Two-mode tuned vibration absorber
A dual-frequency vibration-reduction apparatus includes a beam having a longitudinal axis and a transverse axis perpendicular to the longitudinal axis. An attachment mechanism mechanically couples a portion of the beam to a structure. One or more masses are attached to the beam such that the apparatus vibrates bi-modally at a primary frequency and a secondary frequency for reducing vibrations of the structure at the primary frequency and the secondary frequency. A first mode may be a bending mode of the apparatus, while a second mode is a torsion mode. The vibration reduction apparatus may be tuned such that the primary frequency substantially matches a blade-pass frequency of a propeller-driven aircraft and the secondary frequency substantially matches a harmonic of the blade-pass frequency. The vibration reduction apparatus includes a mounting mechanism for mounting to any structure requiring low-frequency vibration attenuation.
1. A dual-frequency vibration-reduction apparatus, comprising:
a beam having a longitudinal axis and a transverse axis perpendicular to the longitudinal axis;
an attachment mechanism for mechanically coupling a portion of the beam to a structure; and
one or more masses attached to the beam such that the dual-frequency vibration-reduction apparatus vibrates bi-modally at a first frequency and a second frequency for reducing vibrations of the structure at the first frequency and the second frequency,
wherein the one or more masses each are adjustably coupled to the beam for adjusting a position along the longitudinal axis and the transverse axis, thereby enabling the dual-frequency vibration-reduction apparatus to be tuned for attenuating a variety of frequency vibrations.
2. The dual-frequency vibration-reduction apparatus of claim 1 , wherein the one or more masses have an uneven mass distribution with respect to the transverse axis.
3. The dual-frequency vibration-reduction apparatus of claim 1 , wherein the first frequency is substantially matched with a blade-pass frequency of a propeller-driven aircraft and the second frequency is substantially matched with a harmonic of the blade-pass frequency.
4. The dual-frequency vibration-reduction apparatus of claim 1 , wherein the structure is one of a frame, a stringer, a skin portion, an engine beam mount, a rudder pedal, or a heads-up display assembly.
5. A paired dual-frequency vibration reducer, comprising two of the dual-frequency vibration-reduction apparatuses of claim 1 , wherein a first dual-frequency vibration-reduction apparatus is mounted opposite the structure from a second dual-frequency vibration-reduction apparatus, such that torsion loads from the first vibration-reduction apparatus are substantially canceled by the second vibration-reduction apparatus to avoid imposing torsion loads onto the structure.
6. A tuned vibration absorber for attenuating a primary frequency vibration of a structure and a secondary frequency vibration of the structure, comprising:
a beam having an attachment bracket for attaching the beam to the structure;
a first mass adjacent a first end portion of the beam;
a second mass adjacent a second end portion of the beam, the second end portion being opposite the first end portion along a longitudinal axis of the beam, wherein the first mass and the second mass are adapted to provide a bending mode of the beam for attenuating the primary frequency vibration of the structure;
the first mass having an uneven mass distribution along a transverse axis of the beam, the transverse axis being perpendicular to the longitudinal axis; and
the second mass also having an uneven mass distribution along the transverse axis, wherein the uneven mass distributions of the first mass and the second mass are adapted to excite a torsional mode of the beam, based on the bending mode, the torsional mode being adapted for attenuating the secondary frequency vibration of the structure.
7. The tuned vibration absorber of claim 6 , wherein the primary frequency is substantially matched with a blade-pass frequency of a propeller-driven aircraft and the secondary frequency is substantially matched with a harmonic of the blade-pass frequency.
8. The tuned vibration absorber of claim 6 , wherein the structure is one of a frame, a stringer, a skin portion, an engine beam mount, a rudder pedal, or a heads-up display assembly.
9. The tuned vibration absorber of claim 6 , wherein the first mass and the second mass are each adjustably coupled to the beam for adjusting their position along the longitudinal axis and the transverse axis, thereby enabling the tuned vibration absorber to be tuned for attenuating a variety of frequency vibrations.
10. The tuned vibration absorber of claim 9 , wherein the first mass and the second mass are each adjusted closer to the middle of the beam to provide a higher frequency bending mode of the beam, and the first mass and the second mass are each adjusted further from the middle of the beam to provide a lower frequency bending mode of the beam.
11. The tuned vibration absorber of claim 6 , wherein the uneven mass distribution of the first mass is unevenly distributed in an opposite orientation with respect to the transverse axis compared to the uneven mass distribution of the second mass.
12. The tuned vibration absorber of claim 6 , the first mass comprising a subset of smaller masses that are unevenly distributed along the transverse axis thereby providing the uneven mass distribution of the first mass.
13. The tuned vibration absorber of claim 6 , wherein the first mass comprises a small portion and a large portion separated by a gap along the transverse axis, the width of the gap being increased by adjusting positions of the small portion and the large portion thereby increasing the moment of inertia.
14. The tuned vibration absorber of claim 13 , wherein the small portion and the large portion are moved closer together along the transverse axis to provide a higher frequency torsional mode of the beam, and the small portion and the large portion are moved further apart along the transverse axis to provide a lower frequency torsional mode of the beam.
15. A dual-frequency vibration-reduction apparatus, comprising:
a beam having a longitudinal axis and a transverse axis perpendicular to the longitudinal axis;
an attachment mechanism for mechanically coupling a portion of the beam to a structure; and
one or more masses attached to the beam such that the dual-frequency vibration-reduction apparatus vibrates bi-modally at a first frequency and a second frequency for reducing vibrations of the structure at the first frequency and the second frequency,
wherein the one or more masses are each adjustable for enabling the dual-frequency vibration-reduction apparatus to be tuned for attenuating a variety of frequency vibrations,
wherein an amount of mass from each mass of the one or more masses is unevenly distributed about the beam on one or more of the longitudinal axis and the transverse axis,
wherein an uneven distribution of the one or more masses is adapted to excite a torsional mode vibration of the beam.
16. The dual-frequency vibration-reduction apparatus of claim 15 , wherein the one or more masses are adjustable by replacement with at least one or more masses of a varied weight.
17. The dual-frequency vibration-reduction apparatus of claim 15 , wherein a position of the one or more masses is adjustable along the longitudinal axis and the transverse axis.
18. The dual-frequency vibration-reduction apparatus of claim 15 , wherein the first frequency is substantially matched with a blade-pass frequency of a propeller-driven aircraft and the second frequency is substantially matched with a harmonic of the blade-pass frequency.