Rudder assembly with a controlled boundary layer control for an

Details Rudder assembly with a controlled boundary layer control for an Rudder assembly with a controlled boundary layer control for an

1997-10-20

1999-05-04

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244 87, B64C 502

Patent

active

058994165

ABSTRACT:
The boundary layer flow along the surface of an aircraft rudder assembly is controlled by suction applied through perforations primarily installed in the leading edge of the rudder assembly. The control is such that a laminar flow is enforced or at least such that any turbulent flow is displaced so that it begins downstream of the rudder assembly leading edge. Suction air chambers are arranged along the leading edge inside a nose box of the rudder assembly and these boxes are connected through air ducts and a valve system to an exhaust fan. The valve system and the exhaust fan are controlled by a central processing unit providing a flow controller for the suction in response to control signals produced from rated values and sensed actual valves to provide a uniform distribution of the suction along the leading edge of the rudder assembly. The suction system may be switched over to a de-icing mode by blowing warm air out through the perforations in a controlled manner.

REFERENCES:
patent: 3887147 (1975-06-01), Grieb
patent: 3951360 (1976-04-01), Anxionnaz
patent: 4813631 (1989-03-01), Gratzer
patent: 5143329 (1992-09-01), Coffinberry
patent: 5263667 (1993-11-01), Horstman
patent: 5348256 (1994-09-01), Parikh
patent: 5598991 (1997-02-01), Nadkarni et al.
patent: 5740991 (1998-04-01), Gleine et al.
patent: 5772156 (1998-06-01), Parikh et al.
patent: 5779196 (1998-07-01), Timar

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