Patent ID: 6122985
Filing Date: 2000-09-26
Classification: B64D,F16H,Y10T

Abstract:
A torque-dividing transmission (20), for aircraft, comprising a single input pinion (21) and a single output gear (26), both rotatable about respective fixed axes (14); a plurality of gear assemblies (30) interposed between the input pinion (21) and the output gear (26) for transferring a respective portion of input torque from the input pinion (21) to the output gear (26); and torque-dividing means (44) for dividing the input torque equally between said plurality of gear assemblies (30); said torque-dividing means (44) comprising for each said gear assembly (30), a first gear (44) having an axis of rotation (32) parallel to a main axis of rotation (14) of said input pinion, the first gears of the plurality of gear assemblies being arranged around said main axis (14) and connected in driving relation to said output gear, said first gear including a number of radial spokes (52) each comprising an elastically bendable element having a flexural rigidity in a circumferential direction with respect to said axis of rotation (32), which is less than the flexural rigidity in a direction parallel to said axis of rotation (32).