Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Patent
1995-05-24
1997-08-12
Kashnikow, Andres
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
244215, 244216, 244217, B64C 350, B64C 916, B64C 920
Patent
active
056557370
ABSTRACT:
A split rudder control system for an aircraft which reduces the net opening hinge moments opposing return of the split rudders to the fully closed position from small deflection angles. The split rudder control system provides a smoothly faired aerodynamic protuberance on the upper surfaces of the split rudder control members adjacent to the trailing edge of the wing when the control members are in the closed position and at small deflection angles relative to the closed position. The aerodynamic protuberance smoothly deflects the airstream flow over the upper surface of the wing as it approaches the trailing edge, increasing the local velocity of the airstream at a point forward of the trailing edge. The aerodynamic feature is contoured such that a maximum local airstream velocity occurs generally at the interfacing edges of the control members. The local static pressure at that location is reduced relative to the static pressure at the trailing edge in accordance with Bernoulli's principle, and the reduced pressure is communicated into the control cavity between the control members. The lower control cavity pressure reduces the net opening hinge moments acting on the control members at small deflection angles, facilitating full closure of the control members.
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Sears William B.
Wasson Norman F.
Williams Edgar P.
Anderson Terry J.
Hoch Jr. Karl J.
Kashnikow Andres
Mojica Virna Lissi
Northrop Grumman Corporation
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