Rudder assembly with a controlled boundary layer control for an aircraft

US5899416A · kind A · utility

Assignee

• Daimler Chrysler Aerospace Airbus GmbH · DE

Inventors

• Juergen Meister · Neuenkirchen, DE
• Juergen Pfennig · Bruchhausen-Vilsen, DE
• Werner Held · Pöcking, DE

Key dates

• Filing date: Oct 20, 1997
• Grant date: May 4, 1999
• Expiry date: Oct 20, 2017

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/10
• WIPO field: Transport
• WIPO sector: Mechanical engineering

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.