JPS62231142A - Structural element - Google Patents
Structural elementInfo
- Publication number
- JPS62231142A JPS62231142A JP7459986A JP7459986A JPS62231142A JP S62231142 A JPS62231142 A JP S62231142A JP 7459986 A JP7459986 A JP 7459986A JP 7459986 A JP7459986 A JP 7459986A JP S62231142 A JPS62231142 A JP S62231142A
- Authority
- JP
- Japan
- Prior art keywords
- structural element
- light
- optical fiber
- wall member
- optical fibers
- 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
- 239000013307 optical fiber Substances 0.000 claims abstract description 19
- 238000001514 detection method Methods 0.000 claims abstract description 10
- 238000005336 cracking Methods 0.000 abstract 2
- 239000000835 fiber Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 241000270708 Testudinidae Species 0.000 description 1
- 241000209140 Triticum Species 0.000 description 1
- 235000021307 Triticum Nutrition 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
Landscapes
- Investigating Materials By The Use Of Optical Means Adapted For Particular Applications (AREA)
Abstract
Description
【発明の詳細な説明】
Ｅ産業上の利用分野］
Ａ：発明は、航空機の外壁や構造部材などに利用０［虎
な探傷機能を顧えた構造要素に関するものである。[Detailed Description of the Invention] E: Industrial Field of Application] A: The invention relates to a structural element that can be used for external walls of aircraft, structural members, etc., and is designed to have a flaw detection function.
ｌ従来の技ｆｒｌ
繰り返し荷重を受ける構造物においては、その耐用度お
よび損傷状態等を絶えずチェックし、安全性を期する必
要がある。特に航空機においては、その軽φ化が絶対的
な条件であるが故に、機体の各構成部材はｗｋ密な寿命
計算のもとにセーフティマージンの非常に少ない設計と
なっている。したがって、この種の部材には常に亀裂等
の促陥の発）１右無を監視し、その残り寿命を推定する
のが不ｌ「欠とされる０機体外壁などの亀裂等の探傷方
法には、外１しに放射線を照射する放射線探傷法などの
各種の非破壊検査方法の適用が考えられる。l Conventional Techniques frl In structures that are subjected to repeated loads, it is necessary to constantly check their durability and damage status to ensure safety. Particularly in the case of aircraft, since it is an absolute requirement to reduce the weight of the aircraft, each component of the aircraft body is designed with a very small safety margin based on careful life calculations. Therefore, it is indispensable to constantly monitor the occurrence of cracks and other defects in this type of component and estimate its remaining life. Various non-destructive testing methods, such as radiation flaw detection, which irradiates the outside with radiation, can be considered.
［発明が解決しようとする問題点］
ところが、既存の非破壊検査法を適用した場合では、設
備が大型化するヒに、これらの装置により、外壁内部序
の傷を見つけ出すには多くの時間と労力を必要とし、か
つ作業が非常に困難となる不那合がある。特に航空ａ等
のように様々の外力が作用する大型の組立品を分解せず
しかも内部の僅かな傷をも見逃すことのできない構造体
の探傷作業はとりわけ困難なものである。[Problems to be solved by the invention] However, when existing non-destructive inspection methods are applied, it takes a lot of time and effort to find flaws in the internal structure of external walls, as equipment becomes larger. There are disadvantages that require labor and are extremely difficult to work with. It is particularly difficult to detect flaws in structures such as aircraft aircraft, where even the slightest internal flaws cannot be overlooked without disassembling large assemblies that are subject to various external forces.
本発明は航空機に限らず様々の荷重が作用する硝逍′Ａ
！麦の損傷を容易にしかも確実に探知し得る構造要素を
提供することを目的としている。The present invention is applicable not only to aircraft but also to glass
! The object is to provide a structural element with which damage to wheat can be easily and reliably detected.
