Aeronautics and astronautics – Landing gear – Retractable
Reexamination Certificate
2000-02-28
2001-08-28
Eldred, J. Woodrow (Department: 3644)
Aeronautics and astronautics
Landing gear
Retractable
C244S1020SS
Reexamination Certificate
active
06279853
ABSTRACT:
BACKGROUND TO THE INVENTION
The invention relates to an aircraft undercarriage mechanism. The invention is to be applied primarily to an aircraft wing landing gear door which must remain safely closed when the landing gear wheels are retained in a wheel bay during flight.
Typically, an undercarriage door is held closed by a locking mechanism comprising a catch and a member engageable with the catch, one of which member and catch is arranged on the undercarriage door and the other of which is arranged on part of the wing. Aircraft wings deflect during flight as various forces acting on the wings vary in magnitude. Such deflection can cause relative movement to occur between the door and the wing which, in turn, transmits force to the locking mechanism which can be a problem and an object of the invention is to provide a door locking mechanism which minimises that problem.
SUMMARY OF THE INVENTION
According to an aspect of the present invention there is provided an aircraft undercarriage mechanism comprising a first lock member mounted on the undercarriage, the first lock member being engageable with a second lock member mounted on a support part of the aircraft, one of said lock members including means which permits relative movement between the lock members when the undercarriage is retracted with the lock members interengaged to minimise transmission of forces created by wing deflection from one lock member to the other.
The said means may permit relative movement in more than one direction. Where wing deflection is, say, of a combined bending and torsional kind, the movement of the interengaged lock member will preferably accommodate both kinds of deflection.
Preferably, the said means comprises an element movably mounted on the one lock member. In such a case, the element may be slidable and/or rotatable on the one lock member. In that way, the other lock member may remain interengaged with the element while the one lock member having the element thereon is able to move relative to the element. The element may conveniently take the form of a roller.
Preferably, alignment means is provided for receiving and positioning the element relative to the other lock member during closing of the door. That is allows the element to be moved into an optimum position before the lock members interengage. In such a case, the alignment means may have a cam surface which is arranged to position the element. The alignment means may limit the frictional loads which would, in its absence, be transmitted to the other lock member. The alignment means may comprise a fork which receives and positions the element. The alignment means is preferably arranged to hold the element in its aligned position. The element may be received in a recess defined by part of the alignment means.
In a preferred embodiment, the one lock member is in the form of an arm which may be pivotally connected to its mounting at one of its ends. Where a said element is provided, the element may be slidably mounted on an opposite end of the arm. The first lock member may be mounted on a door or leg of the undercarriage.
Preferably, said one lock member is mounted on the undercarriage.
According to a second aspect of the invention there is provided an aircraft undercarriage including a mechanism according to the first said aspect of the invention or any of the consistory clauses relating thereto.
According to another aspect of the invention there is provided an aircraft having an undercarriage mechanism according to the first said aspect of the invention or any of the consistory clauses relating thereto.
REFERENCES:
patent: 2567114 (1951-09-01), Linn
patent: 2661171 (1953-12-01), Allen
patent: 2720369 (1955-10-01), Detzer
patent: 4568045 (1986-02-01), Mayer
patent: 5022609 (1991-06-01), Cranston
patent: 5040747 (1991-08-01), Kane et al.
patent: 5100083 (1992-03-01), Large et al.
patent: 5263664 (1993-11-01), Derrien et al.
patent: 5269481 (1993-12-01), Derrien
patent: 0 265 197 (1988-04-01), None
patent: 2 161 202 (1986-01-01), None
BAE Systems plc
Eldred J. Woodrow
Nixon & Vanderhye P.C.
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