Method for matching vibration mode frequencies on a vibrating structure

• US 5,739,410 A
• Filed: 12/11/1996
• Issued: 04/14/1998
• Est. Priority Date: 08/24/1994
• Status: Expired due to Term

• Current Assignee: Atlantic Inertial Systems Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: British Aerospace, Inc.
• Inventors: Fell, Christopher P.
• Primary Examiner(s): RAEVIS, ROBERT R
• Application Number:
  US08/763,348
• Time in Patent Office: 489 Days
• Field of Search: 73/1 E
• US Class Current: 73/1.77
• CPC Class Codes: G01C 19/5691 of essentially three-dimensional vibrators, e.g. wine glass-type vibrators

Abstract

Vibration mode frequencies of a vibrating structure gyroscope sensing element are matched by removing and/or adding a desired variable amount of material from or to the sensing element (1) at at least one point (4) on or in the vicinity of the neutral axis (5).

Claims

1. A method for matching vibration mode frequencies on a vibrating structure for a vibrating structure gyroscope, in which the vibrating structure is a substantially cylindrical or substantially ring-like sensing element, and in which a desired variable amount of material is removed from and/or added to the sensing element at at least one point on or in the vicinity of the neutral axis of the cross section of the element, to displace and match the vibration mode frequencies around the element, and wherein said desired variable amount of material is removed from and/or added to the sensing element in the absence of a change in width of the element.

2. A method according to claim 1, in which material is removed from and/or added to the element only near points of maximum radial movement of the mode.

3. A method according to claim 1 or claim 2, in which the element is made of metal or silicon.

4. A method according to claim 1, in which the material is removed from the element by laser beam ablation.

5. A method according to claim 1, in which the material is added to the element by adhesive.

6. A method according to claim 1, applied to a substantially planar sensing element.

7. A vibrating structure sensing element for a vibrating structure gyroscope having material added thereto and/or removed therefrom according to the method of claim 1 to match vibration mode frequencies of the element.