Month in the Patent Office

Abstract

An aircraft landing gear bracing strut comprises two arms, pivoted to the aircraft and the landing gear, respectively, and also pivoted together about an axis lying outside the plane containing the pivotal axes of the two arms to the aircraft and landing gear when the latter is extended, wherein one of the arms constitutes the body of a fluid operated jack, of which the piston rod is coupled to the other arm through a connecting link. In FIG. 1, the wheel strut 1 is pivoted to an aircraft wing at C, and braced by a strut 3 breakable at D and pivoted to the wing at A and to the strut 1 at B. In FIG. 2, the strut 3 comprises two arms 4, 5 hinged on a pin 6. The arm 4 forms a cylinder in which works a piston 12, the rod 13 of which is universally jointed to a coupling rod 15 pivoted to the arm 5 at 16. The universal joint runs on a roller 17 in a guide 18 formed in the arm 4. Admission of fluid under pressure to port 21 and connexion of port 22 exhaust breaks and folds the strut, retracting the undercarriage, and vice versa. An abutment 19 on arm 5 abuts a strengthened portion 20 on arm 4 when the strut is extended. The cylinder is formed with members 23, and the piston with a sliding portion 24 as in Specification 527,225 to form a down‐lock. When the strut is fully opened, the piston actuates a member 26 to give an indication to the pilot. Specification 551,673 also is referred to.

Citation

(1959), "Month in the Patent Office", Aircraft Engineering and Aerospace Technology, Vol. 31 No. 8, pp. 259-259. https://doi.org/10.1108/eb033151