Fuselage mounted landing gear
AssigneeThe Boeing Company
InventorsJames Jason Salmon, Sergey D. Barmichev, Michael Allan Long
Life of this patent
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Abstract
A landing gear for an aircraft. The landing gear may have a wheel/truck assembly, an oleo strut/support frame for supporting the wheel/truck assembly, and a retraction assembly attached to the oleo strut/support frame, the retraction assembly for moving the landing gear between a deployed position and a retracted position. The retraction assembly may have a pivoting trunnion brace attached to the oleo strut/support frame and to a fuselage of the aircraft for positioning the wheel/truck assembly, the oleo strut/support frame and the retraction assembly at least substantially fully within the fuselage of the aircraft in the retracted position.
Claims16
A landing gear for an aircraft, comprising:
- a plurality of wheels connected to a number of axles forming a wheel/truck assembly;
- an oleo strut configured to attach the wheel/truck assembly to a retraction assembly;
- and
- the retraction assembly configured to move the landing gear between a deployed position and a retracted position, the retraction assembly including a pivoting trunnion brace having a first end and a second end, wherein the first end is attached to the oleo strut and the second end is attached to a fuselage of the aircraft, and wherein the trunnion brace is configured to position the wheel/truck assembly, the oleo strut, and the retraction assembly fully within the fuselage of the aircraft when in the retracted position.
A landing gear for an aircraft, comprising:
- a plurality of wheels connected to a number of axles forming a wheel/truck assembly;
- an oleo strut configured to attach the wheel/truck assembly to a retraction assembly;
- and
- the retraction assembly configured to move the landing gear between a deployed position outwardly of a fuselage of the aircraft, and a retracted position, the retraction assembly including a pivoting trunnion brace having a first end and a second end, wherein the first end is attached to the oleo strut and the second end is attached to the fuselage, and wherein the trunnion brace is configured to position the wheel/truck assembly, the oleo strut, and the retraction assembly fully within the fuselage when in the retracted position.
Dependencies are inferred from the claim text.