초록 ▼

A mobile platform lift increasing system includes at least one wing-shaped structure having a leading edge, a trailing edge and a chord length perpendicularly measurable between the leading and trailing edges. A rotatable control surface is located near a trailing edge undersurface. The control surf

A mobile platform lift increasing system includes at least one wing-shaped structure having a leading edge, a trailing edge and a chord length perpendicularly measurable between the leading and trailing edges. A rotatable control surface is located near a trailing edge undersurface. The control surface length is approximately one to five percent of the chord length. A deployment device is positioned between the wing shaped structure and the control surface. The deployment device operably rotates the control surface through a plurality of positions ranging between an initial position and a fully deployed position. Wing lift is increased at speeds up to approximately transonic speed by continuously rotating the control surface to accommodate variables including mobile platform weight change from fuel usage.

대표청구항 ▼

1. A spanload modification system for a mobile platform, comprising:at least one wing-shaped structure having a leading edge, a trailing edge, and an aileron, and a chord length measurable between said leading and trailing edges; and at least one control surface disposed on said wing-shaped structur

1. A spanload modification system for a mobile platform, comprising:at least one wing-shaped structure having a leading edge, a trailing edge, and an aileron, and a chord length measurable between said leading and trailing edges; and at least one control surface disposed on said wing-shaped structure having a first end rotatably disposed about a point forward of said trailing edge, a second distal end, and a length measurable between said first end and said second distal end ranging between approximately one to approximately five percent of said chord length; wherein each said control surface operably rotates about said first end through a plurality of positions ranging between an initial position having said control surface approximately parallel to said wing-shaped structure and a fully deployed position having said second end angularly displaced from said initial position. 2. The system of claim 1, comprising: a deployment device disposed between said wing-shaped structure and said control surface; wherein said control surface comprises a rigid plate; wherein said deployment device is operable to rotate said rigid plate through said plurality of positions.3. The system of claim 2, comprising a control system in communication with said deployment device capable of continuously signaling each of a plurality of position changes for said deployment device.4. The system of claim 3, wherein said control system comprises a data set including an altitude, a speed, a weight, a distance traveled and a wing-shaped structural load of said mobile platform.5. The system of claim 4, comprising:said weight of said mobile platform corresponds to a continuously decreasing mobile platform remaining fuel; and said control system operably generates a continuously variable declination angle for said control surface to compensate for said continuously decreasing remaining fuel. 6. The system of claim 4, comprising a maximum deployment position of said control surface determinable from said data set.7. 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. 8. The flight surface of claim 7, comprising a control surface nominal rotation angle ranging from said initial position having an angle with respect to said wing of approximately zero degrees to said deployed position having an angle of up to 90 degrees below said wing.9. The flight surface of claim 7, comprising:a control surface maximum deployed position; and a control surface maximum rotation angle of approximately 90 degrees below said wing measurable between said initial position having an angle with respect to said wing of approximately zero degrees and said maximum deployed position. 10. The flight surface of claim 7, wherein said deployment device comprises:an actuator disposed on one of said plurality of wings or said control surface; and a rod positionable by said actuator, said rod contacting an opposite one of said one wing and said control surface having said actuator disposed thereon, to rotate said control surface. 11. The flight surface of claim 9, wherein said deployment device comprises an inflatable chamber having a diameter varying between a minimum diameter corresponding to said control surface initial position and a maximum diameter corresponding to said control surface maximum deployed position.12. The flight surface of claim 7, comprising:said at least one wing includes a pair of opposed wings; and said at least one control surface includes a plurality of independent control surfaces arranged in an edge adjacent configuration on each of said pair of wings. 13. The flight surface of claim 12, wherein said deployment device comprises a plurality of individual devices each in communication with one of said plurality of control surfaces.14. The flight surface of claim 13, comprising said edge adjacent configuration including one of said independent control surfaces adjacent a tip of each said wing.15. The flight surface of claim 13, comprising said plurality of control surfaces of each said wing being operable as a single group from an underside of said trailing edge of said wing.16. The flight surface of claim 13, comprising said plurality of control surfaces of each said wing being individually operable as a plurality of separate groups from an underside of said trailing edge of said wing.17. 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. 18. The method of claim 17, comprising:continuously calculating a mobile platform fuel usage rate; and optimizing a wing aerodynamic load distribution with the wing control surface for a decreasing mobile platform weight due to the fuel usage rate. 19. The method of claim 17, comprising modifying the wing control surface declination angle to compensate for each of a mobile platform altitude, speed, weight, distance traveled and wing-shaped structural load.20. The method of claim 17, comprising adjusting the wing control surface in one of a failure mode and an automatic mode.21. The method of claim 17, comprising operating the control surface for a mobile platform speed up to approximately a transonic speed.22. 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.