초록 ▼

The invention provides a wing structure for an aircraft, including a top skin and a bottom skin defining a primary wing surface, the surface having a width, a length, a leading edge and a trailing edge; a flap having a width smaller than the width of the wing surface and a length extending over a ma

The invention provides a wing structure for an aircraft, including a top skin and a bottom skin defining a primary wing surface, the surface having a width, a length, a leading edge and a trailing edge; a flap having a width smaller than the width of the wing surface and a length extending over a major portion of the wing length, the flap being hingedly joined adjacent to the trailing edge of the wing, wherein the flap is capable of assuming two limit dispositions, a first disposition in which the flap extends substantially parallel to the bottom skin, and a second disposition extending towards the trailing edge of the wing, at an obtuse angle. A method for slowing down the speed of flight of an aircraft is also provided.

대표청구항 ▼

What is claimed is: 1. A wing structure for an aircraft, comprising: a top skin and a bottom skin defining a primary wing surface, said surface having a width, a length, a leading edge and a trailing edge; at least one abutment surface connected to the trailing edge; a flap having a width smaller t

What is claimed is: 1. A wing structure for an aircraft, comprising: a top skin and a bottom skin defining a primary wing surface, said surface having a width, a length, a leading edge and a trailing edge; at least one abutment surface connected to the trailing edge; a flap having a width smaller than the width of the wing surface and a length extending over a major portion of the length; said flap being hingedly joined adjacent to the trailing edge; wherein said flap is capable of assuming two limit dispositions, a first disposition in which said flap extends substantially parallel to the bottom skin, and a second disposition extending towards the trailing edge at an obtuse angle and contacting the abutment surface; and a detent means for maintaining the flap at said first disposition; wherein movement of said flap from the first disposition to the second disposition is effected by gravity and air flow upon release of the detent means. 2. The wing structure as claimed in claim 1, wherein said detent means is at least one pivotable hook attached adjacent to the leading edge of the wing. 3. The wing structure as claimed in claim 1, wherein said abutment has a surface defining said obtuse angle. 4. The wing structure as claimed in claim 1, wherein said bottom skin has a recess for at least partly accommodating said flap in its first position. 5. The wing structure as claimed in claim 1, wherein said detent means is electrically activatable. 6. A moveable member on an aircraft including an aerodynamic body, and wings, each wing having a bottom surface, a width, a length, leading and trailing edges and tail structures, said moveable member comprising: an abutment surface connected to the trailing edge of the wing; and at least a semi-rigid flap having a width smaller than the width of the wings and a length extending over a major portion of the wing length, said flap being hingeably joined adjacent to the trailing edge of a wing allowing it to assume two limit dispositions, a first disposition in which the flap extends substantially parallel to the bottom surface of the wing and a second disposition in which said flap, being hinged at its leading edge, extends towards the tail of the aircraft at an obtuse angle with respect to said bottom surface, and contacts said abutment surface, movement of the flap from said first disposition to the second disposition being effected by gravity and air flow. 7. The moveable member as claimed in claim 6, further comprising releasable detent means for maintaining said flap in the first disposition and for releasing it to allow movement to the second disposition. 8. The moveable member as claimed in claim 6, further comprising at least one abutment connected to the bottom surface of the trailing edge of said wings, said abutment having a surface defining the second disposition. 9. The moveable member as claimed in claim 6, wherein in said first disposition said flap is at least partly accommodated in a recess made in the bottom surface of the wing. 10. The moveable member as claimed in claim 7, wherein said detent means is electrically activatable to release said flap. 11. A method for slowing down the speed of flight of an aircraft, comprising: providing at least one moveable member including at least a semi-rigid flap hingeably joined to a wing of said aircraft; providing at least one abutment surface connected to the trailing edge of the wing, releasably affixing said flap in a first disposition in which said flap extends substantially parallel to said wing, and when the speed of the aircraft is to be slowed down, releasing said flap so as to allow it to swing about the hinge at its trailing edge and to assume a second disposition by gravity and air flow, in which said flap extends towards the tail of said aircraft at an obtuse angle with respect to said wing and contacts said abutment surface. 12. The method as claimed in claim 11, wherein said flap is releasably affixed in said first disposition by means of at least one pivotable hook. 13. The method as claimed in claim 11, wherein said flap is releasably affixed by means of electrically actuatable detent means. 14. The method as claimed in claim 13, wherein said electrically actuatable detent means comprises a solenoid.