摘要:
L'invention concerne un procédé pour la réparation d'un panneau (10) composite, ledit panneau comportant au moins une première peau (12) composite qui est délimitée par une face inférieure (18), caractérisé en ce qu'il comporte une étape de découpage qui consiste à former un trou (22) étagé en escalier au moins dans la première peau (12), une étape d'appareillage qui consiste à agencer une face d'appui d'un outil de formage contre la face inférieure (18) de la première peau (12), une étape de reconstitution de la première peau (12) consistant à refermer le trou (22) au moyen d'une pièce de réparation (38) et une étape de fixation qui consiste à fixer la pièce de réparation (38) sur la première peau (12) par des moyens de fixation (42) mécanique.
摘要:
The present invention provides a connecting device (100).for connecting an unhardened fibre layer (104) which is arranged on a surface section (112) of a fibre compound structure (102) to the fibre compound structure. The connecting device comprises pressure cushion (390) comprising a pressure cap (120,308) for being arranged above the surface section and a pressure tight cap mat (106) which is pressure tightly connected to a circumferential border (107) of the pressure cap, thereby forming a pressure area which is limited by the pressure cap and. by the cap mat. The connecting device further comprises a pressure inducing means (302) for inducing an overpressure which presses the cap mat against the fibre layer into the pressure area. According to a further aspect the invention provides a processing method for processing a fibre compound structure.
摘要:
An area of a structure is reworked from one side of the structure using resin infusion of a dry fiber patch. Entrapped air and excess resin is removed from the patch during the infusion process by inserting a vacuum device into the patch, and forcing the area resin through the vacuum device.
摘要:
An in-situ double vacuum debulk (DVD) composite repair system designed to produce partially or fully cured autoclave-quality hot-bond composite repairs on contoured structures. The system provides vacuum pressure for hot bond repairs to be performed on flat and contoured structures using one set-up capable of debulking (partially curing) and then fully curing composite repairs on composite and metallic aircraft structures. The use of in-situ DVD also eliminates handling of the patch/adhesive when transferring from an off-aircraft DVD chamber to the repair site on the aircraft. This can increase the probability of successful repairs because the possibility of contaminating and misaligning the adhesive and repair patch are eliminated.
摘要:
Apparatus (10) comprises a stationary structure (12) and a moving structure (14). Mounting arrangements (16) mount the stationary structure to the outside of the pipe (18). The moving structure (14) is moveably carried on the stationary structure by means of toothed drive rings (36) and idler pinions (40) and is driven by a motor (46) through a pinion (48). This allows the moving structure (14) to turn around a pipe on which the stationary structure is mounted. A reinforcement dispensing arrangement (20) dispenses reinforcing material (22) while turning around the pipe, to wrap the reinforcing material (22) around the pipe.
摘要:
Die Erfindung betrifft eine mobile Membranpresse (1) zur Reparatur von Bauteilen (2) mit faserverstärkten Kunststoffen, aufweisend eine flexible beheizbare mit Vakuum beaufschlagbare Membran (46) und eine mit dieser verbundenen Peripherie- und Steuereinheit (20) zur Versorgung der Membranpresse (1) mit Vakuum und zur Steuerung und Regelung der Temperatur, dadurch gekennzeichnet, dass in der Membran (46) eine Heizvorrichtung (40) integriert ausgebildet ist und dass eine umlaufende Dichtung (45) um den zu reparierenden Bereich des Bauteils (2) an der Membran (46) zur vakuumdichten Verbindung der Membran (46) mit dem Bauteil (2) angeordnet ist, wobei die umlaufende Dichtung (45) als Klebeband ausgeführt ist und dass zwischen einer bauteilzugewandten Seite (41) der Membran (46) und dem Bauteil (2) eine Vakuumverteilschicht (47) auf dem zu reparierenden Bereich des Bauteils (2) angeordnet ist.
摘要:
The present disclosure describes one or more systems, methods, routines and/or techniques for thermal management. One or more systems, methods, routines and/or techniques may provide advice or guidance (e.g., to a repair technician) regarding how to perform a hot bond repair, for example, on an aircraft component that has been damaged. The thermal management advisor may provide advice or guidance regarding how to prepare a repair field prior to running a thermal survey. For example, thermal management advisor may recommend a particular heat blanket, a configuration of the heat blanket, placement of various temperature sensors and other preparation guidance. The thermal management advisor may provide advice or guidance regarding how to alter or manage the repair setup during a thermal survey and during the actual curing process. For example, thermal management advisor may recommend particular temperature sensors or areas of the repair field that should be insulated.
摘要:
A tool comprises a caul plate having at least one suction hole and a vacuum port fluidly coupled to the suction hole for drawing a patch against the caul plate under vacuum.
摘要:
Es wird eine Schablone (1), sowie ein Schablonenset (0), umfassend die Schablone (1) und mindestens eine korrespondierende zusätzliche Schablone (1') und der Gebrauch zur Präparation von ebenen und gekrümmten Oberflächen (3), bevorzugt aus mehreren Schichten von Verbundmaterial offenbart. Neben der Präparation der Oberflächen (3) ist mit der Schablone (1) und der mindestens einen zusätzlichen Schablone (1') auch eine Markierung der Zuschnittslinien auf Flicken aus Reparaturmaterial in Form von faserverstärkten Verbundmaterial zusätzlich durchführbar.
摘要:
The invention relates to a method for repairing a damage to a thermoplastic composite element, in particular an aircraft component, wherein a socket (14) is milled at the site of damage to the thermoplastic composite element (10). Then, in said socket a patch is formed from a thermosetting material containing a reinforcing phase of fabric layers and a matrix of thermosetting resin, said patch having a shape and size corresponding to the socket (14) geometry. In the next step, the patch is cured, and finally the cured patch (13) is glued into the socket (14) by means of an adhesive (9).