Abstract: Control systems and methods for a vehicle such as an aircraft or watercraft employ a trailing edge control surface that is pivotal about a pivot axis fixed relative to the vehicle and is deflected to create control forces, and a tab pivotally mounted to an aft end of the control surface. An aft end of a linkage is connected to the tab spaced from the tab pivot axis, and the linkage extends forward to a forward end that is coupled to fixed vehicle structure, such that deflection of the control surface causes a deflection of the tab as long as the forward end of the linkage does not lie in line with the control surface pivot axis, the in-line position defining a neutral position of the linkage. A gearing control actuator is coupled to the linkage and is operable to position the forward end of the linkage at selectively variable distances on one or the other side of the neutral position, thus providing variable gearing ratios between the control surface and the tab.

Abstract: First and second pylon flaps are located on aft portions of the first and second jet engine pylons, respectively. The first and second pylon flaps are moveable between retracted pylon flap angular orientations and extended pylon flap angular orientations. The first and second pylon flaps can assume only fully retracted angular orientations and fully extended angular orientations. When the T-tailed aircraft enters into a deep stall condition, the pilot will more than likely push the control column forward to its maximum position. This full forward movement of the control column commands the first and second pylon flaps to assume fully extended angular orientations. A first pylon flap controller controls the first pylon flap to move between the fully extended and fully retracted angular orientations, and a second pylon flap controller controls the second pylon flap to move between the fully extended and fully retracted angular orientations.

Abstract: An improved geared tab configuration for a moveable airfoil, such as an elevator of an aircraft, is provided which comprises a tab pivotally connected to the airfoil, and linkage connecting the airfoil to the tab for simultaneous opposing pivotal movement of the tab relative to the airfoil to a maximum tab deflection at a determinable intermediate upward airfoil deflection beyond which the relative tab deflection reverses and fairs to the airfoil at a determinable maximum upward airfoil deflection.