JPH05208465A - Sandwich panel - Google Patents
Sandwich panelInfo
- Publication number
- JPH05208465A JPH05208465A JP6266691A JP6266691A JPH05208465A JP H05208465 A JPH05208465 A JP H05208465A JP 6266691 A JP6266691 A JP 6266691A JP 6266691 A JP6266691 A JP 6266691A JP H05208465 A JPH05208465 A JP H05208465A
- Authority
- JP
- Japan
- Prior art keywords
- prepreg
- sandwich panel
- carbon fiber
- core material
- surface material
- 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.)
- Withdrawn
Links
Landscapes
- Laminated Bodies (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、サンドイッチパネルに
係わり、特に航空機の内装材、就中、床材用に好適なハ
ニカムサンドイッチパネルに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a sandwich panel, and more particularly to a honeycomb sandwich panel suitable for aircraft interior materials, especially floor materials.
【０００２】[0002]
【従来の技術】サンドイッチパネルはコアの両面に表面
材を重ね合わせ、接着して作られる成形体であるが、通
常、コア材としてはアルミニウムに代表される金属ハニ
カム、芳香族ポリアミド不織布から成形される有機繊維
製ハニカム、或いは紙を加工して得られるペーパーハニ
カム等のハニカム構造体と、ポリウレタンフォーム、フ
ェノールフォーム、各種ビニルフォーム等のフォーム構
造体がある。又、表面材としては、通常、ガラス繊維、
炭素繊維、アラミド繊維等を用いた繊維強化複合材料
や、アルミニウム、銅等の金属薄板が、単独、あるい
は、複合されて使用される。2. Description of the Related Art A sandwich panel is a molded product made by laminating surface materials on both sides of a core and adhering them to each other. Usually, the core material is molded from a metal honeycomb typified by aluminum or an aromatic polyamide nonwoven fabric. There are honeycomb structures such as organic fiber honeycombs or paper honeycombs obtained by processing paper, and foam structures such as polyurethane foam, phenol foam, and various vinyl foams. The surface material is usually glass fiber,
A fiber-reinforced composite material using carbon fiber, aramid fiber or the like, or a metal thin plate of aluminum, copper or the like is used alone or in combination.
【０００３】このように構成されるサンドイッチパネル
は、軽量、且つ強度、剛性に優れていることから、近
年、航空機、車輛、船舶等の輸送機器に使用され、軽量
化を行うことにより、燃料費の軽減を計ったり、また建
築分野においては、軽量化による建築物の高層化、およ
び工事の簡略化を目的に使用されている。Since the sandwich panel constructed as described above is lightweight and excellent in strength and rigidity, it has recently been used for transportation equipment such as aircrafts, vehicles, and ships, and has been reduced in weight to reduce fuel costs. In the construction field, it is used for the purpose of making buildings taller by reducing weight and simplifying construction.
【０００４】このようなサンドイッチパネルの強度、剛
性等はコア材の材質、密度、形状と、表面材の材質、厚
み等、および、コア材と表面材の接着力等により定ま
り、これらは各々の使用用途毎に、材料が適宜選択され
る。The strength and rigidity of such a sandwich panel are determined by the material, density and shape of the core material, the material and thickness of the surface material, the adhesive force between the core material and the surface material, and the like. The material is appropriately selected for each intended use.
【０００５】特に繊維強化複合材料を表面材に使用する
場合、繊維としては、性能面から長繊維が好んで用いら
れるが、主に繊維を一方向に引き揃えた一方向性プリプ
レグ（以下ＵＤプリプレグと略記する）および、織物プ
リプレグが単層あるいは、２層以上積層して使用され
る。特に、ＵＤプリプレグを使用する場合は方向によっ
てその性能が著しく異なることから、積層角を代えて繊
維が斜交するように２層以上を積層して用いられるのが
通常である。Particularly when a fiber-reinforced composite material is used as a surface material, long fibers are preferably used from the viewpoint of performance as the fibers, but mainly unidirectional prepregs (hereinafter referred to as UD prepregs) in which fibers are aligned in one direction. And a woven prepreg are used as a single layer or as a laminate of two or more layers. In particular, when a UD prepreg is used, its performance remarkably varies depending on the direction. Therefore, it is usually used by laminating two or more layers such that the laminating angle is changed and the fibers are obliquely crossed.
