit masque l'avant,l'arrière et les côtés de la coque et permet d'appliquer la résine chargée de « Nanostrength® ».During the impregnation step, the epoxy resin is applied with or without "Nanostrength®" by brush to impregnate the reinforcing folds. A template can be used to delimit the areas of application. A first mask masks the top of the head and ears and allows to apply the uncharged resin. A second template hides the front, back and sides of the shell and allows the resin loaded with "Nanostrength®" to be applied.

Claims (6)

  1. A helmet shell (C) made from composite material, comprising at least one "armure" made from fabric impregnated with a resin matrix, characterised in that certain dedicated parts (ZN) of the "armure" are impregnated with a resin matrix comprising an additive that is designed to reinforce the mechanical strength of the shell, said parts corresponding to the weakest areas of a human head, the remainder (Z) of the "armure" being impregnated with a resin matrix that does not comprise said additive.
  2. The helmet shell according to claim 1, characterised in that the resin is an epoxy type resin and the additive is based on acrylic block copolymers.
  3. The helmet shell according to claim 2, characterised in that the acrylic block copolymers are of the "Nanostrength®" brand and are marketed by the company bearing the name Arkéma.
  4. The helmet shell according to claim 1, characterised in that the parts of the "armure" that comprise the additive are the upper part of the shell that corresponds to the top of the skull and the left and right lateral parts that correspond to the ears.
  5. A pilot helmet comprising at least one helmet shell according to any one of the preceding claims.
  6. A method for manufacturing a helmet shell made from composite material, comprising at least one "armure" made from fabric impregnated with a resin matrix, said method comprising the following steps of:
    • preparing a first base comprising the epoxy resin only;
    • preparing a second base comprising the epoxy resin and an additive designed to reinforce the mechanical strength;
    • impregnating the fabrics by means of the second base in the part that corresponds to the weakest areas of a human head;
    • impregnating the fabrics by means of the first base outside of said parts;
    • polymerising the impregnated fabrics.
EP10189124A 2009-11-03 2010-10-27 Helmet shell made from composite material Active EP2316291B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0905261A FR2951912B1 (en) 2009-11-03 2009-11-03 HELMET CASE IN COMPOSITE MATERIAL

Publications (2)

Publication Number Publication Date
EP2316291A1 EP2316291A1 (en) 2011-05-04
EP2316291B1 true EP2316291B1 (en) 2012-09-19

Family

ID=42289551

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10189124A Active EP2316291B1 (en) 2009-11-03 2010-10-27 Helmet shell made from composite material

Country Status (3)

Country Link
US (1) US8671466B2 (en)
EP (1) EP2316291B1 (en)
FR (1) FR2951912B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2988692A1 (en) * 2012-04-03 2013-10-04 Sebastien Denneulin Composite material skin for blade of e.g. windmill, has armor fabric impregnated with epoxy type resin matrix, where certain dedicated parts of armor fabric are provided with additive ready to reinforce mechanical resistance of skin
FR2991909B1 (en) * 2012-06-19 2014-07-04 Thales Sa HETEROSTRUCTURE IN COMPOSITE MATERIAL
USD869772S1 (en) * 2018-01-05 2019-12-10 Francois GAND Helmet
US20200054090A1 (en) * 2018-08-17 2020-02-20 Minson Enterprises Co., Ltd. Strengthened helmet with buffer portions and manufacturing method thereof

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2351235A (en) * 1942-06-18 1944-06-13 Gen Motors Corp Helmet
US3567568A (en) * 1967-09-29 1971-03-02 Dow Chemical Co Impact resistant sheet and method for the preparation thereof
US3956447A (en) * 1975-06-16 1976-05-11 The United States Of America As Represented By The Secretary Of The Army Method of making deep drawn, laminated articles
US3958276A (en) * 1975-07-09 1976-05-25 Clausen Carol W Helmet
US4023209A (en) * 1975-12-17 1977-05-17 Gentex Corporation Protective helmet assembly with segmental outer shell
US4748064A (en) * 1985-01-14 1988-05-31 Allied Corporation Ballistic-resistant composite article
JP2509285B2 (en) * 1988-03-18 1996-06-19 富士通株式会社 Semiconductor device testing method
US6003424A (en) * 1990-03-08 1999-12-21 Alliedsignal Inc. Armor systems
US5361420A (en) * 1993-03-30 1994-11-08 C & P Products Protective head gear for wrestlers
US5749096A (en) * 1994-07-01 1998-05-12 Ilixco, Inc. Helmet with high performance head and face protection utilizing complementary materials
ITMI20012071A1 (en) * 2001-10-05 2003-04-05 New Max Srl METHOD FOR THE DECORATION AND FOR THE REINFORCEMENT OF A HIGH STRENGTH SAFETY HELMET AND HELMET PRODUCED WITH SUCH METHOD
US6846758B2 (en) * 2002-04-19 2005-01-25 Honeywell International Inc. Ballistic fabric laminates
US7328462B1 (en) * 2004-02-17 2008-02-12 Albert E Straus Protective helmet
US9631898B2 (en) * 2007-02-15 2017-04-25 Honeywell International Inc. Protective helmets
US8782818B2 (en) * 2009-05-14 2014-07-22 Chang-Hsien Ho Safety helmet structure and processing method thereof
US9107466B2 (en) * 2009-08-31 2015-08-18 Rawlings Sporting Goods Company, Inc. Batting helmet having localized impact protection
US20110203024A1 (en) * 2010-02-25 2011-08-25 Morgan Arthur C Rifle Rated Ballistic Helmet

