JP2020008562A - 温度に敏感でない損傷検出のためのシステム - Google Patents
温度に敏感でない損傷検出のためのシステム Download PDFInfo
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- JP2020008562A JP2020008562A JP2019077706A JP2019077706A JP2020008562A JP 2020008562 A JP2020008562 A JP 2020008562A JP 2019077706 A JP2019077706 A JP 2019077706A JP 2019077706 A JP2019077706 A JP 2019077706A JP 2020008562 A JP2020008562 A JP 2020008562A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0033—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining damage, crack or wear
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/22—Details, e.g. general constructional or apparatus details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/44—Processing the detected response signal, e.g. electronic circuits specially adapted therefor
- G01N29/4409—Processing the detected response signal, e.g. electronic circuits specially adapted therefor by comparison
- G01N29/4436—Processing the detected response signal, e.g. electronic circuits specially adapted therefor by comparison with a reference signal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/02—Indexing codes associated with the analysed material
- G01N2291/028—Material parameters
- G01N2291/0289—Internal structure, e.g. defects, grain size, texture
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/10—Number of transducers
- G01N2291/106—Number of transducers one or more transducer arrays
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/26—Scanned objects
- G01N2291/269—Various geometry objects
- G01N2291/2694—Wings or other aircraft parts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
Description
Gain DI = Gain’ - 1 数式2
102 構造
104 トランスデューサ
104a アクチュエータトランスデューサ
104b センサトランスデューサ
104c センサトランスデューサ
106 アレイ
108 データ収集(DAQ)回路
110 配線束
112 経路
114 経路
116 プロセッサ
118 メモリ
202 基準振動信号
204 振幅
206 時間
208 比較振動信号
210 誤差信号
302 グラフ
304 グラフ
306 グラフ
308 グラフ
310 グラフ
312 グラフ
314 電圧
316 時間
318 基準振動信号
320 比較振動信号
322 比較振動信号
324 比較振動信号
326 比較振動信号
328 比較振動信号
330 比較振動信号
400 方法
Claims (10)
- 航空機構造の損傷を検出するためのシステムであって、前記システムが、
航空機構造(102)と、
前記航空機構造の構造健全性を監視するように構成された構造健全性監視(SHM)システム(100)と、
を備え、前記SHMシステムが、
前記航空機構造に接合され、
第1の時刻に前記航空機構造を通して伝搬する基準振幅を有する基準振動信号を発生させ、
前記第1の時刻の後の第2の時刻に前記航空機構造を通して伝搬する比較振幅を有する比較振動信号を発生させるように構成されたアクチュエータ(104a)であって、前記比較振幅が前記第1の時刻と前記第2の時刻との間に前記航空機構造が受けた損傷を表す、アクチュエータ(104a)と、
前記航空機構造に接合され、前記基準振動信号および前記比較振動信号を受信するように構成されたセンサ(104b、104c)と、
前記基準振幅を前記比較振幅で除算した値の関数として利得損傷指数を計算するように構成されたプロセッサ(116)であって、前記利得損傷指数は、前記SHMシステムが前記航空機構造の前記構造健全性を温度と無関係に監視することを可能にする、プロセッサ(116)と、
を備える、システム。 - 前記利得損傷指数が前記航空機構造(102)内の亀裂の存在または不存在を示す、請求項1に記載のシステム。
- 前記航空機構造(102)が複数の積層を有する複合構造を備える、請求項1または2に記載のシステム。
- 前記アクチュエータ(104a)がチタン酸ジルコン酸鉛(PZT)トランスデューサを備える、請求項1から3のいずれか一項に記載のシステム。
- 前記プロセッサ(116)が、前記第1の時刻と前記第2の時刻との間の温度変化に起因する前記比較振動信号の位相ずれを除去するようにさらに構成された、請求項1から4のいずれか一項に記載のシステム。
- 前記プロセッサ(116)が、前記基準振幅を前記比較振幅で乗算して前記比較振幅の2乗で除算した値の関数として前記利得損傷指数を計算するようにさらに構成された、請求項1から5のいずれか一項に記載のシステム。
