초록 ▼

A laminar flow control system for incorporation in, for example, an aircraft flying surface includes a suction panel comprising a perforated skin ( 20, 40 ) mounted on a base member ( 60 ), a plenum chamber ( 30 ) being in communication with a plurality of micro channels ( 90 ) formed in the top sur

A laminar flow control system for incorporation in, for example, an aircraft flying surface includes a suction panel comprising a perforated skin ( 20, 40 ) mounted on a base member ( 60 ), a plenum chamber ( 30 ) being in communication with a plurality of micro channels ( 90 ) formed in the top surface of the base member ( 60 ), the micro channels ( 90 ) being in communication with the holes ( 40 ) in the skin ( 20 ).

대표청구항 ▼

1. A suction panel for use in a laminar flow control system, said panel comprising:a skin, said skin having a plurality of perforations therethrough;a base member supporting said skin, said base member including at least one plenum chamber supplied with a suitable source of suction; andat least one

1. A suction panel for use in a laminar flow control system, said panel comprising:a skin, said skin having a plurality of perforations therethrough;a base member supporting said skin, said base member including at least one plenum chamber supplied with a suitable source of suction; andat least one micro channel formed between said skin and said base member, said micro channel connecting said at least one plenum chamber to said plurality of perforations, said micro channel having a cross-sectional area which varies along said micro channel between said plenum and at least one of said plurality of perforations in which the perforated skin is mounted on a base member having a first base layer and a second base layer, the micro channels being formed in the first base layer and at least one plenum chamber being formed in the second base layer, with the micro channels being such that a controlled pressure gradient can be established therealong to ensure no outflow therefrom via the skin perforations. 2. A suction panel as claimed in claim 1 in which the perforated skin is bonded to the base member. 3. A suction panel as claimed in claim 1 in which at least one of the first base layer and second base layer comprises at least one layer of carbon fibre composite (CFC). 4. A laminar flow control system which comprises:a skin, said skin having a plurality of perforations therethrough;a base member supporting said skin, said base member including at least one plenum chamber supplied with a suitable source of suction;at least one micro channel formed between said skin and said base member, said micro channel connecting said at least one plenum chamber to said plurality of perforations, said micro channel having a cross-sectional area which varies along said micro channel between said plenum and at least one of said plurality of perforations; andmeans for applying suction to the plenum chambers in order to maintain boundary layer suction on a free surface of the perforated skin. 5. A suction panel for use in a laminar flow control system, said panel comprising:a skin, said skin having a plurality of perforations therethrough;a base member supporting said skin, said base member including at least one plenum chamber supplied with a suitable source of suction; andat least one micro channel formed between said skin and said base member, said micro channel connecting said at least one plenum chamber to said plurality of perforations, said micro channel having a cross-sectional area which varies along said micro channel between said plenum and at least one of said plurality of perforations. 6. A suction panel as claimed in claim 5 in which the perforated skin is a metal. 7. A suction panel as claimed in claim 5 in which the perforated skin is made of a pliable material which enables said material to be stretched over a surface on which it is mounted. 8. A suction panel as claimed in claim 5, in combination with a laminar flow control system. 9. A method of manufacturing a suction panel as claimed in claim 5, including the step of employing a laser beam to form the micro channels and the perforations in the skin. 10. An aircraft flying surface incorporating a laminar flow control system as claimed in claim 5. 11. A suction panel in accordance with claim 5, wherein said cross-sectional area varies smoothly along said channel. 12. A suction panel in accordance with claim 5, wherein said source of suction comprises a means for applying suction to said plenum chamber said suction sufficient for maintaining boundary layer suction along said perforated skin. 13. An aircraft flying surface incorporating a laminar flow control system as claimed in claim 12. 14. A suction panel for use in a laminar flow control system, said panel comprising:a skin, said skin having a plurality of perforations therethrough;a base member supporting said skin, said base member including at least one plenum chamber supplied with a suitable source of suction; andat least one micro channel formed between said skin and said base member, said micro channel connecting said at least one plenum chamber to said plurality of perforations, said micro channel having a cross-sectional area which varies along said micro channel between said plenum and at least one of said plurality of perforations, wherein said cross-sectional area varies stepwise along said channel. 15. A suction panel for use in a laminar flow control system, said panel comprising:a skin, said skin having a plurality of perforations therethrough;a base member supporting said skin, said base member including at least one plenum chamber supplied with a suitable source of suction; andat least one micro channel formed between said skin and said base member, said micro channel connecting said at least one plenum chamber to said plurality of perforations, said micro channel having a cross-sectional area which varies along said micro channel between said plenum and at least one of said plurality of perforations, wherein said at least one micro channel comprises a plurality of parallel micro channels and said plenum chamber extends perpendicular to said micro channels.