Aircraft fin and rudder

Details Aircraft fin and rudder Aircraft fin and rudder

1999-11-05

2001-03-20

Barefoot, Galen L. (Department: 3644)

Aeronautics and astronautics

Aircraft control

Rudders and empennage

C244S130000

Reexamination Certificate

active

06202959

ABSTRACT:

BACKGROUND OF THE INVENTION
The invention relates to an aircraft fin and rudder and is particularly concerned with an aircraft fin and rudder arrangement which will improve fin and rudder effectiveness.
SUMMARY OF THE INVENTION
According to the invention an aircraft fin and rudder arrangement comprises an end plate at the upper end of the fin, the end plate being arranged to contact or lie closely adjacent the upper end of the rudder at all rudder deflections.
By providing such an end plate, the fin and rudder lift curve slopes are increased and the maximum side force generated by the rudder is increased thereby enabling the size of the fin and rudder to be reduced whilst providing the side force previously achieved by a larger arrangement. That, in turn, is useful in that bending moment at the fin root can be reduced when compared to that of a taller fin for a given side force.
Preferably, the upper end of the rudder seals against the end plate at all rudder deflections. In that way, effectiveness of the rudder is optimised at all deflected positions.
Generally, the rudder will pivot about an inclined hinge. To minimise clearance or maintain sealing contact between the upper end of the rudder and the end plate at all rudder deflections, the end plate preferably has a suitably selected dihedral.
The end plate may have a delta plan form, the delta preferably being slender and preferably having an angle which is no greater than that required to ensure that the upper end of the rudder will remain covered by the end plate at all rudder deflections.
In the preferred embodiment, the end plate has an angular setting relative to the incident airflow to minimise drag thereof in the aircraft cruise condition. In such a case, the end plate may be set at a negative angle (i.e. leading edge down) to the horizontal datum of a fuselage on which the fin is mounted in use. Once the aircraft has a reached a cruising condition, the end plate will normal present a zero angle to the direction of relative air flow thereby minimising drag.


REFERENCES:
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patent: 5518210 (1996-05-01), Friberg
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