【０００６】また、航空機の床材用のサンドイッチパネ
ルには色々な特性が要求されるが、これらのうち、単位
重量あたりの力学的な特性、特に、引張、曲げ、および
衝撃特性は重要な特性である。従来は表面材に使用する
強化繊維は、価格の点で安価なガラス繊維が使用されて
きたが、近年、より軽量化の要望により、ガラス繊維よ
りも、比強度、比弾性率の優れた炭素繊維が使用される
ようになってきた。[0006] In addition, sandwich panels for aircraft flooring are required to have various properties. Among these, mechanical properties per unit weight, particularly tensile, bending and impact properties are important properties. Is. Conventionally, glass fiber, which is inexpensive in terms of price, has been used as the reinforcing fiber used for the surface material, but in recent years, due to the demand for lighter weight, carbon, which has better specific strength and specific elastic modulus than glass fiber Fiber has come into use.
【０００７】しかし通常、釣り竿や、ゴルフクラブ等に
使用されている高強度炭素繊維（引張強度ほぼ４００kg
f/mm2 ，破断伸度ほぼ１．５％）を航空機の床材用サン
ドイッチパネルに使用するには耐衝撃性が低く、この
為、サンドイッチパネルの表面材にガラスクロスや熱可
塑性のフィルム等を接合し、耐衝撃性の向上を行ってい
たが、これらのクロス材や、フィルムはサンドイッチパ
ネルの重量を重くするという欠点があった。However, high-strength carbon fibers (tensile strength of about 400 kg) that are usually used for fishing rods, golf clubs, etc.
f / mm 2 , breaking elongation of about 1.5%) has low impact resistance when used for sandwich panels for aircraft flooring. Therefore, glass cloth or thermoplastic film is used as the surface material of sandwich panels. However, these cloth materials and films have a drawback in that the weight of the sandwich panel is increased.
【０００８】[0008]
【発明が解決しようとする課題】従って本発明の目的と
する所は軽量且つ耐衝撃性に優れ、航空機の床材用とし
て特に好適なサンドイッチパネルを提供することにあ
る。SUMMARY OF THE INVENTION Therefore, an object of the present invention is to provide a sandwich panel which is light in weight and excellent in impact resistance and which is particularly suitable for aircraft flooring.
【０００９】[0009]
【課題を解決するための手段】本発明者らは、以上の課
題を解決するために、鋭意検討を行った結果、本発明を
成したもので、その要旨は、コア材と表面材から構成さ
れるパネルにおいて表面材に繊維が斜交する一対以上の
一方向性炭素繊維プリプレグからなる炭素繊維強化プラ
スチックを使用し、且つ該炭素繊維の使用量の少なくと
も２５％以上が、引張強度４００kgf/mm2 以上引張り破
断時の伸度が１．７％以上の炭素繊維であり、さらにコ
ア材として芳香族ポリアミド不織布から形成されたハニ
カムを使用することを特徴とするサンドイッチパネルに
ある。Means for Solving the Problems The inventors of the present invention have made extensive studies in order to solve the above problems, and as a result, the present invention has been achieved. The gist of the present invention is to construct a core material and a surface material. In the panel to be used, a carbon fiber reinforced plastic comprising a pair of unidirectional carbon fiber prepregs in which fibers are obliquely crossed is used as a surface material, and at least 25% or more of the amount of the carbon fiber used has a tensile strength of 400 kgf / mm. 2 or more tensile elongation at break is 1.7% or more of carbon fibers, in a sandwich panel, characterized by the use of which is formed from a further aromatic polyamide nonwoven as a core material a honeycomb.
【００１０】以下本発明を詳細に説明する。まず本発明
に用いられる表面材に使用される炭素繊維は、全使用量
のうち、少なくとも２５％以上が引張強度４００kgf/mm
2 以上, 引張り破断時の伸度が１．７％以上の炭素繊維
である必要がある。The present invention will be described in detail below. First, in the carbon fiber used in the surface material used in the present invention, at least 25% or more of the total amount used has a tensile strength of 400 kgf / mm.
The carbon fiber must have a tensile strength of 2 or more and an elongation at break of 1.7% or more.
