JPH04201696A - Aircraft diagnosis system - Google Patents
Aircraft diagnosis systemInfo
- Publication number
- JPH04201696A JPH04201696A JP2330788A JP33078890A JPH04201696A JP H04201696 A JPH04201696 A JP H04201696A JP 2330788 A JP2330788 A JP 2330788A JP 33078890 A JP33078890 A JP 33078890A JP H04201696 A JPH04201696 A JP H04201696A
- Authority
- JP
- Japan
- Prior art keywords
- sensor
- aircraft
- data processing
- diagnosis
- data
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000003745 diagnosis Methods 0.000 title abstract description 7
- 238000007435 diagnostic evaluation Methods 0.000 claims description 16
- 238000000034 method Methods 0.000 claims description 3
- 238000007689 inspection Methods 0.000 abstract description 15
- 238000010276 construction Methods 0.000 abstract description 4
- 238000001093 holography Methods 0.000 abstract description 3
- 238000011156 evaluation Methods 0.000 abstract 2
- 238000011158 quantitative evaluation Methods 0.000 abstract 1
- 238000012423 maintenance Methods 0.000 description 18
- 238000010586 diagram Methods 0.000 description 5
- 238000001514 detection method Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000002950 deficient Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000002601 radiography Methods 0.000 description 2
- 230000037237 body shape Effects 0.000 description 1
- 239000000084 colloidal system Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
- G01N2291/025—Change of phase or condition
- G01N2291/0258—Structural degradation, e.g. fatigue of composites, ageing of oils
-
- 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
- G01N2291/04—Wave modes and trajectories
- G01N2291/044—Internal reflections (echoes), e.g. on walls or defects
Landscapes
- Analysing Materials By The Use Of Radiation (AREA)
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は航空機の機体構造、装備及びエンジンを迅速、
適確に診断評価する航空機診断システムに関する。[Detailed Description of the Invention] [Industrial Field of Application] The present invention provides a quick and easy way to improve the structure, equipment, and engine of an aircraft.
This invention relates to an aircraft diagnostic system that accurately diagnoses and evaluates.
（従来の技術）
従来は航空機の機体構造、装備の点検、整備（主に重整
ｇ１）は機体装着状態では不可能であり分解点検し、整
備している。又、エンジンについては点検、診断項目に
も関係するが、機体より下ろして点検、整備しているの
で工期、コストの点で問題があり機体の連続計画に大き
な影響を与えて−いる。(Prior Art) Conventionally, inspection and maintenance (mainly heavy maintenance G1) of an aircraft's fuselage structure and equipment was impossible while the aircraft was attached to the aircraft, and maintenance was performed by disassembling and inspecting the equipment. In addition, the engine is also related to inspection and diagnosis items, but since the engine is inspected and maintained by being removed from the aircraft, there are problems in terms of construction time and cost, which has a large impact on the aircraft continuity plan.
〔発明が解決しようとする課題］
航空機の定期点検、整備は機体の飛行安全上、極めて重
要な業務である。この点検、整備に関しては航空機運軌
法又は機体メーカの整備基準等から飛行時間等により、
Ａ（又はＴ）、Ｂ、’Ｃ及びＤチエツクの各整備を行っ
ている。この整備はＡからＤになる程点検整備項目のエ
リアが増大する。[Problems to be Solved by the Invention] Periodic inspection and maintenance of aircraft is extremely important work for flight safety of the aircraft. Regarding this inspection and maintenance, it depends on the flight time etc. based on the Aircraft Trajectory Act or the maintenance standards of the aircraft manufacturer.
A (or T), B, 'C and D checks are being maintained. In this maintenance, the area of inspection and maintenance items increases from A to D.
特にＤチエツクでは機体をかなり分解するほか、エンジ
ンを機体より下ろして点検、整備しなくてはならない。In particular, D-Check requires disassembling the aircraft and removing the engine from the aircraft for inspection and maintenance.
従って、二〇〇又はＤチエツクでの点検整備費用や工期
が大きく、飛行機整備屋としては、迅速、適確な自動診
断システム装置の開発が強く求められている。Therefore, inspection and maintenance costs and construction times for 200 or D checks are large, and there is a strong need for aircraft maintenance shops to develop a quick and accurate automatic diagnosis system.
（課題を解決するための手段］ 本発明は上記課題を解決するため次の手段を講する。(Means for solving problems) The present invention takes the following measures to solve the above problems.
