Pitch-oscillation limitation system applied to an aircraft
View Patent ↗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.
1. 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.
2. An aircraft pitch-oscillation limitation system according to claim 1 wherein the means for applying the time-deferred braking includes a brake-delay calculator that calculates the delay time to be applied using data issued by an inertial reference system.
3. An aircraft pitch-oscillation limitation system according to claim 1 , wherein the time-deferred braking consists of braking the wheels of the wing main landing gears after the wheels of the at least one fuselage main landing gear.
4. An aircraft pitch-oscillation limitation system according to claim 3 wherein the delay time is 0.8 second.
5. An aircraft pitch-oscillation limitation system according to claim 1 , wherein the the time-deferred braking consists of braking the wheels of the wing main landing gears before the wheels of the at least one fuselage main landing gear.
6. An aircraft pitch-oscillation limitation system according to claim 5 , wherein the delay time is 0.8 second.
7. An aircraft including a system for the limitation of pitch oscillation during braking, according to claim 1 .
8. An aircraft according to claim 7 , wherein the aircraft includes brake controls that are located in the cockpit and that are connected to a brake system that includes a braking calculator and hydraulic brake lines equipped with solenoid valves controlled by the calculator.
9. An aircraft according to claim 8 , wherein a brake-delay calculator is incorporated into the braking calculator.