Shock sensor and devices to which the latter is applied

• US 5,349,863 A
• Filed: 02/27/1992
• Issued: 09/27/1994
• Est. Priority Date: 06/28/1989
• Status: Expired due to Fees

• Current Assignee: Aerospatiale Societe Nationale Industrielle
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Riviere Daniel, Dumont, Jean-Pierre
• Primary Examiner(s): Williams, Hezron E.
• Assistant Examiner(s): MILLER, ROSE MARY
• Application Number:
  US07/781,142
• Time in Patent Office: 943 Days
• Field of Search: 73/651, 73/517 A, 73/35 P, 73/650, 73/654, 73/510, 73/105
• US Class Current: 73/651
• CPC Class Codes: G01N 2291/02827 Elastic parameters, strength or force
• CPC Class Codes: G01P 15/09 by piezoelectric pick-up

Abstract

Shock or impact sensor which can be fixed to a structure (14) comprising, along a longitudinal axis (AL) perpendicular to the structure (14), a rod (12) which can be joined to the structure (14) by a first end (16), a weight or counterweight (24) joined to a second end of the rod (12) and acceleration detection fixed to weight or counterweight (24) to detect acceleration along an axis perpendicular to the longitudinal axis of the sensor.

Claims

1. A shock sensor for attachment to a structure and having a fundamental resonant frequency, said sensor comprising:

a rod having a first end, a second end and a longitudinal axis, said first end being attachable to said structure;

a weight attached to said second end;

acceleration detection means attached to said weight for detecting vibrations along an axis perpendicular to said longitudinal axis; and

means to remove a plurality of harmonics of said fundamental resonant frequency from said vibrations.

2. A sensor according to claim 1, wherein said means to remove a plurality of harmonics includes a groove in said rod near said first end.

3. A sensor according to claim 1, wherein said means to remove a plurality of harmonics includes a low-pass filter.

4. A sensor according to claim 3, wherein said low pass filter comprises a sampler operating at a frequency of four times the fundamental resonant frequency.

5. A sensor according to claim 1, wherein said means to remove a plurality of harmonics includes a groove in said rod near said first end and a sampler operating at a frequency of four times the fundamental resonant frequency.

6. A sensor according to claim 1, wherein said fundamental resonant frequency is no more than 1 Khz.

7. A sensor according to claim 1, wherein said acceleration detection means includes two piezoelectric acceleration detectors located on the weight, each piezoelectric acceleration detector having a sensing direction, each of said directions being perpendicular to each other and said longitudinal axis.

8. A sensor according to claim 1, wherein said weight and vibration detection means in combination have a center of gravity located on said longitudinal axis.

9. A sensor according to claim 1, wherein the rod and the weight are cylindrical.

10. A sensor according to claim 1, wherein the weight has a recess and the vibration detection means is attached to the weight in said recess.

11. A gyrometer for measuring a rotation, comprising:

a support;

a first and a second sensor, each sensor having a fundamental resonant frequency and including;

a rod having a first end, a second end and a longitudinal axis, said first end being attached to said support and said rod having a groove near said first end;

a weight attached to said second end; and

acceleration detection means attached to said weight for detecting vibrations along an axis perpendicular to said longitudinal axis;

said first and second sensor first ends being spaced apart; and

means for measuring a velocity for each sensor first end and combining said velocities to provide a measure of said rotation.