- 構造(102)内の損傷を検出する方法(400)であって、
前記構造のための基準振動信号をメモリから取得するステップ(410)であって、前記基準振動信号が以前に収集されたものである、ステップ(410)と、
前記構造に接合された第1のトランスデューサに電圧を加えて、前記構造を通して伝搬する比較振動信号を発生させるステップ(420)と、
前記構造に接合された第2のトランスデューサにおいて前記比較振動信号を受信するステップ(430)と、
前記基準振動信号および前記比較振動信号を使用して利得損傷指数アルゴリズムを実行して、前記基準振動信号の振幅を前記比較振動信号の振幅で乗算して前記比較振動信号の前記振幅の2乗で除算した値の関数として利得損傷指数を計算するステップ(440)と、
前記利得損傷指数が正であるときに前記構造内の損傷を識別するステップ(450)と、
を含む、方法(400)。 - 前記基準振動信号が以前に収集されたときの温度に対する、前記比較振動信号が受信される(430)ときの温度の変化に起因する前記比較振動信号の位相ずれを検出するステップと、
前記利得損傷指数アルゴリズムを実行する(440)前に前記比較振動信号から前記位相ずれを除去するステップと、
をさらに含む、請求項7に記載の方法(400)。 - ほぼ前記第1のトランスデューサの位置において、前記第1のトランスデューサを接合する前に、前記構造に接合された第3のトランスデューサに電圧を加えて前記基準振動信号を発生させるステップと、
ほぼ前記第2のトランスデューサの位置において、前記第2のトランスデューサを接合する前に、前記構造に接合された第4のトランスデューサにおいて前記基準振動信号を受信するステップと、
前記基準振動信号を前記メモリに保存するステップと、
をさらに含む、請求項7または8に記載の方法(400)。 - 前記構造内の損傷を識別するステップ(450)が、前記構造内の亀裂を検出するステップを含む、請求項7から9のいずれか一項に記載の方法(400)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US16/028,962 | 2018-07-06 | ||
US16/028,962 US10816436B2 (en) | 2018-07-06 | 2018-07-06 | System for temperature insensitive damage detection |
Publications (2)
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JP2020008562A true JP2020008562A (ja) | 2020-01-16 |
JP7247007B2 JP7247007B2 (ja) | 2023-03-28 |
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JP2019077706A Active JP7247007B2 (ja) | 2018-07-06 | 2019-04-16 | 温度に敏感でない損傷検出のためのシステム |
Country Status (4)
Country | Link |
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US (1) | US10816436B2 (ja) |
EP (1) | EP3591365B1 (ja) |
JP (1) | JP7247007B2 (ja) |
CN (1) | CN110683061A (ja) |
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US10895592B2 (en) | 2017-03-24 | 2021-01-19 | Rosemount Aerospace Inc. | Probe heater remaining useful life determination |
US11060992B2 (en) | 2017-03-24 | 2021-07-13 | Rosemount Aerospace Inc. | Probe heater remaining useful life determination |
US11061080B2 (en) | 2018-12-14 | 2021-07-13 | Rosemount Aerospace Inc. | Real time operational leakage current measurement for probe heater PHM and prediction of remaining useful life |
US10962580B2 (en) * | 2018-12-14 | 2021-03-30 | Rosemount Aerospace Inc. | Electric arc detection for probe heater PHM and prediction of remaining useful life |
US11639954B2 (en) | 2019-05-29 | 2023-05-02 | Rosemount Aerospace Inc. | Differential leakage current measurement for heater health monitoring |
US11930563B2 (en) | 2019-09-16 | 2024-03-12 | Rosemount Aerospace Inc. | Monitoring and extending heater life through power supply polarity switching |
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EP3591365A1 (en) | 2020-01-08 |
JP7247007B2 (ja) | 2023-03-28 |
CN110683061A (zh) | 2020-01-14 |
US20200011761A1 (en) | 2020-01-09 |
US10816436B2 (en) | 2020-10-27 |
EP3591365B1 (en) | 2022-07-06 |
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