Adaptive wings application problem

The paper provides an adaptive aircraft wing design with an emphasis on the shape control system of the leading and trailing edges. The electromechanical actuator structural scheme intended to control adaptive wing form and damping oscillations is presented here; it allows reduction of mechanical parts wear. The prevailing paradigm for flight control actuation of a fixed wing aircraft involves deflection of small control surface actuators affixed to a geometrically static lifting body; the classical approach yields simple mechanisms, stable flight characteristics that are sufficiently described. However, numerous studies show that a multifunctional wing-shape adaptive mechanism for flight optimization and control would provide substantial improvements across nearly all flight conditions, including increased aerodynamic efficiency, drag reduction and enhanced lift-to-drag performance as well as enhanced maneuverability, reduced fuel consumption, increased actuator effectiveness, decreased actuator power requirements, increased control robustness, control redundancy, shorter required takeoff/landing and others.