Pitch-oscillation limitation system applied to an aircraft
AssigneeAirbus France
InventorsOlivier Regis, Gregory Sicault, Emmanuel Kopp
Life of this patent
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Abstract
A pitch-oscillation limitation system, applied to an aircraft having main landing gear located toward the center of the aircraft and forward landing gear located under the nose of the aircraft, wherein the system includes means for automatically applying, in the event of sudden braking, time-deferred braking between the wheels of the landing gear under the wings and the wheels of the landing gear under the fuselage, so as to reduce the amplitude of the aircraft's pitching motion.
Claims9
An aircraft pitch-oscillation limitation system, applied to an aircraft having wing main landing gears located under a wing of the aircraft, having at least one fuselage main landing gear located under a fuselage of the aircraft and having a forward landing gear located under a nose of the aircraft, wherein the aircraft pitch-oscillation limitation system includes means for automatically applying, in the event of a sudden braking, a time-deferred braking, the delay time of which is comprised between 0.5 second and 1.1 seconds, between wheels of the wing main landing gears and wheels of the at least one fuselage main landing gear, to reduce an amplitude of an oscillation in pitch of the aircraft when the sudden braking occurs.
Dependencies are inferred from the claim text.