１闇題点を解決するための手段】
本発明は、かかる目的をｉｉ［成するために２構造・々
泰の内部または表面に損傷検知用の光ファイ八−を設け
たことを特徴とする。1. Means for Solving the Problems] The present invention is characterized in that an optical fiber for damage detection is provided inside or on the surface of the structure. .
［作用］
このような手段により構成される本発明によれば、様々
の外力が作用する構造安泰に生じた亀裂部の傷は要素の
内部または表面に延設された尤ファイバーに投光し、そ
の漏光状態を検知することにより容易に探傷することが
できる。[Function] According to the present invention constituted by such a means, flaws in the cracks caused in the structural stability where various external forces act are emitted to the light fibers extending inside or on the surface of the element, Flaw detection can be easily performed by detecting the light leakage state.
［実施例］ 以ド１本発明の一実施例を図面を参照して説明する。[Example] An embodiment of the present invention will now be described with reference to the drawings.
第１図は本発明に係る探傷機構を１１：顧した航空機の
外壁部材を略示したものであり、第２図は。FIG. 1 schematically shows an outer wall member of an aircraft incorporating the flaw detection mechanism according to the present invention, and FIG.
その一部を拡大して示したものである。This is an enlarged view of a part of it.
外壁部材ｌはシート状のプリプレグ２をＮａ枚積み重ね
て加熱しつつ圧着したもので形成されている。前記プリ
プレグ２は安泰等の強化繊維にエポキシ樹脂凛を含浸さ
せたもので、強度、剛性および比重等においてアルミ合
金等に優れることから、８年航空機の外壁等に利用され
つつある。The outer wall member 1 is formed by stacking Na sheets of prepreg 2 and pressing them together while heating. The prepreg 2 is made by impregnating reinforcing fibers such as Antai with epoxy resin Rin, and since it is superior to aluminum alloys in terms of strength, rigidity, specific gravity, etc., it has been used for the outer walls of aircraft since 1980.
このようなプリプレグ２で形成された前記外壁部材ｌの
表面には等間隔をあけて長手方向に複数の光ファイバー
３を敷、没しである。具体的には前記光ファイバー３は
、加熱圧着前のプリプレグ２の表面に他のｍｍ４で！１
ＳＪＬ、固着してあり、これらプリプレグ２の積重で形
成される外壁部材の内部に尤ファイバー３を埋設するよ
うにしている（第２図参照）、そして、その投光側端Ｍ
５を一箇所にまとめるとともに、端面をそろえて入光し
易くしてあり、更に受光側端部６は外壁部材ｌの端面か
ら突出させである。光ファイバー３は、周知のように芯
線のコア７の周囲をクラッド８で包んだもので、コア７
の中を光が伝幡するようになっており、また両端５．６
間に損傷が無いかぎり途中で漏光しないようになってい
る。A plurality of optical fibers 3 are laid in the longitudinal direction at equal intervals on the surface of the outer wall member l formed of such prepreg 2. Specifically, the optical fiber 3 is placed on the surface of the prepreg 2 before heat and pressure bonding with another mm4! 1
SJL is fixed, and the fiber 3 is embedded inside the outer wall member formed by stacking these prepregs 2 (see Fig. 2), and its light emitting side end M
5 are gathered in one place, and their end faces are aligned to facilitate light entry, and the light-receiving side end 6 is made to protrude from the end face of the outer wall member l. As is well known, the optical fiber 3 has a core 7 wrapped around a cladding 8.
Light is transmitted through the inside, and both ends are 5.6
As long as there is no damage in between, no light will leak in the middle.