Also Published As

Publication number Publication date
FR2951912A1 (en) 2011-05-06
US8671466B2 (en) 2014-03-18
US20110265235A1 (en) 2011-11-03
EP2316291A1 (en) 2011-05-04
FR2951912B1 (en) 2011-12-02

Similar Documents

Publication Publication Date Title
EP2316291B1 (en) Helmet shell made from composite material
CA2464337C (en) Rolled product having a thickness that can be adjusted by means of peeling, the production method thereof and the application of same in the production of shims for mechanical assemblies
CN103320647B (en) The method for handling titanium aluminide intermetallic complex
EP0210918A1 (en) Protecting cap for the brain pan, and method of its manufacture
EP0502796B1 (en) Spectacle frames of synthetic resin and method of manufacture
CN109811164B (en) Preparation method of additive manufacturing aluminum alloy
EP3249064A1 (en) Additive manufacture of high temperature components from tial
TW200904352A (en) Protective helmets
WO2016132821A1 (en) Method for manfacturing ceramic-based composite material
EP1393884B1 (en) Composite products and molded articles obtained therefrom
CN108871073B (en) TC4-Al3Ti-TC 4-ceramic laminated composite armor and preparation method thereof
JP6194379B2 (en) Hybrid metal and composite spools for rotating machinery
EP0621879B1 (en) Epoxy resin composition and uses thereof, particularly in composite structures
WO1990012911A1 (en) Deformable textile structure
JP7448971B2 (en) composite material
CN113891951A (en) Aluminium-based alloy having improved mechanical strength on ageing at high temperatures and adapted to rapid solidification
CA2946603A1 (en) Airfoil with energy absorbing edge guard
EP0538108B1 (en) Composite material with a glass-ceramic or ceramic matrix obtained via the sol-gel process and reinforced with silicon carbide type fibers, its production and uses
CA1310894C (en) Articles formed from laminated material and manufacturing process thereof
FR2695409A1 (en) A composite material combining a magnesium alloy containing zirconium with a carbon reinforcement, and its manufacturing method.
EP2762208B1 (en) Method for manufacturing a snowboard and snowboard obtained by said method
CA2296043C (en) Adhesive composition for hot bonding and bonding method using same
CN109878124B (en) Blade and method for manufacturing the same
FR2988693A1 (en) BLADES IN COMPOSITE MATERIALS FOR WIND TURBINES OR HELICOPTERS
FR2991909A1 (en) Composite material structure, useful in e.g. helmet used by pilot of an aircraft, comprises internal surface, external surface, and three folds made of first fabric of a resin matrix, where first fold is close to external surface

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20110615

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 575557

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602010002883

Country of ref document: DE

Effective date: 20121108

RIN2 Information on inventor provided after grant (corrected)

Inventor name: REJSEK, VIRGINIE

Inventor name: LALUQUE, LAURENT

Inventor name: PERBET, JEAN-NOEL

Inventor name: GERVAIS, MATTHIEU

Inventor name: VIOT, PHILIPPE

Inventor name: DENNEULIN, SEBASTIEN

Inventor name: SOUM, ALAIN

Inventor name: BAUDOU, JOEL

Inventor name: COUPEAUD, CHRISTOPHE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121219

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20120919

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 575557

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120919

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Effective date: 20120919

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121220

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

BERE Be: lapsed

Owner name: THALES

Effective date: 20121031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121230

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130119

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130121

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121219

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121031

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

26N No opposition filed

Effective date: 20130620

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602010002883

Country of ref document: DE

Effective date: 20130620

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121027

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121027

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20101027

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20141031

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120919

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20141031

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20201013

Year of fee payment: 11

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602010002883

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220503

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230427

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230914

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230921

Year of fee payment: 14