Plastic and nonmetallic article shaping or treating: processes – Laser ablative shaping or piercing
Patent
1995-09-21
1998-04-21
Watkins, William
Plastic and nonmetallic article shaping or treating: processes
Laser ablative shaping or piercing
428137, 428131, 428113, 428107, 428109, 428114, 2191217, 21912171, 21912172, 181292, B23K 2600
Patent
active
057414564
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
The present invention relates to aircraft carbon fibre panels, a method of making aircraft carbon fibre panels, an aircraft incorporating a carbon fibre panel and a method of using an aircraft carbon fibre panel.
U.S. Pat. No. 4,612,737 (Rohr) discloses a method of making an aircraft carbon/carbon panel in which holes are drilled in the panel. Rohr also states that laser drilling was tried but was undesirable.
SUMMARY OF THE INVENTION
According to one aspect of the present invention a method of making an aircraft carbon fibre panel which includes permeable openings therethrough comprising forming a layer having a first and second side, the layer including a plurality of fibres and epoxy resin and subjecting the layer to heat and pressure is characterised in that the openings are subsequently burnt through the panel from the first side to the second side with a laser and in that the region of the layer adjacent to the second side is formed with substantially unidirectionally extending fibres.
The method may comprise forming the region adjacent to the second side with substantially unidirectionally extending fibres.
The method may comprise forming more than one, or forming all regions of the layer with substantially unidirectional fibres. Adjacent regions of substantially unidirectionally extending fibres may extend in different directions. The method may comprise forming the panel by arranging for adjacent regions of unidirectionally extending fibres to extend at different angles to each other, for example at 0.degree.,90.degree.,45.degree. and 135.degree. with respect to each other or at 0.degree.,90.degree.,45.degree.,135.degree.,135.degree.,45.degree.,90.degr ee. and 0.degree. relative to each other.
The method may comprise forming the panel as a substantially flat panel. Alternatively the method may comprise forming at least a part of the panel as a curved panel which may include a double curvature. Alternatively the method may comprise forming the panel as a tubular panel.
The present invention also includes an aircraft carbon fibre panel including a plurality of permeable openings therethrough characterised in that the openings have been formed by burning through the layer from a first side to a second side with a laser and in that the region of the layer adjacent to the second side has substantially uni-directionally extending fibres.
The cross sectional area of the openings may be less than 32k, 8k, 5k or in the region of 2k microns.sup.2. The openings may be substantially circular in cross section. One side of the panel at least may include substantially unidirectionally extending fibres. The layer may include more than one region including, or all regions of the layer may include, substantially unidirectional fibres. Adjacent regions within the layer having unidirectional fibres may have different extents for the unidirectional fibres. The layer may include adjacent regions going across the layer having unidirectional fibres extending at 0.degree.,90.degree.,45.degree., and 135.degree. to each other or at 0.degree.,90.degree.,45.degree.,135.degree.,135.degree.,45.degree.,90.degr ee. and 0.degree. to each other.
The panel may comprise a substantially flat panel. Alternatively the panel may include at least a part which is curved or which includes a double curvature and the panel may comprise a substantially tubular panel.
The present invention also incorporates an aircraft carbon fibre panel as herein referred to or an aircraft carbon fibre panel which has been made by a method as herein referred to.
The present invention also includes a method of using an aircraft carbon fibre panel as herein referred to or the method of using an aircraft carbon fibre panel which has been made by a method as herein referred to comprising allowing fluid (such as air) to be located within the openings, and may comprise pressure in the fluid passing from one side to the other and may further comprise fluid flowing through the openings.
The present invention includes any combination of
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Butje, "Optimal mit Angepassten Strahlgoellen und Prozessparamevern", Technische Rundschare, No. 31, Aug. 1991 Bern, CH pp. 32-38.
Hurel DuBois UK Limited
Watkins William
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