このような実施例によると、加熱圧着前のプリプレグ２
の自己接着性を利用して該プリプレグ２の表面に容易に
光ファイバー３を敷設することができるとともに、プリ
プレグ２が硬化後は、プリプレグ２本体と一体化される
ため光ファイバー３にはプリプレグ２に発生する損傷が
そのまま伝幡される。すなわち、前記光ファイバー３は
、構造安泰１の傷Ａで、構造要素ｌの本体とともに分断
されるため、第３図に示すように、光ファイバー３の一
端５から入光した光源Ｂ側の光は亀裂部分で漏光するこ
とになり、その状態を亀裂部分または他端６側で容易に
確認することができる。According to such an embodiment, the prepreg 2 before heat compression bonding
The optical fiber 3 can be easily laid on the surface of the prepreg 2 by utilizing the self-adhesive property of the prepreg 2. After the prepreg 2 is cured, the optical fiber 3 is integrated with the main body of the prepreg 2. The damage caused will be transmitted as is. That is, since the optical fiber 3 is separated along with the main body of the structural element 1 at the flaw A in the structural stability 1, the light from the light source B side entering from the one end 5 of the optical fiber 3 is transmitted through the crack, as shown in FIG. Light leaks at some portions, and the condition can be easily confirmed at the cracked portion or on the other end 6 side.
このため、構造要素ｌの内部等のように視認不可能ある
いは困難な部所の探傷も短時間にしかもＩＦｉ単に実施
することができる。Therefore, flaw detection of invisible or difficult parts such as the inside of the structural element 1 can be carried out in a short time and with simple IFi.
なお、本発明は前記実施例に限定されないのは勿論であ
り１例えば、前記実施例においては光ファイバー３を外
壁部材ｌの表面に一方向にのみ延設しているが、これを
プリプレグ２間に縦、横に配設すれば、さらに損傷部茅
の検索を確実に行うことができる。It should be noted that the present invention is of course not limited to the above-mentioned embodiment.1For example, in the above-mentioned embodiment, the optical fiber 3 is extended only in one direction on the surface of the outer wall member l, but it is possible to extend the optical fiber 3 between the prepregs 2. By arranging them vertically and horizontally, it is possible to more reliably search for damaged moss.
あるいは、第４図に示すように、光ファイバー３を外壁
部材ｌに埋設するとともに、その両端に発光素子Ｃと受
光素子りを配設しておけば、常時部材に生じる損傷を検
知することがＯｒ１＠となる（ｍ１図、第２図に相当す
る部分には同符吟を付して説明を省略する）、また、金
ｋｉｌ″Ｊの構造部材で内部に尤ファイバーを埋設し難
い場合は、その裏面笠に前記実施例のように尤ファイバ
ーを延設したプリプレグを貼り付けておけば部材の補強
とともに、損傷の検知にも太いに有効である。Alternatively, as shown in FIG. 4, if the optical fiber 3 is buried in the outer wall member L and a light emitting element C and a light receiving element are arranged at both ends, it is possible to constantly detect damage to the member. (The parts corresponding to Figure m1 and Figure 2 are marked with the same sign and the explanation is omitted.) Also, if it is difficult to embed the fiber inside the structural member of gold kil''J, If a prepreg with extended fibers is attached to the back of the cap as in the above embodiment, it will be very effective in reinforcing the member and also in detecting damage.
また本発明は航空機用の構茹要素に限らず、槽または室
の壁を４ＩＩ成する部材や構％部材などの構造部材一般
に適用口１能である。Furthermore, the present invention is applicable not only to structural elements for aircraft, but also to structural members in general, such as members forming walls of tanks or chambers, and structural members.
【発１ｊ＋の効果１
本発明は、以ヒのように損傷検知…の光ファイバーを表
面または内部に設けたものであるから、構ゐ°Ｊ／素に
発生する亀ｆｌＪ等の傷を簡便に検知することかでさる
ものである。[Effects of Irradiation 1j+ 1] Since the present invention is provided with an optical fiber for damage detection on the surface or inside as described below, it is possible to easily detect scratches such as tortoise flJ that occur naturally. It depends on what you do.
４図面の［１１１な説明
第１図は２本発明の一実施例を示す全体図、第２図は第
１図の部分拡大図、第３図は作用、悦明図、第４図は本
発明の他の実施例を示す図である。4. [111 Explanation of the Drawings] Figure 1 is an overall view showing an embodiment of the present invention, Figure 2 is a partially enlarged view of Figure 1, Figure 3 is a diagram of the operation, and Figure 4 is a diagram of the present invention. FIG. 7 is a diagram showing another embodiment of the invention.
