Torsional anomalies detection system
First Claim
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1. A system for detecting torsional anomalies of an aircraft during a failure, the aircraft having a first drive shaft and a second drive shaft, the system comprising:
- a grating, having;
a plurality of teeth extending from the grating, the grating coupled to a first interconnection between the first drive shaft and the second drive shaft;
a support bracket in close proximity to the first interconnection and positioned about the grating;
a first sensor mounted on the support bracket;
a second sensor mounted on the support bracket; and
a processor comprising;
a lookup table comprising;
a plurality of spectral data of predetermined faults;
the processor for comparing a spectral analysis of an output of the first sensor and second sensor to the lookup table;
wherein the first sensor and second sensor are configured to detect the teeth of the grating.
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Abstract
A method and apparatus for determining failure diagnosis of drive systems of rotorcrafts through measuring the spectral characteristics of rotational oscillations and torsional oscillations and steady windup of a drive shaft. Mechanical anomalies of the drive system will alter the spectral characteristics of rotational oscillations and torsional oscillations and steady windup as detected by a pair of variable reluctance sensors in conjunction with a radial grating mounted on the drive shaft.
41 Citations
14 Claims
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1. A system for detecting torsional anomalies of an aircraft during a failure, the aircraft having a first drive shaft and a second drive shaft, the system comprising:
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a grating, having; a plurality of teeth extending from the grating, the grating coupled to a first interconnection between the first drive shaft and the second drive shaft; a support bracket in close proximity to the first interconnection and positioned about the grating; a first sensor mounted on the support bracket; a second sensor mounted on the support bracket; and a processor comprising; a lookup table comprising; a plurality of spectral data of predetermined faults; the processor for comparing a spectral analysis of an output of the first sensor and second sensor to the lookup table; wherein the first sensor and second sensor are configured to detect the teeth of the grating. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A system for detecting torsional anomalies of an aircraft during a failure, the aircraft having a first drive shaft and a second drive shaft, the system comprising:
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a first sensor assembly having; a forward support bracket; a first forward sensor; a second forward sensor; and a first grating, having; a plurality of teeth radially extending from the first grating; the first and second forward sensors being mounted on the forward support bracket and positioned about the first grating; a second sensor assembly having; an aft support bracket; a first aft sensor; a second aft sensor; and a second grating; the first and second aft sensors being mounted on the aft support bracket and positioned about the second grating; and a processor having; a lookup table; wherein the lookup table comprises a plurality of spectral data of predetermined faults, the processor configured for analyzing a spectral analysis of an outputs of the first and second forward sensors and a spectral analysis of an outputs of the first and second aft sensors; wherein the first and second forward sensors are configured to detect the teeth of the first grating. - View Dependent Claims (8, 9, 10, 11, 12, 13, 14)
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Specification