Abstract: The invention is a proportional rudder boost system for manually controlled aircraft which also have a yaw dampening system. The boost system includes four sensors in the pilot's and copilot's pedals including a summation means which adds the manual inputs from both pilots to provide a combined output signal to the power boost computer. Once the combined output signal exceeds a minimum force level, the boost computer signals the yaw servo to increase its torque applied to the rudder from zero in proportion to the increase in manual force applied to the rudder pedals up to a maximum power assist force level.

Abstract: A thin, high performance swept wing of the tapered type with an improved leading edge characterized by (1) camber that increases from a minimum near the wing root to a maximum near the wing tip, and (2) substantially a constant leading edge radius extending substantially across the wing span which defines a "blunt" contour. The wing in combination with a T-tail aircraft with a stick shaker/pusher activated by a rate of change of angle of attack sensor and optionally a strake between the leading edge and a wing tip tank which intrinsically combine to define a system that enhances aircraft performance by reducing minimum airspeed without impairing aircraft performance at high subsonic Mach (M) numbers.