【００１１】この場合、引張強度４００kgf/mm2 以上,
引張り破断時の伸度が１．７％以上の炭素繊維が２５％
未満であると、耐衝撃性が低く、耐衝撃性を向上させる
ためにサンドイッチパネルの表面に各種のクロス、ある
いは各種のフィルムを必要とし、これによりサンドイッ
チパネルの重量が増加するという点で好ましくない。In this case, the tensile strength is 400 kgf / mm 2 or more,
25% carbon fiber with an elongation at break of 1.7% or more
When it is less than 1, the impact resistance is low, and various cloths or various films are required on the surface of the sandwich panel in order to improve the impact resistance, which is not preferable in that the weight of the sandwich panel is increased. ..
【００１２】又、この炭素繊維強化プラスチックのマト
リックスとなる樹脂は熱硬化性樹脂としては、本発明パ
ネルの使用用途が航空機の内装材であることを考慮し
て、燃焼特性に優れたエポキシ樹脂、フェノール樹脂等
が挙げられる。又、熱可塑性樹脂に関しては、同様に、
本発明パネルの使用用途が航空機の内装材であることを
考慮して、燃焼特性に優れた、ポリエーテルイミド、ポ
リエーテルエーテルケトン等が挙げられる。The thermosetting resin used as the matrix of the carbon fiber reinforced plastic is an epoxy resin having excellent combustion characteristics, considering that the panel of the present invention is used as an interior material for aircraft. Examples thereof include phenolic resins. Further, regarding the thermoplastic resin, similarly,
Considering that the intended use of the panel of the present invention is an aircraft interior material, polyetherimide, polyetheretherketone and the like, which have excellent combustion characteristics, can be mentioned.
【００１３】又、これらの樹脂は、その特性を向上させ
る為に、１種あるいは２種以上を組合わせて使用しても
良く、また他の改質材、難燃材、変性材等を添加しても
良い。These resins may be used alone or in combination of two or more in order to improve their properties, and other modifiers, flame retardants, modifiers, etc. are added. You may.
【００１４】これとは別に、サンドイッチパネルの特性
を向上させるために、例えば、耐摩耗性を向上させるた
めに、必要に応じてパネルの表面に各種のフィルム、例
えば、ポリふっ化ビニル、ポリエーテルイミド、ナイロ
ン等や、各種の織物、例えば、ガラス繊維織物、炭素繊
維織物、アラミド繊維織物、ポリエーテルエーテルケト
ン繊維織物、或いは、アルミニウム箔、銅箔等の金属箔
等を併用しても良い。Apart from this, in order to improve the properties of the sandwich panel, for example, to improve the abrasion resistance, various films are optionally formed on the surface of the panel, for example, polyvinyl fluoride and polyether. It is also possible to use imide, nylon and the like, and various woven fabrics such as glass fiber woven fabric, carbon fiber woven fabric, aramid fiber woven fabric, polyether ether ketone fiber woven fabric, and metal foil such as aluminum foil and copper foil.
【００１５】また本発明においては、コア材として芳香
族ポリアミド不織布から成形されたハニカムを使用し、
これに前記表面材を接着してパネルとして構成されるも
のであるが、ここでいう芳香族ポリアミド不織布とは、
例えばデュポン社製のノーメックスの如きアラミド繊維
不織布を紙状にしたもので、これをハニカム状に加工し
たのち、フェノール樹脂を含浸させ、コア材（例えば昭
和飛行機工業（株）製ノーメックスハニカム）として使
用するものである。In the present invention, a honeycomb formed from an aromatic polyamide nonwoven fabric is used as the core material,
The surface material is adhered to this to form a panel, and the aromatic polyamide nonwoven fabric here means
For example, a paper-shaped aramid fiber non-woven fabric such as DuPont Nomex is processed into a honeycomb shape, which is then impregnated with phenol resin and used as a core material (for example, Showa Aircraft Industry Co., Ltd. Nomex honeycomb). To do.
【００１６】この場合、金属ハニカム或いはペーパーハ
ニカムを本発明で使用しない理由は、金属ハニカムで
は、航空機の内装材に使用した場合、長年の使用中にお
いて、金属ハニカムが腐食するためであり、又、ペーパ
ーハニカムを使用をすると、難燃性の点で問題があるた
めである。In this case, the reason why the metal honeycomb or the paper honeycomb is not used in the present invention is that, when the metal honeycomb is used as an interior material of an aircraft, the metal honeycomb is corroded during many years of use, and This is because the use of paper honeycomb has a problem in flame retardancy.