すなわち、軌空機診断システムとして、診断用センサと
、同センサを支持し上下左右前後移動可能なセンサ操作
手段と、上記診断用センサの信号を受け処理解析するデ
ータ処理解析装置と、同データ処理解析装置のデータを
受け診断評価処理する診断評価装置と、上記診断用セン
サ、上記センサ操作手段、上記データ処理解析装置、お
よび上記診断評価装置へ信号を送りそれぞれを制御する
制御盤とを設ｉ才る。In other words, the orbital vehicle diagnostic system includes a diagnostic sensor, a sensor operating means that supports the sensor and is movable up, down, left, right, forward and backward, a data processing and analysis device that receives and processes and analyzes the signals of the diagnostic sensor, and a data processing A diagnostic evaluation device that receives data from the analysis device and performs diagnostic evaluation processing, and a control panel that sends signals to the diagnostic sensor, the sensor operating means, the data processing analysis device, and the diagnostic evaluation device and controls each of them is installed. Be talented.
上記手段により、制御盤の信号でセンサ操作手段が移動
し、診断用センサ（送受信部）を航空−の所定の個所に
沿って動かす０診断用センサにより機体構造、装備の健
全性、エンジン性能等の情報が検出され、データ処理解
析装置へ送られ処理解析される。そのデータは診断評価
装置へ送られ診断評価処理され、修理内容、部品交換の
要否、残存寿命等を出力する。With the above means, the sensor operation means moves in response to a signal from the control panel, and the diagnostic sensor (transmission/reception unit) is moved along a predetermined point on the aircraft. The information is detected and sent to a data processing and analysis device for processing and analysis. The data is sent to the diagnostic evaluation device, where it undergoes diagnostic evaluation processing, and outputs information such as the details of the repair, whether or not parts need to be replaced, and the remaining service life.
以上のようにして、自動的に航空機が診断されるように
なる。In the manner described above, the aircraft will be automatically diagnosed.
本発明の一実施例を第１図から第７図により説明する。 An embodiment of the present invention will be described with reference to FIGS. 1 to 7.
第１図（ａ）にて、検査対象の航空機１のそばに、セン
サ操作手段が配置される。センサ操作手段は台車２２と
、台車２２に取付けられ、上下および左右に移動可能で
かつ上端に診断用センサ（送受信部）７を持つ操作台７
を有する。In FIG. 1(a), sensor operating means is placed near the aircraft 1 to be inspected. The sensor operating means includes a trolley 22 and an operating table 7 that is attached to the trolley 22 and is movable up and down and left and right, and has a diagnostic sensor (transmission/reception unit) 7 at the upper end.
has.
診断用センサ７としてはレーザホログラフィ、サーモビ
エア、レーザ超音波探傷、超音波探傷、中性子ラジオグ
ラフィ、ＡＥ （アコ−ステイクエミッション）ならび
に光、音、熱および放射線等のセンサを有する。The diagnostic sensor 7 includes laser holography, thermovia, laser ultrasonic flaw detection, ultrasonic flaw detection, neutron radiography, AE (acoustic emission), and light, sound, heat, and radiation sensors.
台車２２にはデータ処理解析装置３、診断評価装置４．
１ＩＪＩＩ盤６が搭載されている。また、第５図に示す
ように、センサ７の出力はデータ処理解析装置３、診断
評価装置４へ送られる。また制御盤６の出力は台車２２
、センサ操作台２３、センサ７、データ処理解析装置３
、診断評価装置４へ送られる。The trolley 22 includes a data processing analysis device 3, a diagnostic evaluation device 4.
1IJII board 6 is installed. Further, as shown in FIG. 5, the output of the sensor 7 is sent to a data processing analysis device 3 and a diagnostic evaluation device 4. In addition, the output of the control panel 6 is
, sensor operation table 23, sensor 7, data processing analysis device 3
, is sent to the diagnostic evaluation device 4.
