DETAILED ACTION
Drawings
Figure 5 should be designated by a legend such as --Prior Art-- because only that which is old is illustrated. See MPEP § 608.02(g).
Corrected drawings in compliance with 37 CFR 1.121(d) are required in reply to the Office action to avoid abandonment of the application. The replacement sheet(s) should be labeled “Replacement Sheet” in the page header (as per 37 CFR 1.84(c)) so as not to obstruct any portion of the drawing figures. If the changes are not accepted by the examiner, the applicant will be notified and informed of any required corrective action in the next Office action. The objection to the drawings will not be held in abeyance.
Abstract
The abstract of the disclosure is objected to because it is unclear due to apparent administrative errors. Going forward with examination, the abstract is interpreted to be (Note that in applicant’s response, where a change is requested in the abstract, a separate page of the abstract containing the change will be needed):
--The present invention relates to a gyroscopic measurement method by means of a sensor (10) comprising a housing (12) and a vibrating element (15) able to vibrate relative to the housing (12) simultaneously according to a direction (x) of a pilot mode and a direction (y) of a detection mode, comprising s of the vibrating element (15) according to the directions of the pilot mode and detection mode respectively to a predetermined pilot amplitude (xmax) and detection amplitude (ymax), and mes) of the housing (12).
A predetermined bias (ξ(t)) is introduced into a measurement of an angular position (θ) of the direction (x) of the pilot mode used to determine a biased force (Fass,bias) to be exerted on the vibrating element (15) for the control of the first and/or second vibration amplitudes, to cause controlled rotation of the direction (x) of the pilot mode in the plane of vibration (XY).--
Correction is required. See MPEP § 608.01(b).
Specification
The disclosure (specification) is objected to because of apparent administrative errors. Going forward with examination, the following specification paragraphs are interpreted to be (Note that in applicant’s response, where a change is requested in the specification, an entire paragraph of the specification containing the change will be needed):
Page 10, the paragraph beginning from line 9:
--The second control module 40 is able to estimate, from estimations of the vibrations of the vibrating element 15 according to the direction y of the detection mode transmitted by the reference frame change module 21 and of the phase φ(t) a second force Fass,y, the direction of which is the direction y of the detection mode. The second force Fass,y is the force that must be exerted to servo a second amplitude characteristic of the vibrations of the vibrating element 15 according to the direction y of the detection mode to a detection amplitude ymax, the vibrating element 15 vibrating in sinusoidal mode according to the direction y of the detection mode at the resonance angular frequency ω.--
Appropriate correction is required.
Claim Rejections - 35 USC § 101
35 U.S.C. 101 reads as follows:
Whoever invents or discovers any new and useful process, machine, manufacture, or composition of matter, or any new and useful improvement thereof, may obtain a patent therefor, subject to the conditions and requirements of this title.
Claims 1-10 are rejected under 35 U.S.C. 101 because it is directed to a judicial exception relating to an abstract idea without significant more.
The claims recite a gyroscopic measurement method comprising steps that appear to be merely a mental process practiced mentally and not integrated into any of the physical statutory patentable categories: process, machine, manufacture, or composition of matter. One would not be able to physically practice claims 1-10 (See MPEP 2106).
Going forward with examination, at least independent claim 1 is interpreted to be (Note that the numbers in parentheses are for ease of understanding the claims, but may be omitted):
--1. A gyroscopic measurement method by means of a sensor (10) comprising a housing (12) and a vibrating element (15) able to vibrate relative to the housing (12) in a plane of vibration attached to the housing (12) simultaneously according to a direction (X) of a pilot mode and according to a direction (Y) of a detection mode different from the direction (X) of the pilot mode, the method comprising the following steps of:
a) using a control module (35, 40) to servo to servo a second vibration amplitude of the vibrating element according to the direction of the detection mode to a predetermined detection amplitude, and
b) using a determination module (55) to determine mes) of the housing (12) relative to a sensitive axis (Z-axis) of the sensor from measurements of the vibrations of the vibrating element (15) and the pilot amplitude,
the method being characterized in that excitation means (45B, 45C) introduces a predetermined bias (ξ(t)) , the predetermined bias (ξ(t)) is used to determine a biased force (Fass,bias) to be exerted on the vibrating element (15) for servoing the first and/or second vibration amplitudes, wherein
(ξ(t)) causes and
the determination module (55) further determines the instantaneous angular speed (Ωmes) of the housing (12) (ξ(t)).--
Allowable Subject Matter
Claims 1-10 would be allowed if the above objections and rejections were overcome. The following would be an examiner’s statement of reasons for allowance:
With respect to independent claim 1, prior art of record doesn’t teach, suggest, or render obvious the total combination of the recited features, including the following allowable subject matter:
“…a) using a control module (35, 40) to servo a first vibration amplitude of the vibrating element (15) according to the direction of the pilot mode to a predetermined pilot amplitude, and to servo a second vibration amplitude of the vibrating element according to the direction of the detection mode to a predetermined detection amplitude, and
b) using a determination module (55) to determine an instantaneous angular speed (Ωmes) of the housing (12) relative to a sensitive axis (Z-axis) of the sensor from measurements of the vibrations of the vibrating element (15) and the pilot amplitude,
the method being characterized in that excitation means (45B, 45C) introduces a predetermined bias (ξ(t)) into a measurement of an angular position of the direction of the pilot mode, the predetermined bias (ξ(t)) is used to determine a biased force (Fass,bias) to be exerted on the vibrating element (15) for servoing the first and/or second vibration amplitudes, wherein
the predetermined bias (ξ(t)) causes a controlled rotation of the direction of the pilot mode in the plane of vibration, and
the determination module (55) further determines the instantaneous angular speed (Ωmes) of the housing (12) from the predetermined bias (ξ(t)).”
(Claims 2-10 are dependent on claim 1.)
Conclusion
The prior art made of record below and not relied upon is considered pertinent to applicant’s disclosure/invention.
US 6,598,455 B1 to Gutierrrez et al. (a reference listed in an IDS filed on 7/30/2024) discloses a gyroscope measurement method in which electrostatic elements already present in a gyroscope are used to simulate Coriolis forces. Similar to the present invention, an artificial electrostatic rotation signal (bias) is added to a closed-loop force rebalance system to perform an inertial test of a Coriolis vibratory gyroscope. Gutierrrez et al. however fails to teach the allowable subject matter.
Any inquiry concerning this communication or earlier communications from the examiner should be directed to Nguyen (Wyn) Q. Ha whose telephone number is (571) 272-2863, email: nguyenq.ha@uspto.gov. The examiner can normally be reached Monday - Friday 8 am - 4:30 pm (Eastern Time).
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/Nguyen Q. Ha/Primary Examiner, Art Unit 2853 June 17, 2026
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