【００１７】また、本発明のコア材となるハニカム構造
体とは、一般に平断面が六角形状の筒を組み合わせた蜂
の巣状の板状物を指すが、本発明においてはその断面は
六角形でない他の三角、四角、五角、七角、八角等の多
角形でも又円形、不定形でも良く、特にその形状は限定
しないが、好ましくは、その筒の直径は２〜１０ｍｍ
で、筒側面の厚みは０．０１〜１．０ｍｍで、筒の高さ
は５〜５０ｍｍである。The honeycomb structure serving as the core material of the present invention generally refers to a honeycomb-shaped plate-like product in which cylinders having a flat cross section of hexagon are combined, but in the present invention, the cross section is not hexagonal. The polygon may be a polygon such as a triangle, a square, a pentagon, a heptagon, and an octagon, or a circle or an indeterminate shape. The shape is not particularly limited, but the diameter of the cylinder is preferably 2 to 10 mm.
The thickness of the side surface of the cylinder is 0.01 to 1.0 mm, and the height of the cylinder is 5 to 50 mm.
【００１８】なお表面材とコア材を接着する場合の方法
については特に制限は無く、接着剤を用いて接着して
も、またＵＤプリプレグ中に含有される樹脂により接着
しても問題は無く、成形方法についても、加熱加圧成形
法、オートクレーブ成形法、真空バッグ成形法等の如何
なる成形方法を用いて、成形してもよい。There is no particular limitation on the method of adhering the surface material and the core material, and there is no problem even if they are adhered by using an adhesive or by the resin contained in the UD prepreg. As for the molding method, any molding method such as a heat and pressure molding method, an autoclave molding method, a vacuum bag molding method or the like may be used.
【００１９】[0019]
【実施例】以下実施例により、本発明をさらに詳述す
る。尚、以下に示した実施例の各値は以下の方法に従い
測定した。The present invention will be described in more detail with reference to the following examples. Each value in the examples shown below was measured according to the following methods.
【００２０】（１）衝撃強度 図１に示したように、１００ｍｍ角のサンドイッチパネ
ル試験片ａに接した直径１４φの曲率を持つ重量９０８
ｇの圧子ｂに、２ポンドの重量を持つ落下体ｃを高さを
変化させて落下させ、そのときの衝撃エネルギーを（２
ポンド×落下体の高さ）で表した。衝撃強度は、落下後
にサンドイッチパネルの表面を観察し、ＵＤプリプレグ
の繊維が破断しない最大衝撃エネルギーを目視にて判断
した。(1) Impact strength As shown in FIG. 1, a weight 908 having a curvature of 14φ in diameter and in contact with a 100 mm square sandwich panel test piece a.
A falling body c having a weight of 2 pounds is dropped onto the indenter b of g by changing the height, and the impact energy at that time is (2
It is expressed in pounds x height of falling body. For the impact strength, the surface of the sandwich panel was observed after dropping, and the maximum impact energy at which the fibers of the UD prepreg were not broken was visually determined.
【００２１】（２）曲げ強度 幅５０ｍｍ，長さ６１０ｍｍのサンドイッチパネル試験
片ａを図２に示したように上部スパン２５４ｍｍ、下部
スパン５０８ｍｍのスパン長にて、４点支持し、クロス
ヘッドスピード２５．４ｍｍ／ｍｉｎにて４点曲げ試験
を行った。変位量の測定は試験片中央部のノギス測定に
より行った。(2) Bending strength A sandwich panel test piece a having a width of 50 mm and a length of 610 mm was supported at four points with an upper span of 254 mm and a lower span of 508 mm as shown in FIG. A 4-point bending test was performed at 0.4 mm / min. The displacement amount was measured by measuring the caliper of the central portion of the test piece.
