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US4983034A Expired / Lapsed US ⏱️ 0.0 years remaining

Composite integrity monitoring

Assignee: Simmonds Precision Products Inc
•
Filing: 1989-02-13
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Granted: 1991-01-08
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Expires: 2009-02-13
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Abstract

No abstract record available.

Inventors

  • 👤 William B. Spillman, Jr.

Bibliographic Details

Application Number —
Jurisdiction US
Data Source google_patents
Last Synchronized 2026-11-08 16:22
CPC Classifications
G; G01; G01L; G01L1/00; G01L1/24; G01L1/242

Claims Analysis

Total Claims: 16
Claim 1
Independent Claim 137 words
A method of composite integrity monitoring by sensing strain distributed along an optical fiber, comprising the steps of: providing a composite structure, and an optical fiber, said structure comprising composite material, said optical fiber being embedded in said composite material, said optical fiber being subjected to strain; launching initial frequency varying modulated optical energy having a selectively controllable polarization state into said optical fiber; providing a reference signal representative of the modulated optical energy; mixing a portion of the optical energy backscattered from the fiber with a portion of the reference signal to produce a beat signal, the frequency of which is representative of strain at a location along the fiber; sensing the polarization state of the backscattered optical energy; and controlling the polarization state of said initial optical energy launched in response to said beat signal.
Claim 2
Independent Claim 137 words
A method of composite integrity monitoring by sensing strain distributed along an optical fiber, comprising the steps of: providing a composite structure, and an optical fiber, said structure comprising composite material, said optical fiber being embedded in said composite material, said optical fiber being subjected to strain; launching initial frequency varying modulated optical energy having a selectively controllable polarization state into said optical fiber; providing a reference signal representative of the modulated optical energy; mixing a portion of the optical energy backscattered from the fiber with a portion of the reference signal to produce a beat signal, the frequency of which is representative of strain at a location along the fiber; sensing the polarization state of the backscattered optical energy; and controlling the polarization state of said initial optical energy launched in response to said beat signal.
Claim 3
Dependent Claim 38 words
The method of claim 1, wherein said controlling step comprises controlling the polarization state of the optical energy launched in response to said beat signal, to reduce the effect of backscattering at locations other than said strain location.
Claim 4
Dependent Claim 11 words
The method of claim 1 wherein said structure is an aircraft.
Claim 5
Dependent Claim 11 words
The method of claim 1 wherein said structure is a spacecraft.
Claim 6
Dependent Claim 11 words
The method of claim 1 wherein said composite material comprises graphite.
Claim 7
Independent Claim 158 words
A method of composite integrity monitoring by sensing strain at a selected location along an optical fiber, comprising the steps of: providing a composite structure, and an optical fiber, said structure comprising composite material, said optical fiber being embedded in said composite material, said optical fiber being subjected to strain; launching initial frequency varying optical energy having a selectively controllable polarization state into said optical fiber; providing a reference signal representative of the modulated optical energy; sensing the polarization state of the backscattered optical energy from the fiber below a selected frequency; controlling the polarization state of said initial optical energy launched in response to said sensed polarization state of the backscattered energy to minimize backscatter; and increasing the selected frequency to correspond to a selected location and mixing a portion of the optical energy backscattered from the fiber with a portion of the reference signal to produce a beat signal representative of strain at the selected location.
Claim 8
Independent Claim 158 words
A method of composite integrity monitoring by sensing strain at a selected location along an optical fiber, comprising the steps of: providing a composite structure, and an optical fiber, said structure comprising composite material, said optical fiber being embedded in said composite material, said optical fiber being subjected to strain; launching initial frequency varying optical energy having a selectively controllable polarization state into said optical fiber; providing a reference signal representative of the modulated optical energy; sensing the polarization state of the backscattered optical energy from the fiber below a selected frequency; controlling the polarization state of said initial optical energy launched in response to said sensed polarization state of the backscattered energy to minimize backscatter; and increasing the selected frequency to correspond to a selected location and mixing a portion of the optical energy backscattered from the fiber with a portion of the reference signal to produce a beat signal representative of strain at the selected location.
Claim 9
Dependent Claim 11 words
The method of claim 6 wherein said structure is an aircraft.
Claim 10
Dependent Claim 11 words
The method of claim 6 wherein said structure is a spacecraft.
Claim 11
Dependent Claim 11 words
The method of claim 6 wherein said composite material comprises graphite.
Claim 12
Independent Claim 169 words
A method of composite integrity monitoring by sensing strain at successive selected locations along an optical fiber, comprising the steps of: providing a composite structure, and an optical fiber, said structure comprising composite material, said optical fiber being embedded in said composite material, said optical fiber being subjected to strain; launching initial frequency varying optical energy having a selectively controllable polarization state into said optical fiber; providing a reference signal representative of the modulated optical energy; sensing the polarization state of the backscattered optical energy from the fiber below a selected frequency; controlling the polarization state of said initial optical energy launched in response to said sensed polarization state of the backscattered energy to minimize backscatter; increasing the selected frequency to correspond to a selected location and mixing a portion of the optical energy backscattered from the fiber with a portion of the reference signal to produce a beat signal representative of strain at the selected location; and repeating the second, third, and fourth steps at selectively incremented frequencies.
Claim 13
Independent Claim 169 words
A method of composite integrity monitoring by sensing strain at successive selected locations along an optical fiber, comprising the steps of: providing a composite structure, and an optical fiber, said structure comprising composite material, said optical fiber being embedded in said composite material, said optical fiber being subjected to strain; launching initial frequency varying optical energy having a selectively controllable polarization state into said optical fiber; providing a reference signal representative of the modulated optical energy; sensing the polarization state of the backscattered optical energy from the fiber below a selected frequency; controlling the polarization state of said initial optical energy launched in response to said sensed polarization state of the backscattered energy to minimize backscatter; increasing the selected frequency to correspond to a selected location and mixing a portion of the optical energy backscattered from the fiber with a portion of the reference signal to produce a beat signal representative of strain at the selected location; and repeating the second, third, and fourth steps at selectively incremented frequencies.
Claim 14
Dependent Claim 11 words
The method of claim 10 wherein said structure is an aircraft.
Claim 15
Dependent Claim 11 words
The method of claim 10 wherein said structure is a spacecraft.
Claim 16
Dependent Claim 11 words
The method of claim 10 wherein said composite material comprises graphite.

References Cited (Backward Citations)

US4836030A Cited
US4692610A Cited
US4840481A Cited

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