Aircraft comprising a landing gear with controlled detachment in the event of an accident
AssigneeAerospatiale Airbus
InventorsFrancis Dazet, André Maurin
Life of this patent
Estimating the term…
Abstract
On an aircraft, particularly of the commercial type, a landing gear (16) placed in front of a fuel tank (18) comprises a rod system (32) capable of coming into contact with a sliding rail (52) formed on a reinforced structural part (48) of the aircraft, in the event of accidental tilting of the gear to the rear. The deformation resulting from the rod system (32) then successively induces the complete slackening of the damper (24) of the gear, the rupture of its slack limit stop (25), followed by the rupture of a part of the rod system (32). The lower part of the gear (16) is then ejected and guided by a rear part (52b) of the sliding rail (52), with no risk of perforation of the tank (18).
Claims9
Aircraft, comprising a structure and at least one landing gear fitted under the structure, the landing gear comprising a frame, a bogie, a damper equipped with a slack limit stop and a rod system placed behind the damper, the damper and the rod system connecting the bogie to the frame separately, wherein the structure comprises a sliding rail with which the rod system can come into contact, in the event of accidental tilting of the landing gear to the rear, to induce successively a complete slackening of the damper, a rupture of the slack limit stop and a rupture of the rod system.
Dependencies are inferred from the claim text.