Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Reexamination Certificate
1999-10-12
2001-08-07
Barefoot, Galen L. (Department: 3644)
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
C244S215000, C244S075100, C244S131000
Reexamination Certificate
active
06270039
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to a hinge for movable control surfaces in an aircraft.
The invention further relates to a connecting piece intended to convey the force needed for moving a control surface of an aircraft from an actuator to a hinge.
2. Description of the Prior Art
In aircrafts, such as aeroplanes, various movable control surfaces are used for piloting the aircrafts and for controlling different flight operations, such as take-offs and landings. Examples of such movable control surfaces are ailerons, elevators rudders and different airbrakes and flaps. In addition, aeroplanes use spoilers arranged on the upper surface of the wings, which remove the lift caused by the wings when the aeroplane is descending or landing. Spoilers can also be used during the flight to maneuver the aircraft
FIG. 1
illustrates such a spoiler.
FIG. 2
further shows a hinge us with the spoiler. In relation to the hinge the spoiler can be moved upwards and downwards with a hydraulic cylinder in relation to the wing. Since high reliability and fall safe solutions are required in aircrafts, there are generally at least six hinge lugs for each control surface. Typically the two middlemost hinge lugs form an entity which is referred to as a middle hinge. The middle hinge further comprises connecting elements used to arrange the hydraulic cylinder or an equivalent actuator to move the control surface with the hinge. The force, up to 50 t, moving the control surface provided by the actuator is thus conveyed using the middle hinge to the control surface. The problem with prior art solutions is the heavy weight used by the massive structure of the middle hinge. Furthermore, in order for the middle hinge to be supported on the control surface, the control surface has to be made firm, and heavy at the same time. However, lightness together with reliability is one of the most important criteria in aircraft constructions.
SUMMARY OF THE INVENTION
It is an object of the present invention to provide a, hinge arrangement of aircraft control surfaces that avoids prior art problems.
A hinge according to the invention is characterized in that the hinge comprises two hinge lugs arranged on the control surface at a predetermined distance from each other by means of joint surfaces in the hinge lugs, the hinge lugs comprising fastening lugs which can be connected to the aircraft with hinge pins or the likes the hinge lugs comprising connecting lugs between which an elongated connecting piece is arranged, the ends of the connecting piece including journals from where the connecting piece is pivoted to the connecting lugs rotatably about its longitudinal axis, and a middle portion between the journals of the connecting piece being flat so that the middle portion is thicker in the direction of the force conveyed from the actuator than in the transversal direction of the force, and the connecting piece comprising means for connecting the actuator, whereby the actuator can be used for turning the control surface in relation to said hinge pins, and wherein the connecting piece is arranged to simultaneously revolve about its longitudinal axis when turning the control surface.
A connecting piece of the invention is further characterized in that the connecting piece is an elongated element comprising journals at both ends, from where it can be rotatably pivoted about is longitudinal axis between the connecting lugs on the control surface hinge, and a middle portion between the journals of the connecting piece being plate-like and tapering towards the journals, and the middle portion of the connecting piece comprising means for connecting the actuator to the connecting piece.
An essential idea of the invention is that a hinge to be attached to a movable control surface comprises two hinge lugs arranged at a predetermined distance from each other. The hinge lugs include fastening lugs from where they are hinged with hinge pins or the like to the lugs arranged to an aircraft. Furthermore, both hinge lugs comprise a connecting lug, whereby an elongated connecting piece is rotatably pivoted about its longitudinal axis between said lugs, the ends of the connecting piece including pivoting journals. The force using the control surface is conveyed from the actuator to the hinge with a connecting piece. The connecting piece is able to revolve about its lontgitudinal aids, when the control surface is moved. An essential idea of a preferred embodiment of the invention is that the hinge comprises two separate hinge lugs arranged at a predetermined distance from one another. Me hinge lugs comprise fastening lugs, from where they are both separately hinged to the lugs stationarily arranged to the aircraft using hinge pins. Both hinge lugs also comprise a connecting lug, whereby a connecting piece is rotatably pivoted about its longitudinal axis between said lugs. A further essential idea of a second preferred embodiment of the invention is that there is an elliptic flat middle portion between the journals of the connecting piece. The middle point of the connecting piece may comprise a transverse connecting hole, to which a fastening element provided with a branch-like end connected to the actuator can be attached with a mate pin. The flat middle portion of the connecting piece, can then be fitted between the branches of the fastening element. As the connecting piece may revolve when the control surface is moved, the connecting piece always remains in the predetermined position in relation to the direction of the force provided by the actuator and thus the bend is directed towards the connecting piece only in the direction of movement of the power unit. The connecting piece is particularly designed to receive the bend in said direction. A further essential idea of a third preferred embodiment of the invention is that the fastening lug and the connecting lug are substantially arranged in the same fine in the direction of the force provided by the actuator. The fastening lug and the connecting lug are preferably in the same lug and form an integral structure. Another essential idea of a; fourth preferred embodiment of the invention is that ball joints or corresponding bearings that allow an angle position change between the connecting piece and the connecting lug are arranged at both ends of the connecting piece, whereby the possible bend of the connecting piece does not cause torque to the connecting lug.
An advantage of the invention is that the forces are divided into a larger surface area, as the hinge lugs are arranged further apart from one another. Local loads at the fastening points of the hinge remain lighter and a higher reliability is achieved, On the other hand, reduced loading, allows to reduce the weight of the structures. Thinner surface plates may thus be employed on the control surfaces. Furthermore, the actual hinge is on account of its construction lighter than the massive integrated prior art hinges. According to surveys conducted the new hinge easily provides a 30% reduction in weight compared to the prior art construction. A similar reduction in weight is hard to achieve merely by providing a lighter control surface structure. This is difficult because attempts have already been made to optimize the relation between the stiffness and the weight of the control surfaces in current structures by using, for example, light cell structures and reinforcements, such as carbon fibre. Although the new hinge structure is significantly lighter than the previous ones, It is still at least as steady and reliable as prior art structures. In addition, the maintenance is made easier since separate hinge lugs can be detached irrespective of each other.
When the connecting piece is journalled between the connecting, lugs using ball joints or corresponding bearing elements, no torsional/bending load from the possible bend of the connecting piece is conveyed to the hinge lugs nor to the joint surface between the hinge lug and the movable control surface. Compared to prior art solutions a
Barefoot Galen L.
Ladas & Parry
Patria Finavicomp Oy
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