【００２２】（実施例１）Ｈｉ−ＣＡＲＢＯＲＯＮ（旭
化成社製炭素繊維；引張強度４００kgf/mm2 ，引張破断
伸度１．５％）とマグナマイト（ＩＭ−６Ｇ、住友化学
社製、引張強度５１０kgf/mm2 、引張破断伸度１．７８
％）の２種類の炭素繊維をそれぞれフェノール樹脂（新
日鐵化学社製；ＰＲ−２２０）に含浸させ、炭素繊維目
付け７５g/m2，樹脂含有率３７ｗｔ％の２種類の一方向
性プリプレグを製造した。以下の説明ではＨｉ−ＣＡＲ
ＢＯＲＯＮを用いたプリプレグをプリプレグ（ａ）、マ
グナマイトを用いたプリプレグをプリプレグ（ｂ）と便
宜上きめた。これら２種類のプリプレグを用い、コア材
側から順に、プリプレグ（ａ）／プリプレグ（ａ）／プ
リプレグ（ａ）／プリプレグ（ｂ）の順で０°／９０°
／９０°／０°方向に４層積層したのち、このプリプレ
グの両側にガラス繊維織物（ＫＳ−５３７０：鐘紡
（株）製 平織り）を重合わせたものを表面材とし、オ
ートクレーブにて、１４０℃で１時間、１７０℃で１時
間、面圧、３kgf/cm2 ＋真空圧下で成形を行った。得ら
れた表面材とノーメックスハニカム（ＳＡＨ−１／８−
４．０ 昭和飛行機工業（株）製）を合わせ、プレス成
形法にて、１４０℃、７kgf/cm2 にて２時間成形を行
い、サンドイッチパネルを成形した。得られたサンドイ
ッチパネルから、各々、衝撃特性、曲げ強度用の試験片
を切出し評価を行った。(Example 1) Hi-CARBORON (carbon fiber manufactured by Asahi Kasei; tensile strength 400 kgf / mm 2 , tensile breaking elongation 1.5%) and magnamite (IM-6G, manufactured by Sumitomo Chemical Co., Ltd., tensile strength 510 kgf / mm 2 , tensile elongation at break 1.78
%) Two kinds of carbon fibers are impregnated into phenol resin (PR-220 manufactured by Nippon Steel Chemical Co., Ltd.) respectively, and two kinds of unidirectional prepregs having a carbon fiber basis weight of 75 g / m 2 and a resin content of 37 wt% are prepared. Manufactured. In the following description, Hi-CAR
The prepreg using BORON is defined as prepreg (a), and the prepreg using magnamite is defined as prepreg (b) for convenience. Using these two types of prepregs, the prepreg (a) / prepreg (a) / prepreg (a) / prepreg (b) are sequentially 0 ° / 90 ° from the core material side.
After laminating 4 layers in the direction of / 90 ° / 0 °, a glass fiber woven fabric (KS-5370: plain weave manufactured by Kanebo Co., Ltd.) was superposed on both sides of this prepreg as a surface material, and it was autoclaved at 140 ° C. Molding was carried out for 1 hour at 170 ° C. for 1 hour under a surface pressure of 3 kgf / cm 2 + vacuum pressure. The obtained surface material and Nomex honeycomb (SAH-1 / 8-
4.0 Showa Aircraft Industry Co., Ltd. was combined and molded by a press molding method at 140 ° C. and 7 kgf / cm 2 for 2 hours to form a sandwich panel. From the obtained sandwich panel, test pieces for impact property and bending strength were cut out and evaluated.
【００２３】（比較例１）実施例１に使用したプリプレ
グ（ｂ）をプリプレグ（ａ）に変えた以外は実施例１と
全く同条件下でサンドイッチパネルを作成し、評価を行
った。Comparative Example 1 A sandwich panel was prepared and evaluated under exactly the same conditions as in Example 1 except that the prepreg (b) used in Example 1 was changed to prepreg (a).
【００２４】（実施例２）実施例１に使用した表面材の
構成を、コア材から順に、プリプレグ（ａ）／プリプレ
グ（ａ）／プリプレグ（ｂ）／プリプレグ（ｂ）に変え
た以外は、実施例１と全く同条件下でサンドイッチパネ
ルを作成し、評価を行った。(Example 2) The constitution of the surface material used in Example 1 was changed to prepreg (a) / prepreg (a) / prepreg (b) / prepreg (b) in order from the core material. A sandwich panel was prepared under the same conditions as in Example 1 and evaluated.
【００２５】（実施例３）実施例１に使用した表面材の
構成を、コア材から順に、プリプレグ（ａ）／プリプレ
グ（ｂ）／プリプレグ（ｂ）／プリプレグ（ｂ）に変え
た以外は、実施例１と全く同条件下でサンドイッチパネ
ルを作成し、評価を行った。(Example 3) The constitution of the surface material used in Example 1 was changed to prepreg (a) / prepreg (b) / prepreg (b) / prepreg (b) in order from the core material. A sandwich panel was prepared under the same conditions as in Example 1 and evaluated.
