Ucsnik S.,LKR Leichtmetallkompetenzzentrum Ranshofen GmbH |
Scheerer M.,ARC Seibersdorf Research |
Zaremba S.,FACC AG |
Pahr D.H.,Vienna University of Technology
Composites Part A: Applied Science and Manufacturing | Year: 2010
An integrative joining technology between steel and carbon fibre-reinforced plastics (CFRP) is presented for lightweight design applications in aviation industries. Small spikes are welded onto metal surfaces via "cold-metal transfer" which then build up a fibre-friendly fixation through form-closure with co-cured composites. Manufacture of such reinforced hybrid specimens and results of static tensile testings are discussed. Video-extensometry is applied to characterize the hybrid joints in terms of strength and failure history. Comparisons with epoxy bonded references show improvements in ultimate load, maximum deformation and energy absorption capacity. © 2009 Elsevier Ltd. All rights reserved.
Mayr G.,Research and Development Ltd. |
Plank B.,Research and Development Ltd. |
Sekelja J.,FACC AG |
Hendorfer G.,Upper Austria University of Applied Sciences
NDT and E International | Year: 2011
In this work active thermography was successfully applied as a quantitative method for the non-destructive evaluation of porosity in carbon fiber reinforced polymers. Results showed that not only the level of porosity, but also the shape of the pores strongly influences the active thermography results, in particular the measured thermal diffusivity. In an experiment the shape of the pores was obtained by means of X-ray computed tomography. Based on this microstructural information, the dethermalization theory can be deduced as the most effective thermal diffusivity model with respect to quantitative porosity determination. Furthermore, the obtained experimental data on active thermography correspond to measurements made using ultrasonic testing with respect to the influence of pore shapes. © 2011 Elsevier Ltd.
Facc Ag | Date: 2010-11-25
A concealed 180 hinge for the movable connection of two parts between a collapsed state and a fully opened-out state of the parts has at least two U-shaped pivoting brackets. The hinge, which has the highest possible strength and also allows the two parts to be moved in relation to one another without any risk of collision, includes rotary pins of the two pivoting brackets on the one hinge part that are arranged in a plane substantially parallel to the plane of the part, which can be connected to this one hinge part. The rotary pins of the two pivoting brackets on the second hinge part are disposed in a plane located substantially perpendicularly to the plane of the part, which can be connected to this second hinge part.
Facc Ag | Date: 2015-03-06
A device for a spaced apart connection of a structural element, in particular made from a fiber-reinforced plastic composite material, with a holding element by means of a connection screw, with a distance compensation element comprising a longitudinal bore for the passage of the connection screw, and with an entraining element arranged in the longitudinal bore, which entraining element can be connected to the connection screw by means of a friction fit, so that the distance compensation element can be transferred into an abutment position bridging the distance between the structural element and the holding element by screwing in of the connection screw, wherein the distance compensation element is connected to an insertion part via a screw connection, which insertion part comprises a fastening section that can be arranged within the structural element for bonding with the structural element.
Facc Ag | Date: 2014-01-28
An overhead luggage compartment for aircraft can be constructed as a fixed luggage compartment with a stationary housing and a pivotable flap, or as a lowerable luggage compartment with a lowerable tray, a stationary part having side walls and a movable part which is pivotable between a closed and an open position and has a closure element for retaining the movable part in the closed position. Those parts define a luggage-receiving space. Two fastening devices for fastening to a supporting structure of the aircraft on the side walls of the stationary part are disposed on the stationary part. At least one further fastening device is disposed in the region of the lower side of the rear side of the stationary part. The fastening devices are the same for the fixed luggage compartment and for the lowerable luggage compartment.
Facc Ag | Date: 2011-09-06
A device fixes fittings, in particular wall or floor elements in airplanes, to a structure such that no vibrations are generated. The device has a fixing element which is configured on one end for fixing to the structure and on the opposite end for receiving the fittings. The opposite end of the fixing element is movably mounted in a spacer sleeve which can be connected to the fittings to be received and which contains an elongated hole-shaped cross-section, and the opposite end is configured for fixing to the fittings. At least one damping element is provided and disposed between the structure and the fittings. The spacer sleeve has an elongated hole-shaped cross-section, and the one end of the fixing element is formed by a stand or can be connected to a stand. The stand is configured for movably mounting in a rail section that lies on the structure.
Facc Ag | Date: 2010-04-15
A frame for reinforcing a hull of a craft, particularly an aircraft, contains at least one frame element that is shaped in accordance with the curvature of the hull and has recesses at a side facing the hull for the passage of longitudinal beams of the craft. Each frame element is integrally formed from a fiber-reinforced plastic composite material and the recesses are configured as integral cut-outs of each frame element.
Facc Ag | Date: 2015-01-20
A device for opening an aircraft door, comprising: a support arm arranged between the aircraft fuselage and the aircraft door; an opening system for opening the aircraft door; a support arm cover covering the support arm in the closed position of the aircraft door, the support arm cover having a cover element, and a flap element which swivels between being flush with the cover element, and a state in which the flap element overlaps the cover element; and a guide system for guiding the flap element, wherein the guide system has at least one guide arm, one end of which is joined in an articulated manner to the support arm, and the other end of which is joined to at least one guide element, which guide element can be guided along a guide track on the inner side of the flap element, when the aircraft door is opened.
Facc Ag | Date: 2011-10-13
A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure p in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded.
Facc Ag | Date: 2012-03-01
A method using a tool for producing a fiber composite component includes a planar fiber lay-up placed on a carrier mold, provided with a stiffening section protruding from the lay-up and pressed between parts of a molding tool. A chamber sealed from the mold is formed by an air-tight film enclosing the tool, the lay-up and the stiffening section. The chamber is connected to a resin supply line and a vacuum line. Resin is aspirated by negative pressure applied to the vacuum line, and the lay-up and the stiffening section are saturated by resin to form the fiber composite component. Air and resin are drawn between the parts of the tool, through the stiffening section and into a suction channel extending in the tool and connected to the vacuum line through a suction opening of the tool, for conducting air and/or resin.