以上の構成において、機体外板検査を行う場合、同モー
ドを選ぶと、制御盤６からの信号でセンサ７のレーザホ
ログラフィまたはサーモビエアが作動しながらセンサ操
作台２３および台車２２の移動により、航空機１の機体
外面の要点検部位に沿って移動する。センサ７の出力は
データ処理解析装置３へ送られ処理解析され、例えば同
図（ｂ）に示すようにデータ表示される０図中ａは欠陥
部を示す。In the above configuration, when inspecting the outer skin of the aircraft, if the same mode is selected, the laser holography or thermovia of the sensor 7 is activated by the signal from the control panel 6, and the sensor operation table 23 and the trolley 22 are moved. Move along the areas requiring inspection on the exterior of the aircraft. The output of the sensor 7 is sent to the data processing and analysis device 3, where it is processed and analyzed, and the data is displayed, for example, as shown in FIG.
さらにこれらの信号は診断評価装置４へ送られ診断評価
処理され、例えば同図（ｃ）に示すように表示される。Furthermore, these signals are sent to the diagnostic evaluation device 4 where they are subjected to diagnostic evaluation processing and displayed, for example, as shown in FIG. 4(c).
き裂、はく離検査の場合、同モードを選ぶと、制御盤６
からの信号で、センサ７のレーザ超音波探傷または超音
波探傷が作動し、上記のように要点検部位を移動する（
第２図（ａ））、センサ７からの情報はデータ処理解析
装置３へ送られデータ処理解析され、例えば同図Ｃｂ）
または（ｃ）のようにデータ表示される０図中すはき裂
、Ｃはファスナ、ｄはフィンティング、ｅは接着不良部
を示す、接着不良部ｅの断面を第４図に示す０図中２５
はスキン、２６はハニカムコア、ｆはコアの潰れ、破壊
、ｇはミストコロージッン、ｈは水滴、ｉはスキンのは
く離を示す。When inspecting cracks and peeling, if you select this mode, the control panel 6
The laser ultrasonic flaw detection or ultrasonic flaw detection of the sensor 7 is activated by the signal from the sensor 7, and the inspection area is moved as described above (
Figure 2 (a)), the information from the sensor 7 is sent to the data processing and analysis device 3 for data processing and analysis, for example, Figure 2 (Cb))
Or, data is displayed as shown in (c) in Figure 0, where C is a fastener, d is a finning, and e is a defective bonding area. Figure 4 shows the cross section of the defective bonding area e. middle school 25
26 is the skin, 26 is the honeycomb core, f is the crushing or destruction of the core, g is the mist colloid, h is the water droplet, and i is the peeling of the skin.
これらの情報は診断評価装置４へ送られ診断評価処理さ
れ、例えば第３図（ａ）、 （ｂ）のように表示される
。This information is sent to the diagnostic evaluation device 4, where it undergoes diagnostic evaluation processing and is displayed, for example, as shown in FIGS. 3(a) and 3(b).
腐食検査の場合、同モードを選ぶと、制御盤６からの信
号で、センサ７の中性子ラジオグラフィまたはＸ線ラジ
オグラフィが作動し、上記のように要点検部位を移動す
る（第５図（ａ））、センサ７からの情報はデータ処理
解析装置３へ送られデータ処理され、例えば同図（ｂ）
または（ｃ）のようにデータ表示される０図中ｊは水分
腐食部、ｋは腐食部、２７は外板、２８は桁材、２９は
ファスナを示す。In the case of corrosion inspection, when the same mode is selected, the neutron radiography or )), the information from the sensor 7 is sent to the data processing analysis device 3 and data processed, for example, as shown in FIG.
Or, data is displayed as shown in (c). In the figure, j indicates a water-corroded portion, k indicates a corroded portion, 27 indicates an outer plate, 28 indicates a girder material, and 29 indicates a fastener.
これらの情報は診断評価装置４へ送られ診断評価処理さ
れ、例えば第６図（ａ）、 （ｂ）のように表示される
。These pieces of information are sent to the diagnostic evaluation device 4, subjected to diagnostic evaluation processing, and displayed, for example, as shown in FIGS. 6(a) and 6(b).
以上のようにして、大きさ、機体形状の異なる各種航空
機に対しても、点検整備の必要性及びその程度等を定量
的に評価するのみならず、残存寿命（余寿命予測）まで
推定する。In the manner described above, not only the necessity and extent of inspection and maintenance are quantitatively evaluated for various aircraft with different sizes and body shapes, but also the remaining lifespan (remaining lifespan prediction) is estimated.
