Aircraft wing comprising a controllable-attack wing tip
An aircraft wing, including a main part and a wing tip mounted mobile in attack relative to the main part.
1. An aircraft wing comprising:
a main part,
a wing tip mounted mobile in attack relative to the main part, and
a junction device between the wing tip and the main part of the wing, the junction device being configured to allow rotation of the wing tip relative to the main part about a first rotation axis enabling control in attack of the wing tip, and to allow rotation of the wing tip relative to the main part about a second rotation axis enabling the wing tip to be folded to raise the wing tip,
wherein the wing tip is mounted mobile in attack relative to the main part in accordance with a limited pivot amplitude about the first axis of rotation, wherein said limited pivot amplitude is capable of pivoting in a range of angles between 15° and −90°.
2. The aircraft wing as claimed in claim 1 , wherein the first rotation axis is substantially parallel to a spanwise direction of the wing or is oriented substantially along a transverse direction of the aircraft, and wherein the second rotation axis is substantially parallel to a direction of flow of the airflow over the wing.
3. The aircraft wing as claimed in claim 1 , wherein said limited pivot amplitude is capable of pivoting in a range of angles between 15 and −15°.
4. The aircraft wing as claimed in claim 1 , wherein the junction device includes a first actuator and a second actuator respectively enabling control in attack and control in folding.
5. The aircraft wing of claim 1 , the junction device is configured to allow rotation of the wing tip relative to the main part about a first rotation axis enabling control in attack of the wing tip via a first actuator, and to allow rotation of the wing tip relative to the main part about a second rotation axis enabling the wing tip to be folded to raise the wing tip via a second actuator, wherein the second actuator is located between the first actuator and the main part.
6. The aircraft of claim 5 , wherein the first actuator is positioned perpendicularly to a chord of the wing, at approximately 40% of a total length of the chord.
7. The aircraft of claim 5 , wherein the second actuator is oriented substantially parallel to a direction of flow of airflow over the wing.
8. The aircraft of claim 7 , wherein the first actuator is oriented substantially perpendicularly to the first second actuator.
9. An aircraft comprising at least one wing, the aircraft wing comprising:
a main part,
a wing tip mounted mobile in attack relative to the main part, and
a junction device between the wing tip and the main part of the wing, the junction device being configured to allow rotation of the wing tip relative to the main part about a first rotation axis enabling control in attack of the wing tip via a first actuator in the wing tip, and to allow rotation of the wing tip relative to the main part about a second rotation axis enabling the wing tip to be folded to raise the wing tip via a second actuator,
wherein the second actuator is located between the first actuator and the main part.
10. The aircraft of claim 9 , wherein the first actuator is positioned perpendicularly to a chord of the wing, at approximately 40% of a total length of the chord.
11. The aircraft of claim 9 , wherein the second actuator is oriented substantially parallel to a direction of flow of airflow over the wing.
12. The aircraft of claim 11 , wherein the first actuator is oriented substantially perpendicularly to the first second actuator.
13. A method of controlling an aircraft wing, the wing comprising:
a main part,
a wing tip mounted mobile in attack relative to the main part, and
a junction device between the wing tip and the main part of the wing, the junction device being configured to allow rotation of the wing tip relative to the main part about a first rotation axis enabling control in attack of the wing tip via a first actuator, and to allow rotation of the wing tip relative to the main part about a second rotation axis enabling the wing tip to be folded to raise the wing tip via a second actuator, wherein the second actuator is located between the first actuator and the main part, and,
the method comprising the step of controlling the wing tip in attack relative to the main part of the wing as a function of at least one flight parameter.
14. The method according to claim 13 , wherein said at least one flight parameter comprises an altitude of the aircraft.
15. The method according to claim 13 , wherein said at least one flight parameter comprises a mass of the aircraft.