Single slotted flap with sliding deflector flap and lowerable spoiler

1. A device for adjusting the lift characteristics of an aircraft, comprising:

a high lift device;

a first slot covering device;

a second slot covering device; and

a wing element;

wherein the high lift device is movably attached to the wing element such that a slot is defined by a gap formed between the high lift device and the wing element, when the high lift device is extended rearwardly from the wing element;

the first slot covering device and the second slot covering device are movably attached to the wing element; the first slot covering device is movably and controllably attached on an underside of the wing element to regulate an opening size between the underside of the wing element and the high lift device; and the second slot covering device is movably and controllably attached to a top of the wing element to regulate an opening size of the slot between the top of wing element and the high lift device, such that the opening size of the slot between the top of the wing element and the high lift device and the opening size of the slot between the underside of the wing element and high lift device are regulatable; and

the first slot covering device, the second slot covering device, or both the first slot covering device and the second slot covering device are retractable into indentations in the wing element; and

the first slot covering device, the second slot covering device, or both the first slot covering device and the second slot covering device being movable rearward along the indentations such that the first slot covering device, the second slot covering, or both the first slot covering device and the second slot covering device extend in the direction of the high lift device so as to selectively and controllably or regulatably close the slot when the high lift device is extended rearwardly from the wing element.

2. The device of claim 1 , wherein the first slot covering device and the second slot covering device are attached so as to be rotatable on a longitudinal axis of the wing element.

3. The device of claim 1 , wherein the high lift device is movably attached to a rear region of the wing element.

4. The device of claim 1 , wherein the high lift device is hingedly attached to the wing element such that the high lift device is capable of being hinged downward from the wing element.

5. The device of claim 1 , wherein the first slot covering device is independently movable from the second slot covering device such that the opening size of the slot between the underside of the wing element and the high lift device is independently regulatable from the opening size of the slot between the top of the wing element and the high lift device by regulating the movement of the first slot covering device and the second slot covering device independently.

6. A method for adjusting the lift characteristics of an aircraft using the device of claim 1 , comprising:

regulating the opening size of the slot between the top, underside or both top and underside of the wing element and the high lift device using the first slot covering device, the second slot covering device or both the first slot covering device and the second slot covering device during one phase of flight;

retracting the first slot covering device, the second slot covering device or both the first slot covering device and the second slot covering device into an indentation in the wing element during another phase of flight; and

moving the first slot covering device, the second slot covering device, or both the first slot covering device and the second slot covering device being movable rearward along the indentations such that the first slot covering device, the second slot covering device, or both the first slot covering device and the second slot covering device extend in the direction of the high lift device and selectively and controllably or regulatably close the slot when the high lift device is extended rearwardly from the wing element.

7. The method of claim 6 , wherein the method includes a step of extending rearward the high lift device or a step of hinging downwardly the high lift device or both steps of extending and hinging during a takeoff phase or a landing phase or both takeoff and landing phases.

8. The method of claim 6 , wherein the step of regulating of the method includes a step of closing the slot during a takeoff phase by using both the first slot covering device and the second slot covering device.

9. The method of claim 6 , wherein the method includes a step of extending rearwardly the high lift device or a step of hinging downwardly the high lift device Or both steps of extending and hinging during a landing phase of the aircraft.

10. The method of claim 6 , wherein the step of regulating of the method includes a step of controlling the slot by regulating the second slot covering device, independently of the first slot covering device, such that stalling is prevented during a landing phase.

11. The method of claim 6 , further comprising:

regulating the opening size of the slot between the underside of the wing element and the high lift device independently of the opening size of the slot between the top of the wing and the high lift device by moving the second slot covering device independently of the first slot covering device.

12. The method of claim 6 , wherein the method includes a step of providing an on-board computer for controlling the first and second slot covering devices or the high lift device or both the first and second slot covering devices and the high lift device.

13. The method of claim 12 , wherein the step of providing the on-board computer includes selecting control parameters of the on-board computer from the group consisting of flight speed, angle of attack, wing profile, air pressure, temperature and flight altitude.