これによって、従来の航空機型整備時（Ｄチエツク又は
ＩＲＡＮ ）における点検、整備の迅速化が図れるのみ
ならず、機体構造、装備及びエンジン等容対象部位の損
傷程度に応じた適材適所の整備や修理が適確かつ効率的
に実施できる。This not only speeds up inspection and maintenance during conventional aircraft type maintenance (D-check or IRAN), but also allows for maintenance and repair using the right people in the right places depending on the degree of damage to the aircraft structure, equipment, engine, etc. can be carried out appropriately and efficiently.
従って、整備費用の節減と工期の短縮化につながると同
時に機体装備、エンジンのシステマテイックな保全管理
が可能となる。Therefore, it is possible to reduce maintenance costs and shorten the construction period, while at the same time enabling systematic maintenance management of aircraft equipment and engines.
以上に説明したように、この発明によれば、大きさ、機
体形状の異なる各種航空機に対しても点検整備の必要性
及びその程度等を定量的に評価するのみならず、残存寿
命（余寿命予測）まで推定できるようになる。As explained above, according to the present invention, it is possible to not only quantitatively evaluate the necessity and extent of inspection and maintenance for various aircraft of different sizes and shapes, but also to evaluate the remaining life (remaining life). prediction).
ゝ 第１図（ａ）は本発明の一実施例の構成斜視図、同
図（ｂ）、 （ｃ）は作用説明図′、第２図（ａ）、
（ｂ）、 （ｃ）は同実施例の作用説明図、第３図（ａ
）、 （ｂ）は同実施例の作用説明図、第４図は同実施
例の作用説明図、第５図軸）、 （ｂ）、 （ｃ）は同
実施例の作用説明図、第６図（ａ）、 （ｂ）は同実施
例の作用説明図、第７図は同実施例の構成ブロック図で
ある。
ｌ・・・航空機（被検機体）
３・・・データ処理解析装置ゝ Fig. 1(a) is a perspective view of the configuration of an embodiment of the present invention, Fig. 1(b) and (c) are action explanatory views, Fig. 2(a),
(b) and (c) are action explanatory diagrams of the same embodiment, and Fig. 3 (a)
), (b) is an explanatory diagram of the action of the same embodiment, FIG. 4 is an explanatory diagram of the action of the same embodiment, and FIG. Figures (a) and (b) are action explanatory diagrams of the same embodiment, and Fig. 7 is a block diagram of the configuration of the same embodiment. l... Aircraft (tested aircraft) 3... Data processing analysis device
Claims (1)
能なセンサ操作手段と、上記診断用センサの信号を受け
処理解析するデータ処理解析装置と、同データ処理解析
装置のデータを受け診断評価処理する診断評価装置と、
上記診断用センサ、上記センサ操作手段、上記データ処
理解析装置、および上記診断評価装置へ信号を送りそれ
ぞれを制御する制御盤とを備えてなることを特徴とする
航空機診断システム。A diagnostic sensor, a sensor operating means that supports the sensor and is movable up, down, left, right, forward and back, a data processing and analysis device that receives and processes and analyzes signals from the diagnostic sensor, and a data processing and analysis device that receives and processes data from the data processing and analysis device. a diagnostic evaluation device for
An aircraft diagnostic system comprising: the diagnostic sensor, the sensor operating means, the data processing and analysis device, and a control panel that sends signals to and controls each of the diagnostic evaluation devices.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2330788A JPH04201696A (en) | 1990-11-30 | 1990-11-30 | Aircraft diagnosis system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2330788A JPH04201696A (en) | 1990-11-30 | 1990-11-30 | Aircraft diagnosis system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04201696A true JPH04201696A (en) | 1992-07-22 |
Family
ID=18236556
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2330788A Pending JPH04201696A (en) | 1990-11-30 | 1990-11-30 | Aircraft diagnosis system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04201696A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007183172A (en) * | 2006-01-06 | 2007-07-19 | Toshiba Corp | Method and apparatus for inspecting airframe |
| JP2012121562A (en) * | 2010-12-06 | 2012-06-28 | Boeing Co:The | Rapid rework analysis system |
-
1990
- 1990-11-30 JP JP2330788A patent/JPH04201696A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007183172A (en) * | 2006-01-06 | 2007-07-19 | Toshiba Corp | Method and apparatus for inspecting airframe |
| JP2012121562A (en) * | 2010-12-06 | 2012-06-28 | Boeing Co:The | Rapid rework analysis system |
| US9508047B2 (en) | 2010-12-06 | 2016-11-29 | The Boeing Company | Rapid rework analysis system |
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