Aircraft and methods of use for aerodynamic control with winglet surfaces

1. An aircraft for transonic flight comprising:

a fuselage extending to a back portion lacking a vertical tailfin, wherein the back portion comprises a first main body control surface and a second main body control surface;

a propulsor configured to generate thrust;

a first substantially swept wing having a first winglet disposed beyond the back portion of the fuselage, the first winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the first winglet comprises at least a first control surface including a first trailing edge of the first winglet, wherein the fuselage and a leading edge of the first substantially swept wing creates a continuous curvilinear geometry;

a second substantially swept wing having a second winglet disposed beyond the back portion of the fuselage, the second winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the second winglet comprises at least a second control surface including a second trailing edge of the second winglet, wherein the fuselage and a leading edge of the second substantially swept wing creates a continuous curvilinear geometry;

wherein the at least a first control surface and the at least a second control surface are independently movable and the at least a first control surface and the at least a second control surface each comprise at least two control surface segments, wherein each of the at least two control surface segments are independently positioned;

a first actuator configured to move the at least first control surface; and

a second actuator configured to move the at least second control surface, wherein an actuator of the first actuator and second actuator comprises a pneumatic actuator.

2. The aircraft of claim 1 , further comprising a blended wing body.

3. The aircraft of claim 1 , wherein the at least a first control surface and the at least a second control surface each comprise a rudder.

4. The aircraft of claim 1 , further comprising:

at least a first actuator configured to move the at least a first control surface;

at least a second actuator configured to move the at least a second control surface; and

a controller configured to control each of the at least a first actuator and the at least a second actuator.

5. The aircraft of claim 4 , wherein the controller is further configured to control each of the at least a first actuator and the at least a second actuator to reduce drag using the at least a first control surface and the at least a second control surface.

6. The aircraft of claim 4 , wherein the controller is further configured to control one or more of the at least a first actuator and the at least a second actuator to introduce a yaw moment using one or more of the at least a first control surface and the at least a second control surface.

7. The aircraft of claim 4 , wherein the controller is further configured to control one or more of the at least a first actuator and the at least a second actuator to introduce a side force using one or more of the at least a first control surface and the at least a second control surface.

8. The aircraft of claim 4 , wherein the controller is further configured to control each of the at least a first actuator and the at least a second actuator to adjust wing bending using the at least a first control surface and the at least a second control surface.

9. The aircraft of claim 4 , wherein the controller is further configured to control each of the at least a first actuator and the at least a second actuator to increase drag using the at least a first control surface and the at least a second control surface.

10. The aircraft of claim 9 , wherein:

the at least a first control surface and the at least a second control surface each comprise at least two control surface segments; and

the controller is further configured to increase drag by moving the at least two control surface segments in opposite directions.

11. A method of using an aircraft for transonic flight comprising a fuselage extending to a back portion lacking a vertical tailfin, wherein the back portion comprises a first main body control surface and a second main body control surface; a propulsor configured to generate thrust; a first substantially swept wing having a first winglet extending beyond the back portion of the fuselage, the first winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the first winglet comprises at least a first control surface including a first trailing edge of the first winglet, wherein the fuselage and a leading edge of the first substantially swept wing creates a continuous curvilinear geometry and a second substantially swept wing having a second winglet extending beyond the back portion of the fuselage, the second winglet comprising a carbon-fiber composite with carbon fibers between 5-10 micrometers at a distal end of the wing, wherein the second winglet comprises at least a second control surface including a second trailing edge of the second winglet, wherein the fuselage and a leading edge of the second substantially swept wing creates a continuous curvilinear geometry, wherein the at least a first control surface and the at least a second control surface are independently movable and the at least a first control surface and the at least a second control surface each comprise at least two control surface segments, wherein each of the at least two control surface segments are independently positioned, the method comprising:

driving, by a controller incorporated in the aircraft, at least a first actuator to move the at least a first control surface;

driving, by the controller, at least a second actuator to move the at least a second control surface; and

wherein an actuator of the at least first actuator and the at least second actuator comprises a pneumatic actuator.

12. The method of claim 11 , wherein driving the at least a first actuator and the at least a second actuator further comprises driving each of the at least a first actuator and the at least a second actuator to reduce drag.

13. The method of claim 11 , further comprising driving, using the controller, one or more of the at least a first actuator and the at least a second actuator to move one or more of the at least a first control surface and the at least a second control surface to introduce a yaw moment.

14. The method of claim 11 , further comprising driving, using the controller, one or more of the at least a first actuator and the at least a second actuator to move one or more of the at least a first control surface and the at least a second control surface to introduce a side force.

15. The method of claim 11 , further comprising driving, using the controller, the at least a first actuator and the at least a second actuator to move the at least a first control surface and the at least a second control surface to increase drag.

16. The method of claim 11 , further comprising driving, using the controller, the at least a first actuator and the at least a second actuator to move the at least a first control surface and the at least a second control surface to adjust wing bending.

17. The method of claim 11 , further comprising, driving, using the controller, the at least a first actuator and the at least a second actuator to move the at least a first control surface and the at least a second control surface to increase drag.

18. The method of claim 17 , wherein the method further comprises driving, by the controller, at least one of the at least a first actuator and the at least a second actuator to move the at least two control surface segments in opposite directions and increase drag.

19. The aircraft of claim 1 , wherein the fuselage comprises a nose portion, wherein the nose portion comprises a cockpit.

20. The aircraft of claim 19 , wherein the nose portion of the fuselage and a leading edge of a substantially swept wing creates a continuous curvilinear geometry.