Patent ID: 6196066
Filing Date: 2001-03-06
Classification: B64C,F16F

Abstract:
A rotor aircraft rotor blade fitted with a static and dynamic balancing device in an external end portion, towards a blade tip, of an aerodynamic profiled main blade section, of the blade, said balancing device including static balancing weights and static and dynamic balancing weights which are housed in at least two cavities delimited, on either side a chord centring axis of the blade, in said external end portion of the blade main blade section, and accessible from outside the blade through one access opening which opens in a surface of the blade and able to be closed by one access door on said surface of the blade, wherein said cavities of the balancing device are arranged in two elongated housings substantially in the direction of the span of the blade and substantially symmetrical to each other on either side said chord centring axis, the device including a single access opening which opens in one of the extrados and intrados surfaces of the blade, and in communication with an internal end, towards a blade root, of each of the two elongated housings, so as to enable the introduction and withdrawal of each weight into and from each housing, a first set of weights, for the static balancing, the first set of weights to be equally distributed by mass in the two housings, and a second set of weights for the static and dynamic balancing, the second set of weights to be distributed by mass in the two housings so as to ensure a dynamic adjustment of the blade.