Abstract: A braking system for the landing gear of an aircraft, which landing gear includes a bogey containing at least four wheels, each equipped with a brake, with the bogey having at least two axles that are connected to the aircraft by a telescoping strut, wherein when the aircraft makes a low-speed turn around a center of rotation, the straight line linking the center of rotation of the turn to the barycenter of the landing gear does not pass between the front wheels and the rear wheels of the landing gear which system further includes means for applying differential braking between the front wheels and the rear wheels of the landing gear.

Abstract: A braking-energy equalization system applied to an aircraft undercarriage, which undercarriage includes at least two sets of landing gear, with each set of landing gear including at least two wheels and with each of wheels being equipped with a brake, wherein the system includes means intended to introduce a delay time to delay the braking of the brakes having a higher braking torque in comparison with the other brakes having a lower braking torque, so as to equalize the braking energies absorbed by the brakes of the landing gear during the landing or during an interrupted takeoff of the aircraft.

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.

Abstract: A mobile test rig for tires, composed of a self-driven platform capable of following rectilinear and circular trajectories and including: a test instrument module for a wheel-tire assembly to be tested that permits the assembly to be orientated in all directions, to lean the assembly and apply a vertical effort to the assembly, first swivelling axles, equipped with suspensions and driving wheels, a processing unit associated to a memory, and a control of the test cycle permitting orientation of the assembly to be controlled, as well as a load applied to the assembly.

Abstract: A braking system for the landing gear of an aircraft, which landing gear includes a bogey containing at least four wheels, each equipped with a brake, with the bogey having at least two axles that are connected to the aircraft by a telescoping strut, wherein when the aircraft makes a low-speed turn around a center of rotation, the straight line linking the center of rotation of the turn to the barycenter of the landing gear does not pass between the front wheels and the rear wheels of the landing gear which system further includes means for applying differential braking between the front wheels and the rear wheels of the landing gear.

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.

Abstract: A braking-energy equalization system applied to an aircraft undercarriage, which undercarriage includes at least two sets of landing gear, with each set of landing gear including at least two wheels and with each of wheels being equipped with a brake, wherein the system includes means intended to introduce a delay time to delay the braking of the brakes having a higher braking torque in comparison with the other brakes having a lower braking torque, so as to equalize the braking energies absorbed by the brakes of the landing gear during the landing or during an interrupted takeoff of the aircraft.

Abstract: A mobile test rig for tires, composed of a self-driven platform capable of following rectilinear and circular trajectories and including: a test instrument module for a wheel-tire assembly to be tested that permits the assembly to be orientated in all directions, to lean the assembly and apply a vertical effort to the assembly, first swivelling axles, equipped with suspensions and driving wheels, a processing unit associated to a memory, and a control of the test cycle permitting orientation of the assembly to be controlled, as well as a load applied to the assembly.

Abstract: The invention relates to a method for detecting that the design loads of an aircraft have been exceeded during landing.According to the invention:--in a preliminary step:the load criteria (C1, C2, . . . , Cp) are defined; andthe laws of variation of the allowable values (C1ad, C2ad, . . . , Cpad) of these load criteria (C1, C2, . . . , Cp) are determined, as a function of input parameters (P1, P2, . . . , Pn); and--at the moment of landing:the values of the said input parameters (P1, P2, . . . , Pn) and of the said load criteria (C1, C2, . . . , Cp) are measured;the allowable values (C1ad, C2ad, . . . , Cpad) of the said load criteria (C1, C2, . . . , Cp) are calculated;for each of the said load criteria (C1, C2, . . . , Cp), the measured effective value (C1m, C2m, . . . , Cpm) is compared with the calculated allowable value (C1ad, C2ad, . . . , Cpad); andit is determined whether a structural inspection must be carried out.