split rudder airplaneshinedown attention attention
Soar_dude. : 1,841,804, 1,875,593, 1,916,475, 1,992,158, 2,045,463, and 2,166,292, all to Hall; 1,854,444 to Barnhart; 2,241,335 to Wedberg; 2,279,615 to Bugatti; and 2,412,647 to Northrop. The Split-S: The Split-S is essentially an inverted Immelmann turn, if you like. Lower control member 80 also has a lower surface 84 which extends between first forward end 81 and first aft edge 82, and a convex-upward first upper surface 86 which extends forward from first aft edge 82 and away from lower surface 84 to a peak edge 87. Chord line C extends between the leading edge 12 of wing 10 and the wing trailing edge, which in FIG. The U. S. Government has a paid-up license in this invention and the right in limited circumstances to require the patent owner to license others on reasonable terms as provided for by the terms of contract number F33657-81-C-0067 awarded by the United States Air Force.This application is a continuation-in-part of commonly-assigned application Ser. Furthermore, it has been found that the aerodynamic feature of the present invention does not adversely increase aerodynamic drag or radar cross section, the latter being a valuable attribute of the invention for use in a stealth type of aircraft.Other and further features, advantages, and benefits of the present invention will become apparent in the following description taken in conjunction with the following drawings. Split Rudder Air Brake. The split rudder control system as claimed in claim 10 wherein said aerodynamic feature smoothly deflects airstream flow over said upper wing surface approaching said trailing edge initially away from said plane of said chord line and thence toward said plane of said chord line, whereby a velocity of said airstream flow is increased to a local maximum velocity at a location forward of said trailing edge generally proximate said peak edge and said second aft edge and a local static pressure at said location is reduced relative to a static pressure at said trailing edge, said reduced local static pressure being communicated into said control cavity and reducing net opening hinge moments acting on said upper and lower control members.Split rudder control system aerodynamically configured to facilitate closure No. In the closed position, the forward portion forms a portion of the upper surface of the wing, and thus has a shape as taught by methods known in the conventional aerodynamic art for that portion of the wing and the applicable aerodynamic design conditions.From the forward tangent point, however, a transition portion of the second upper surface extends aft in a concave-upward direction away from the lower opposing surface to an aft tangent point (again as viewed in cross section), and an aft portion of the second upper surface extends in a convex-upward direction from the aft tangent point to the second aft edge.In the closed position, the second aft edge of the upper control member is positioned proximate to, but spaced from and forward of, the peak edge of the lower control member. Chord line C extends between the leading edge 12 of wing 10 and the wing trailing edge, which in FIG. I'm using channel 4 for braking. 2.In accordance with the invention, lower and upper control members 80 and 90 are pivotally secured to wing 10 about lower and upper control axes 40 and 50 respectively.Lower control member 80 has a first forward end 81 pivotally connected to wing 10 by lower control axis 40, which is spaced forward from and generally parallel with first aft edge 82. That could also mean a rigidly split rudder will still want to flutter as a unit. 1.Lower control member 20 is pivotally mounted to wing 10 about a lower control axis 40 which is spaced forward from and generally parallel with aft edge 22 of lower control member 20. 2, a split rudder control system in accordance with the invention, comprising lower and upper control members 80, 90, respectively, is shown on wing 10 with control members 80, 90 in the closed position.
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