Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Reexamination Certificate
1999-10-28
2001-09-11
Jordan, Charles T. (Department: 3644)
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
Reexamination Certificate
active
06286790
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to an aerofoil having a slat mounted to extend and retract relative to the aerofoil to increase lift especially during landing and take off of an aircraft.
2. Discussion of Prior Art
In certain aircraft, it is usual to provide a data link between the slat and the aerofoil to enable data such as pressure and temperature to be monitored. Known data links necessitate use of the usual slat mounting track to form a component of the data link. That involves complexity and considerable expense and an object of the present invention is to provide an aerofoil having a slat with an improved data link arrangement.
SUMMARY OF THE INVENTION
According to the invention there is provided an aerofoil having a slat mounted to extend and retract relative to the aerofoil and a data link extending between the slat and the aerofoil, the data link comprising a line arranged to lie against the aerofoil in the fully retracted position of slat and to extend across a gap between the aerofoil and the slat when the slat is in its fully extended position.
By using a simple line as set out above, the cost of providing the data link is reduced significantly and the data link is far less complex.
Preferably, the line is arranged to wrap around the leading edge of the aerofoil when the aerofoil is in its fully retracted position.
In the preferred embodiment, the line extends substantially along a straight line across the gap when the slat is in its fully extended position.
By causing the line to wrap around the leading edge of the aerofoil as set out above, the risk of fretting against the leading edge is minimised. Also, with the line extending substantially along a straight line between the aerofoil and the slat, the risk of vibration and significant flapping due to air flow is also substantially minimised.
In use, fluid flow between the aerofoil and the slat preferably causes the line to lie partially against the rear of the slat and to wrap partially around the leading edge of the aerofoil where the slat lies between the fully retracted and fully extended positions.
Preferably, the slat moves along a track on the aerofoil and, in such a case, the line is preferably positioned to one side of the track. In such a case, and where the aerofoil extends outwardly from a mounting such as an aircraft fuselage, the line is preferably arranged outboard of the track.
In the preferred embodiment, the line is carried by a support such as a cable anchored at one end to the aerofoil and at the other end to the slat. Tension in the support is preferably sufficient to maintain the support line substantially straight but insufficient to lead to vibration thereof resulting from air flow over the support and the line thereon when the slat is in its fully extended position. The positioning of anchor points on the aerofoil and slat for the support is preferably selected such that the shortest distance around the leading edge of the aerofoil between the two anchor points in the fully retracted position of the slat is substantially the same as the distance in a straight line between the two anchor points in the fully extended position of the slat.
REFERENCES:
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patent: 3792189 (1974-02-01), Grassl
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patent: 5680124 (1997-10-01), Bedell et al.
patent: 5839698 (1998-11-01), Moppert
patent: 6143987 (2000-11-01), Makita
patent: 0 397 438 (1990-11-01), None
patent: 0 680 878 (1995-11-01), None
BAE Systems plc
Dinh Tien
Jordan Charles T.
Nixon & Vanderhye P.C.
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