【００２６】（実施例４）実施例１に使用した表面材の
構成を、コア材から順に、プリプレグ（ｂ）／プリプレ
グ（ｂ）／プリプレグ（ｂ）／プリプレグ（ｂ）に変え
た以外は、実施例１と全く同条件下でサンドイッチパネ
ルを作成し、評価を行った。(Example 4) The composition of the surface material used in Example 1 was changed to prepreg (b) / prepreg (b) / prepreg (b) / prepreg (b) in order from the core material. A sandwich panel was prepared under the same conditions as in Example 1 and evaluated.
【００２７】（比較例２）比較例１に使用したガラス繊
維織物（ＫＳ−５３７０：鐘紡（株）製 平織り）をプ
リプレグの両面に２層ずつ重ね合わせた以外は比較例１
と同様にサンドイッチパネルを作成し、評価を行った。(Comparative Example 2) Comparative Example 1 except that two layers of the glass fiber woven fabric (KS-5370: plain weave manufactured by Kanebo Co., Ltd.) used in Comparative Example 1 were laminated on both sides of the prepreg.
A sandwich panel was prepared and evaluated in the same manner as in.
【００２８】[0028]
【表１】 [Table 1]
【００２９】[0029]
【発明の効果】本発明によれば、特に航空機の床材用と
して優れた軽量且つ高耐衝撃性のサンドイッチパネルを
提供することが可能となるものであり、実用上の効果は
極めて顕著である。According to the present invention, it is possible to provide a lightweight and highly impact-resistant sandwich panel especially for aircraft flooring, and the practical effect is extremely remarkable. ..
【００３０】[0030]
【図１】実施例に用いられた衝撃強度の測定手段を示す
模式図である。FIG. 1 is a schematic view showing an impact strength measuring means used in Examples.
【図２】実施例に用いられた曲げ特性の測定条件を示す
模式図である。FIG. 2 is a schematic diagram showing measurement conditions of bending characteristics used in Examples.
ａ サンドイッチパネル試験片 ｂ 圧子 ｃ 落下体 a Sandwich panel test piece b Indenter c Falling body
Claims (1)
において表面材に繊維が斜交する一対以上の一方向性炭
素繊維プリプレグからなる炭素繊維強化プラスチックを
使用し、且つ該炭素繊維の使用量の少なくとも２５％以
上が、引張強度４００kgf/mm2 以上、引張り破断時の伸
度が１．７％以上の炭素繊維であり、さらに、コア材と
して芳香族ポリアミド不織布から成形されたハニカムを
使用することを特徴とするサンドイッチパネル。1. A carbon fiber reinforced plastic comprising a pair of unidirectional carbon fiber prepregs having fibers obliquely intersecting with a surface material in a panel comprising a core material and a surface material, and the use of the carbon fiber. At least 25% or more of the amount is carbon fiber having a tensile strength of 400 kgf / mm 2 or more and an elongation at tensile rupture of 1.7% or more, and a honeycomb formed from an aromatic polyamide nonwoven fabric is used as a core material. A sandwich panel characterized by being.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6266691A JPH05208465A (en) | 1991-03-04 | 1991-03-04 | Sandwich panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6266691A JPH05208465A (en) | 1991-03-04 | 1991-03-04 | Sandwich panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05208465A true JPH05208465A (en) | 1993-08-20 |
Family
ID=13206848
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP6266691A Withdrawn JPH05208465A (en) | 1991-03-04 | 1991-03-04 | Sandwich panel |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH05208465A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11300870A (en) * | 1998-04-20 | 1999-11-02 | Mitsubishi Rayon Co Ltd | Sandwich board made of fiber reinforced plastic |
| EP1167020A3 (en) * | 2000-06-27 | 2002-04-10 | Sakura Rubber Co., Ltd. | Honeycomb sandwich panel |
| KR100769848B1 (en) * | 2006-08-29 | 2007-10-25 | 국방과학연구소 | Method to increase adhesive strength for metal tube and carbon fiber/epoxy resin layer and thereof increasing structure |
| JP2007312269A (en) * | 2006-05-22 | 2007-11-29 | Kyocera Chemical Corp | Diaphragm for planar speaker and planar speaker using the same |
| JP2008230235A (en) * | 2007-02-22 | 2008-10-02 | Toray Ind Inc | Sandwich structure and molded product using it, and electronic instrument casing |