ｌ・・・外壁部材 ２ ａ ｓ ＊プリプレグ３・・φ
光ファイバー
５・・φ投光側端部
６・・会堂光側端面l...Outer wall member 2 a s *Prepreg 3...φ
Optical fiber 5... φ light emission side end 6... Synagogue light side end surface
Claims (1)
機能を備えたことを特徴とする構造要素。A structural element characterized by having a flaw detection function by installing an optical fiber for flaw detection inside or on the surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7459986A JPS62231142A (en) | 1986-03-31 | 1986-03-31 | Structural element |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7459986A JPS62231142A (en) | 1986-03-31 | 1986-03-31 | Structural element |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62231142A true JPS62231142A (en) | 1987-10-09 |
Family
ID=13551776
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7459986A Pending JPS62231142A (en) | 1986-03-31 | 1986-03-31 | Structural element |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62231142A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2638526A1 (en) * | 1988-07-04 | 1990-05-04 | Westland Helicopters | METHOD AND APPARATUS FOR DETECTING CRACKS IN HELICOPTER ROTOR BLADES |
| EP0401153A2 (en) * | 1989-06-01 | 1990-12-05 | United Technologies Corporation | Fiber optic damage detection system |
| JP2002039950A (en) * | 2000-07-21 | 2002-02-06 | Ohbayashi Corp | Method for detecting gap of concrete |
| WO2018101374A1 (en) * | 2016-12-01 | 2018-06-07 | ヤマハ発動機株式会社 | Tilting vehicle |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56160644A (en) * | 1980-05-14 | 1981-12-10 | Fuji Electric Co Ltd | Detecting method for crack |
| JPS59114443A (en) * | 1982-12-21 | 1984-07-02 | Agency Of Ind Science & Technol | Method and apparatus for detecting crack of fragile material |
| JPS606853A (en) * | 1982-11-20 | 1985-01-14 | メツセルシユミツト−ベルコウ−ブロ−ム・ゲゼルシヤフト・ミツト・ベシユレンクテル・ハフトウング | Measuring device detecting crack |
-
1986
- 1986-03-31 JP JP7459986A patent/JPS62231142A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56160644A (en) * | 1980-05-14 | 1981-12-10 | Fuji Electric Co Ltd | Detecting method for crack |
| JPS606853A (en) * | 1982-11-20 | 1985-01-14 | メツセルシユミツト−ベルコウ−ブロ−ム・ゲゼルシヤフト・ミツト・ベシユレンクテル・ハフトウング | Measuring device detecting crack |
| JPS59114443A (en) * | 1982-12-21 | 1984-07-02 | Agency Of Ind Science & Technol | Method and apparatus for detecting crack of fragile material |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2638526A1 (en) * | 1988-07-04 | 1990-05-04 | Westland Helicopters | METHOD AND APPARATUS FOR DETECTING CRACKS IN HELICOPTER ROTOR BLADES |
| EP0401153A2 (en) * | 1989-06-01 | 1990-12-05 | United Technologies Corporation | Fiber optic damage detection system |
| JP2002039950A (en) * | 2000-07-21 | 2002-02-06 | Ohbayashi Corp | Method for detecting gap of concrete |
| WO2018101374A1 (en) * | 2016-12-01 | 2018-06-07 | ヤマハ発動機株式会社 | Tilting vehicle |
| TWI648189B (en) * | 2016-12-01 | 2019-01-21 | 日商山葉發動機股份有限公司 | Tilt vehicle |
| JPWO2018101374A1 (en) * | 2016-12-01 | 2019-10-24 | ヤマハ発動機株式会社 | Inclined vehicle |
| US11753099B2 (en) * | 2016-12-01 | 2023-09-12 | Yamaha Hatsudoki Kabushiki Kaisha | Leaning vehicle |
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