one or more sensors positioned on the wing and counter the disturbance via one more actuator controlled flight surfaces the sensed forces may further be used to compensate for latency in angular rate sensors or to adapt actuator positions to compensate for system uncertainty and sensor bias considerations when implementing p wings may include the use a limited number of sensors implemented in tight simple control loops to enable outer loops to be designed with less knowledge of the inner loop dynamics much as current control systems rely on the servos to deliver consistent performance over their range of operation even though the underlying components may exhibit performance variations due to manufacturing variations loads and heating however such considerations can be customized to a particular vehicle configuration to address specific situations with the suavs as illustrated in fig1 a rather than a single conventional aileron configuration a p wing may use a plurality of span wise distributed independently actuated ailerons e g wing borne control surfaces or u201c flaperons u201d generally speaking a flaperon is a type of aircraft control surface that combines aspects of both flaps and ailerons in addition to controlling the roll or bank of an aircraft as do conventional ailerons both flaperons can be lowered together to function similarly to a dedicated set of flaps similarly both ailerons could also be raised which would give spoilerons the flaperon may incorporation on types of flaps or flap features including without limitation plain split slotted fowler junkers flap gouge fairey youngman zap krueger gurney and in certain aspects leading edge flaps such as leading edge droop and blown flaps the wing may utilize a continuous set of sensors e g strain torque measurement sensors along the wing to manipulate the span wise continuous trailing edge surface.