Variable trailing edge geometry and spanload control

A variable trailing edge geometry flight surface for an aircraft, comprising:

• a plurality of wings each having a leading edge, a trailing edge, at least one flap, at least one aileron, and a chord length perpendicularly measurable between said leading and trailing edges;
• at least one control surface connectably disposed adjacent an undersurface of said trailing edge between any one of said at least one flap or said at least one aileron and said trailing edge, said at least one control surface having a length measurable along said chord length ranging between approximately one to approximately five percent of said chord length;
• said control surface including a forward facing edge forming an axis of rotation for said control surface and a distally extending edge;
• and
• a deployment device connectably disposed to said control surface and operable to move said control surface about said axis of rotation from an initial position to a deployed position, and return said control surface to said initial position.

A method of varying a trailing edge geometry of a mobile platform wing, comprising the steps of:

• rotatably disposing a wing control surface adjacent an aft, lower portion of a platform wing;
• positioning said wing control surface between any one of a flap and an aileron connected to said wing and a wing trailing edge;
• defining a wing control surface rotation path variable between an initial position and a deployed position;
• and
• continually adjusting a declination angle of the wing control surface throughout said rotation path to compensate for a plurality of mobile platform operating conditions.

A variable trailing edge geometry flight surface system for an aircraft wing, comprising:

• a wing having a leading edge, a trailing edge, a flap, an aileron, and a chord length measurable between the leading and trailing edges;
• a control surface positionable between any one of the flap or the aileron and the trailing edge, the control surface having a length defining a portion of the chord length, the length ranging between approximately one to approximately five percent of the chord length;
• a forward facing edge of the control surface defining an axis of rotation of the control surface;
• a deployment device connectable to the control surface and operable to move the control surface about the axis of rotation;
• and
• a computer in communication with the deployment device, the computer operable to identify a wing load distribution and vary the wing load distribution by controlling operation of the deployment device.