Patent application number | Description | Published |
20090140098 | COMPONENT WITH CARBON NANOTUBES - The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component. | 06-04-2009 |
20090324765 | Apparatus for the forming of a lay-up of fibre composite material - An apparatus for the forming of a lay-up of fibre composite material, in particular in the aerospace sector is provided. In this case, the apparatus has at least one forming tool, which has a surface contour corresponding to a desired geometry of the lay-up after the forming, and a tool carrier, to which the at least one forming tool is releasably fastened. From a further viewpoint, the invention makes available an apparatus with a modular structure, it then being possible for any desired forming tools to be combined with the tool carrier according to requirements. This leads in particular to less laborious handling, since it obviates the need for handling of the comparatively large tool carrier. | 12-31-2009 |
20100015405 | PRODUCTION METHOD FOR A WORKPIECE COMPOSED OF A FIBRE-COMPOSITE MATERIAL , AND A FIBRE-COMPOSITE COMPONENT IN THE FORM OF A PROFILE WITH A PROFILE CROSS SECTION WHICH VARIES OVER ITS LENGTH - The present invention relates to a production method for a workpiece ( | 01-21-2010 |
20100059169 | DEVICE AND METHOD - The present invention provides a device, in particular within the aeronautical and aerospace fields, comprising a first and second tool and guide means, which guide the first and second tools in such a way that they press a preliminary fabric arranged in a pressing zone of the device along a second axis as said fabric moves along a first axis through the pressing zone, said second axis being substantially transverse to the first axis, so as to form a consolidated preliminary fabric, the guide means guiding the first and second tools parallel to one another, in part, along the first axis in the pressing zone. | 03-11-2010 |
20100065760 | METHOD FOR DETERMINING A CHARACTERISTIC PARAMETER OF A CRP SPECIMEN - The invention relates to a method for determining at least one characteristic parameter of a CRP specimen ( | 03-18-2010 |
20100072654 | METHOD FOR PRODUCING PROFILE PARTS - The present invention relates to a method for producing profile parts, each having an L-shaped cross-section, or an assembled profile part having, in particular, a T-shaped cross-section. For this purpose a lay-up made of composite fibre material is initially placed on a forming tool. In a further step, the lay-up is deformed by the forming tool to form a profile having a preferably U-shaped cross-section, the profile thus exhibiting the book effect at each opposite end. In a further step, the profile is preferably cut in the longitudinal direction in order to produce two profile parts. The idea on which the invention is based is to allow the layers in the lay-up to shift during the deformation process and subsequently to produce a substantially right-angled chamfered end on the profile parts by means of a cutting process. The disadvantageous formation of corrugations and complex clamping of the lay-up are thus avoided. | 03-25-2010 |
20100139847 | METHOD FOR PRODUCING A STRUCTURAL COMPONENT - This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric is formed from a composite fibre material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric is then connected to at least one hardening part of a composite fibre material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric connected to the at least one holding part is hardened at the first hardening temperature to form the structural component. The idea on which this invention is based consists in replacing expensive tools of special steel previously used for holding dimensionally unstable prepreg fabrics with at least one holding part of composite fibre materials, wherein the at least one holding part has a lower hardening temperature than the prepreg fabric, and can therefore be produced with a lower cost tool. | 06-10-2010 |
20100200156 | METHOD AND TOOL FOR PRODUCING A T-STRINGER - The present invention provides a method as well as a tool ( | 08-12-2010 |
20100276069 | METHOD AND DEVICE FOR THE PRODUCTION OF TUBULAR STRUCTURAL COMPONENTS - The present invention provides a method for the production of a tubular structural component. A tubular moulding tool having an inner mould surface which is shaped corresponding to an outer surface of the structural component is provided. A support surface of an expandable support which is formed such that in an unexpanded state, it fills the moulding tool, leaving an expansion spacing of the support surface to the mould surface, is covered with a tubular fibre-woven fabric. After the support has been arranged in the moulding tool, the fibre-woven fabric is pressed against the mould surface by expanding the support and is infiltrated by a curable matrix. From another point of view, a device is provided for the production of a tubular structural component. | 11-04-2010 |
20100314042 | METHOD FOR REINFORCING A FIBRE COMPOSITE COMPONENT AND A VACUUM MAT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBRE COMPOSITE COMPONENT - In a method for reinforcing a fibre composite component for aviation and space flight, a vacuum mat is configured with at least one receiving portion for reproducibly receiving at least one reinforcing element. The at least one reinforcing element is introduced into the at least one receiving portion of the vacuum mat. The vacuum mat with at least one introduced reinforcing element is applied reproducibly in a sealed manner to the fibre composite component to be reinforced to form a mould portion and at least the formed mould portion is cured to connect the at least one reinforcing element to the fibre composite component. The vacuum mat is then removed from the reinforced fibre composite component so that the vacuum mat can be reused. | 12-16-2010 |
20100314807 | METHOD FOR PRODUCING A PROFILE FROM COMPOSITE FIBER MATERIAL - The present invention provides a method for producing a profile from composite fiber material, in particular in the aviation and aerospace field, having the following steps: A preliminary fabric, particularly made of pre-impregnated fiber material, is first packed in a vacuum bag. Then support elements are laid on the packed preliminary fabric to support the latter. The vacuum bag is then supplied with a vacuum. Next, the preliminary fabric is hardened to the profile under the action of heat, in particularly in an autoclave. With the claimed method the support elements can be formed advantageously from favorable material, in particular aluminum, instead of highly expensive nickel-36 steel, since the support elements are uncoupled mechanically from the preliminary fabric in a longitudinal direction by means of the vacuum bag, enabling movement of the support elements in the longitudinal direction relative to the preliminary fabric. | 12-16-2010 |