| JP2009000933A (en) * | 2007-06-22 | 2009-01-08 | Jamco Corp | Sandwich panel |
| JP2012126387A (en) * | 2010-12-13 | 2012-07-05 | Boeing Co:The | Improved, green aircraft interior panel |
| JP2016520458A (en) * | 2013-06-06 | 2016-07-14 | ル ストラティフィース | Composite panel for floor or wall covering parts and method for manufacturing such a panel |
| WO2019030740A1 (en) * | 2017-08-11 | 2019-02-14 | Fibre Reinforced Thermoplastics B.V. | Fiber-reinforced laminates and sandwich composites including the same |
-
1991
- 1991-03-04 JP JP6266691A patent/JPH05208465A/en not_active Withdrawn
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11300870A (en) * | 1998-04-20 | 1999-11-02 | Mitsubishi Rayon Co Ltd | Sandwich board made of fiber reinforced plastic |
| EP1167020A3 (en) * | 2000-06-27 | 2002-04-10 | Sakura Rubber Co., Ltd. | Honeycomb sandwich panel |
| JP2007312269A (en) * | 2006-05-22 | 2007-11-29 | Kyocera Chemical Corp | Diaphragm for planar speaker and planar speaker using the same |
| KR100769848B1 (en) * | 2006-08-29 | 2007-10-25 | 국방과학연구소 | Method to increase adhesive strength for metal tube and carbon fiber/epoxy resin layer and thereof increasing structure |
| JP2008230235A (en) * | 2007-02-22 | 2008-10-02 | Toray Ind Inc | Sandwich structure and molded product using it, and electronic instrument casing |
| JP2009000933A (en) * | 2007-06-22 | 2009-01-08 | Jamco Corp | Sandwich panel |
| JP4699425B2 (en) * | 2007-06-22 | 2011-06-08 | 株式会社ジャムコ | Sandwich panel |
| US8334042B2 (en) | 2007-06-22 | 2012-12-18 | Jamco Corporation | Sandwich panel |
| JP2012126387A (en) * | 2010-12-13 | 2012-07-05 | Boeing Co:The | Improved, green aircraft interior panel |
| JP2016520458A (en) * | 2013-06-06 | 2016-07-14 | ル ストラティフィース | Composite panel for floor or wall covering parts and method for manufacturing such a panel |
| WO2019030740A1 (en) * | 2017-08-11 | 2019-02-14 | Fibre Reinforced Thermoplastics B.V. | Fiber-reinforced laminates and sandwich composites including the same |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7087296B2 (en) | Energy absorbent laminate | |
| US4983433A (en) | Fiber reinforced plastic and its reinforcement | |
| RU2383440C2 (en) | Elastic metal composite material, reinforced with fibres, having lamellar structure and having high impact resistance | |
| EP0312151B1 (en) | Laminate of metal sheets and continuous glass filaments-reinforced synthetic material | |
| KR102006511B1 (en) | Composite laminate having improved impact strength and the use thereof | |
| US5460865A (en) | Hybrid honeycomb sandwich panel | |
| EP2006464B1 (en) | Sandwich panel | |
| JP4278677B2 (en) | Sandwich panel | |
| JP2012139841A (en) | Fiber reinforced resin composite material | |
| JPH05208465A (en) | Sandwich panel | |
| US6228473B1 (en) | Fiber-reinforced composite materials | |
| JPH0575575B2 (en) | ||
| JPS6384932A (en) | Laminated panel | |
| US3755059A (en) | High impact strength in graphite fiber laminates | |
| JPH04276435A (en) | Sandwich panel | |
| JP5426458B2 (en) | Glass long fiber cloth resin impregnated sheet for tatami core material composition, multilayer glass long fiber cloth resin impregnated sheet for tatami core material composition, tatami core material, and tatami mat | |
| JPH07329199A (en) | Cylindrical molding of fiber-reinforcing composite material | |
| JPH0872200A (en) | Composite molding | |
| CN209869584U (en) | Light high-strength unidirectional carbon fiber laminated board | |
| JPH0768679A (en) | Impact-resistant laminated structure | |
| JPH09226039A (en) | