Blade-mounted centrifugal pendulum

Claim 2

Apparatus for reducing vibrations at the hub of a helicopter rotor assembly which has a plurality of blades, each affixed to a blade grip that is secured to the hub which is mounted on a rotatable mast, the combination comprising: (a) a pair of pivot means, one extending through each said grip diametrically opposed and equidistant from the axis of said mast and substantially perpendicular to the chord axis of the blade adjacent said pivot means, and (b) masses mounted in the form of simple pendulums, two on each said pivot means and symmetrical to the feathering axis of the adjacent blade.

Claim 3

Apparatus according to claim 1 further including means for tuning the response of said pendulums.

Claim 4

Apparatus according to claim 2 wherein said means for tuning comprises a weight positionable at selected distances from said pivot means.

Claim 5

Apparatus according to claim 2 wherein said means for tuning comprises a plurality of incremental weights attachable to said pendulums in selected numbers.

Claim 6

Vibration reduction apparatus for a helicopter lift assembly which includes a plurality of rotor blades each secured to a blade grip, said grips connected to a hub that is mounted on a mast, comprising in combination: (a) a rotatable shaft disposed within each of said grips, said shafts essentially parallel to the axis of said mast, (b) A support rigidly connected to each of said shafts with said supports being free to move in a plane essentially parallel to the plane of said rotor blades, and (c) a mass joined to each of said supports to form a pendulum pivotable about said shaft.

Claim 7

Vibration reduction apparatus for a helicopter lift assembly which includes a plurality of rotor blades each secured to a blade grip, said grips connected to a hub that is mounted on a mast, comprising in combination: (a) a rotatable shaft disposed within each of said grips, said shafts essentially parallel to the axis of said mast, (b) A support rigidly connected to each of said shafts with said supports being free to move in a plane essentially parallel to the plane of said rotor blades, and (c) a mass joined to each of said supports to form a pendulum pivotable about said shaft.

Claim 8

Vibration reduction apparatus according to claim 5 further including means for positioning the center of gravity of said pendulum at predetermined distances from said shaft to select the response of said pendulum.

Claim 9

Vibration reduction apparatus according to claim 6 wherein said means for positioning comprises a threaded shaft joined to said support, said mass positionable on said threaded shaft by a nut engaged thereto.

Claim 10

Vibration reduction apparatus according to claim 6 wherein said means for positioning comprises a plurality of incremental weights attachable to said pendulum in selected numbers.

Claim 11

Apparatus for reducing vibration at the hub of a helicopter rotor system which includes a plurality of blades, the combination comprising: (a) a blade grip for securing each blade to said hub, said grip having upper and lower projecting lugs with a hole formed in each said lug, said holes being colinear, (b) a shaft adapted to fit between said lugs, the ends of said shaft disposed in said holes, (c) bearing means disposed about said shaft within each of said holes to support said shaft while allowing said shaft to rotate, (d) a cap member joined to each lug of said grip, covering said hole in said lug and maintaining said shafts axially within said grip, (e) a first arm rigidly joined to said shaft adjacent a first of said lugs of said grip, said first arm movable essentially parallel to the plane of said blades, (f) a second arm rigidly joined to said shaft adjacent a second of said lugs of said grip, said second arm movable essentially parallel to the plane of said blades, (g) a first mass rigidly coupled to said first arm, and a second mass rigidly coupled to said second arm, said masses of a magnitude to damp inplane vibrations generated by said blades.

Claim 12

Apparatus for reducing vibration at the hub of a helicopter rotor system which includes a plurality of blades, the combination comprising: (a) a blade grip for securing each blade to said hub, said grip having upper and lower projecting lugs with a hole formed in each said lug, said holes being colinear, (b) a shaft adapted to fit between said lugs, the ends of said shaft disposed in said holes, (c) bearing means disposed about said shaft within each of said holes to support said shaft while allowing said shaft to rotate, (d) a cap member joined to each lug of said grip, covering said hole in said lug and maintaining said shafts axially within said grip, (e) a first arm rigidly joined to said shaft adjacent a first of said lugs of said grip, said first arm movable essentially parallel to the plane of said blades, (f) a second arm rigidly joined to said shaft adjacent a second of said lugs of said grip, said second arm movable essentially parallel to the plane of said blades, (g) a first mass rigidly coupled to said first arm, and a second mass rigidly coupled to said second arm, said masses of a magnitude to damp inplane vibrations generated by said blades.

Claim 13

The combination according to claim 9 wherein each of said masses comprises, (a) a plate having a hole therein, (b) a bolt threadedly connected to said first plate, and (c) weight members secured to said plate by means of said bolt.