Rudder assembly with a controlled boundary layer control for...

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

B - Operations, Transporting

64

C

B64C 21/04 (2006.01) B64C 21/06 (2006.01) B64C 21/08 (2006.01) B64D 15/00 (2006.01)

Patent

CA 2218800

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.

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