20110011980 | CONNECTING ARRANGEMENT FOR JOINING TWO STIFFENING ELEMENTS HAVING DIFFERENT CROSS-SECTIONAL PROFILES FOR AN AIRCRAFT OR SPACECRAFT, AND SHELL COMPONENT - A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with in each case at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto in each case. | 01-20-2011 |
20110108188 | TAPE INSTALLATION DEVICE AND METHOD FOR THE CONSTRUCTION OF A LAMINATE - The present invention creates a tape laying device as well as a method for the construction of a laminate by means of a tape laying device, in particular in the field of aviation and aerospace. The tape laying device comprises a laying arrangement for laying tape for the construction of a laminate and a stimulation arrangement by means of which the tape which has to be laid can be stimulated directly and evenly over the thickness thereof so as to be heated. The idea the present invention is based on consists in that instead of the stimulation at the surface of the tape which has to be laid which is known to the Applicant a direct and evenly stimulation of the tape which has to be laid takes place, that means, a stimulation which acts substantially direct and evenly over the thickness of the tape which has to be laid on the tapes components. The heating achieved by this is much faster than by means of convection according to the known approach. Therefore, the desired tackiness of the tape which has to be laid can be achieved at the desired high laying velocity. | 05-12-2011 |
20110114895 | Fiber Composite Part for an Aircraft or Spacecraft - In a fibre composite component for an aircraft or spacecraft which has electrically conductive fibres at least in portions, the fibres are coupled with an electrical energy source for charging with current to heat up the fibres and/or for measuring the electrical resistance of the fibres. | 05-19-2011 |
20110121479 | Forming Device for Manufacturing Profiled Semifinished Products, System with such a Forming Device and Method for Manufacturing Profiled Semifinished Products - Disclosed is a method for producing a profiled semifinished fiber composite (FC) product from a semifinished product ( | 05-26-2011 |
20110308714 | METHOD AND SHAPING DEVICE FOR PRODUCING A COMPOSITE FIBRE COMPONENT FOR AIR AND SPACE TRAVEL - A forming tool with a predefined mould portion is provided in a method for producing a reinforced fibre composite component for aviation and aerospace. A forming/support element is moulded by means of the mould portion of the forming tool. A semi-finished fibre product is then deposited at least in portions on the shaped forming/support element. The deposited semi-finished fibre product is deformed by means of the forming/support element to form at least one reinforcing portion. The forming/support element is then removed from the forming tool together with the reinforcing section formed on this element, followed by defined positioning of the reinforcing section thus formed with respect to an associated fibre composite component portion by supporting with the forming/support element. The reinforcing portion is cured to form the reinforced fibre composite component. A forming device is provided with a predefined mould portion which holds a forming/support element such that it can be removed. | 12-22-2011 |
20110308722 | METHOD FOR JOINING PRECURED STRINGERS TO AT LEAST ONE STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT - The invention relates to a method for joining precured stringers to at least one structural component of an aircraft or spacecraft, including depositing covering vacuum films in advance at least on a predetermined region of each of the stringers to be joined, placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing in such a manner that a continuous vacuum arrangement, including the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by the continuous vacuum arrangement formed. | 12-22-2011 |
20120152461 | METHOD FOR REINFORCING A FIBRE COMPOSITE COMPONENT AND A VACUUM MAT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBRE COMPOSITE COMPONENT - In a method for reinforcing a fibre composite component for aviation and space flight, a vacuum mat is configured with at least one receiving portion for reproducibly receiving at least one reinforcing element. The at least one reinforcing element is introduced into the at least one receiving portion of the vacuum mat. The vacuum mat with at least one introduced reinforcing element is applied reproducibly in a sealed manner to the fibre composite component to be reinforced to form a mould portion and at least the formed mould portion is cured to connect the at least one reinforcing element to the fibre composite component. The vacuum mat is then removed from the reinforced fibre composite component so that the vacuum mat can be reused. | 06-21-2012 |
20130175723 | method and a device for the preparation of a dry textile preform - A method for the preparation of a dry textile preform for a large surface area fibre-reinforced composite component, in which resin-free textile material layers for purposes of manufacturing the preform are tensioned in each case in a tensioning frame, and in the stretched state are laid down on a moulding body by means of a linear relative movement between the tensioning frame and the moulding body. Also disclosed is a device for the execution of a method of this type with a tensioning frame for purposes of tensioning the material layers, and with a clamping unit for purposes of fixing the laid-down material layers on a moulding body. | 07-11-2013 |
20140346715 | METHOD AND DEVICE FOR THE PRODUCTION OF TUBULAR STRUCTURAL COMPONENTS - A method for producing a tubular structural component and device for production thereof are disclosed. A tubular moulding tool has an inner mould surface shaped corresponding to an outer surface of the structural component. A support surface of an expandable support, formed corresponding to the moulding tool shape such that in an unexpanded state the support fills the moulding tool while the support surface and the mould surface run parallel leaving an expansion spacing of the support surface to the mould surface, is covered with a tubular non-crimp fibre fabric, such that fibres of a fibre layer of the non-crimp fibre fabric run diagonally around the support. After the support has been arranged in the moulding tool, the non-crimp fibre fabric is pressed against the mould surface by expanding the support with radial expansion of the non-crimp fibre fabric. The non-crimp fibre fabric is infiltrated by a curable matrix. | 11-27-2014 |