METHOD OF PRODUCING INTEGRAL ARTICLES

Abstract: A method of producing integral articles such as rudder parts etc. of plastics, reinforced with relatively long, continuous fibres is described. During the hot-setting or thermoforming process pressure is applied along at least two co-ordinate axes, with an angle between them of 30 DEG to 90 DEG . The method is characterized particularly in that to achieve the required pressures for each co-ordinate axis, from one of its co-ordinate directions a pressure element movable relative to the article is pressed against the article, while from the opposite co-ordinate axis at least one principally form stable bucker-up element in conjunction with said pressure element is caused to provide a pressure that acts on the article and against the direction of the force of the pressure element.

Description: Method of producing integral articles The present invention relates to a method of producing integral articles of hot-setting resins or thermoplasts reinforced with relatively long fibres, so called composites, whereby during the hot-setting or thermoforming process pressure is applied along at least two co-ordinate axes between which the angle is 30° to 90°. Such fibre-reinforced plastics, i.e. composites, are used for the manufacturing of articles, whereby in the aircraft industry methods with increased air pressure, i.e. autoclaves, are usually used, and in other industries usually presses. Originally in manu¬ facturing more complicated articles of composite material, simpler parts were made separately and then put together to the desired article by means of gluing or mechanical joints. Re¬ garding pure plastics and plastics reinforced with short fibres development has gone far in integrating form and function. This has been possible in that such material can float a long way in complicated closed tool moulds. For composites with relatively long, continuous fibres this possibility does not exist. Articles that are intended to be manufactured according to the aforementioned method comprise for instance integrally set stiffen- ers in panels or integrally set ribs, spars and crusts in rudders. Hitherto, the required pressure has been attained for the manufac¬ turing of the last-mentioned articles with the aid of double tools and with deformable bucker-up elements in the form of silicone inserts, whereby the pressure has been attained in auto¬ clave or through the thermal expansion of the silicone. These hitherto known methods of manufacturing have not been entirely satisfactory in the manufacturing of integral articles, particularly not regarding such articles that have a relatively complicated form and/or articles on which there are extremely high demands on strength combined with low weight. The object of the present- invention is therefore to provide a method as mentioned in the introduction that admits a relatively simple and reliable method of manufacturing integral articles on which are placed the aforementioned demands. According to the invention such a method is characterized primarily in that in order to attain the required pressures for each co¬ ordinate axis a pressure element movable relative to the article is pressed against the article from one co-ordinate direction, while from the opposite co-ordinate direction at least one principally form stable bucker-up element in conjunction with said pressure element is caused to provide a pressure that acts on the article and against the direction of the force of the pressure element. In an appropriate embodiment of the invention the heat required for the hot-setting or thermoforming process is supplied at least partly via said bucker-up element. There are also applications of the invention where it is advantageous that in addition to the form stable bucker-up elements, a deformable bucker-up element, such as a silicone insert, in conjunction with said pressure element is caused to provide a pressure that acts on the article and against the direction of the force of the pressure element. Some articles have such an internal form that the bucker-up element must be separable so that it can be put in and out of the required working position. The invention will now be described in detail, with reference to the accompanying drawings, in which Figure 1 shows a view of a part of an aircraft rudder with suggested ribs; Figure 2 shows a cross-section along the marks II - II in figure 1; Figure 3 shows a cross-section along the markings III - III in figure 1; Figure 4 shows a vertical longitudinal section through a portion of another rudder (on a larger scale compared with figures 1-3), with bucker-up elements positioned for the application of the method according to the invention; whereas Figure 5 shows a cross-section along the markings V - V in figure 4. In figure 1-3 the upper composite crust of the rudder part is designated by 1, composite ribs by 2 and a lower composite crust by 3. In figure 4, 4 designates an upper composite crust, 5 a lower composite crust and 6 composite ribs. These are provided partly with upper and lower flanges 7, 8 for attachment to the compo- site crusts 4, 5 and partly with essentially vertical front and rear coupling flanges 9, 10 to be connected to spars, which are not shown. The rudder parts that are shown are in this case built of hot-setting resins, reinforced with relatively long, continuous fibres, for example of glass. Each form stable bucker-up element of aluminium is divided into three, and is designated by 11a, 11b and 11c. This trisecting is necessary for the bucker-up element to be capable of being placed in working position and taken out of such a position, because the coupling flanges 9, 10 prevent the positioning of a bucker-up element in one single piece. Therefore the bucker-up element parts 11b and 11c are firstly set in position, where¬ upon the centre bucker-up element part 11a is pushed in. Then the bucker-up elements 12 and 13 are arranged working from the outside on the vertical coupling flanges 9 and 10. The required pressure is so built up by means of a pressing tool in the order Px, Py and Pz according to the figures, whereupon the setting process is started, in this case through the supply of heat from the outside. As has already been mentioned the bucker-up elements can also be provided with heating arrangements to facili¬ tate a steady temperature distribution during the setting process. When this is done the pressure is removed and the bucker-up elements are taken out in the order 11a, 11b and 11c.

Claims: AMENDED CLAIMS [received by the International Bureau on 29 September 1989 (29.09.89) original claim 1 amended; other claims unchanged (1 page)] 1. Method of producing integral articles of hot-setting resins or thermoplasts reinforced with relatively long fibres, so called composites, whereby during the hot-setting or thermo¬ forming process, pressure is applied alonq al least two eπ- ordinate axes, whereby the angle between the axes is 30 -90 , c h a r a c t e r i z e d m that m order to attain the required pressures for each co-ordinate axis from one co¬ ordinate direction, a pressure element movable relative to the article is pressed against the article, while front thp opposite co-ordinate direction al least one principally form stable bucker-up element (11A. 11B, 11C) in conjunction with said pressure element is caused to provide a pressure (P , P ■ 7 λ that acts on the article and against the direction of the force of the pressure element, the pressure element and hucker- up element (11A, 11B, 11C), respectively, substantially cover¬ ing the cross section of the article perpendicularly to the re¬ spective co-ordinate axis. 2. Method according to claim 1, c h a r a c t e r i z e d in that the required heat for the hot-setting or thermoforming process is partly supplied via said bucker-up element. 3. Method according to claim 1 or claim 2, c h a r a c t e¬ r i z e d in that in addition to the form stable bucker- up ' element, a defor able bucker-up element in conjunction with said pressure element is caused to provide a pressure that acts on the article and against the direction of the force of the pressure element.

Inventors: HANSSON JAN, HANSSON, JAN
Applicants: SAAB SCANIA AB, SAAB-SCANIA AKTIEBOLAG
Application year: 1989
Main classification: B29C43
IPC codes: B29C70