Methods of manufacturing single piece multi-spar boxes of composite material in a closed mould
First Claim
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1. A method of manufacturing a single piece multi-spar box made of composite material for aircraft, comprising:
- placing a bottom panel of composite material on a first plate and a top panel of composite material on a second plate;
suspending, above the bottom panel, one or more intermediate spars of composite material arranged between elongated inner tools which are each enclosed inside a respective pressurisable impermeable tubular bag;
arranging two outer lateral spars of composite material with a C-shaped cross-section inside two respective C-shaped seats formed in two respective rigid, lateral, outer tools, where the two outer lateral spars have respective concavities directed towards each other and the two seats have respective concavities directed towards each other;
moving the lateral outer tools towards each other such that the inner tools wrapped in pressurisable bags are partially inserted inside the C-shaped outer spars;
simultaneously lowering the inner tools and the lateral outer tools so as to bring bottom bases of said intermediate and lateral spars into contact with the bottom panel;
transferring the second plate with the top panel above said intermediate and lateral spars;
lowering the second plate so as to bring the top panel into contact with top bases of said intermediate and lateral spars;
locking the two lateral outer tools to the first plate and to the second plate, so as to form, together with the plates, a closed mould wherein in the closed mould condition the lateral outer tools are arranged vertically between the first plate and the second plate so as to support the second plateso that the multi-spar box to be polymerized is closed between the first plate, the second plate and the two lateral outer tools;
sealing open opposite ends of the tubular bags so that the pressure applied in an autoclave during a following polymerization step causes expansion of the tubular bags, compressing them against bases and cores of said intermediate and lateral spars; and
curing the box in an autoclave by applying a programmed cycle of heat and pressure.
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Abstract
Methods of making single piece multi-spar boxes made of composite material for aircraft are provided. Such methods include providing outer spars of the boxes which are made with a C-shaped cross-section such that the spars, during curing, are molded on the inside onto rigid, outer, lateral forming tools. As a result it is possible to obtain very precise outer profiles and positions of the spars.
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Citations
5 Claims
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1. A method of manufacturing a single piece multi-spar box made of composite material for aircraft, comprising:
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placing a bottom panel of composite material on a first plate and a top panel of composite material on a second plate; suspending, above the bottom panel, one or more intermediate spars of composite material arranged between elongated inner tools which are each enclosed inside a respective pressurisable impermeable tubular bag; arranging two outer lateral spars of composite material with a C-shaped cross-section inside two respective C-shaped seats formed in two respective rigid, lateral, outer tools, where the two outer lateral spars have respective concavities directed towards each other and the two seats have respective concavities directed towards each other; moving the lateral outer tools towards each other such that the inner tools wrapped in pressurisable bags are partially inserted inside the C-shaped outer spars; simultaneously lowering the inner tools and the lateral outer tools so as to bring bottom bases of said intermediate and lateral spars into contact with the bottom panel; transferring the second plate with the top panel above said intermediate and lateral spars; lowering the second plate so as to bring the top panel into contact with top bases of said intermediate and lateral spars; locking the two lateral outer tools to the first plate and to the second plate, so as to form, together with the plates, a closed mould wherein in the closed mould condition the lateral outer tools are arranged vertically between the first plate and the second plate so as to support the second plate so that the multi-spar box to be polymerized is closed between the first plate, the second plate and the two lateral outer tools; sealing open opposite ends of the tubular bags so that the pressure applied in an autoclave during a following polymerization step causes expansion of the tubular bags, compressing them against bases and cores of said intermediate and lateral spars; and curing the box in an autoclave by applying a programmed cycle of heat and pressure. - View Dependent Claims (2, 3, 4, 5)
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Specification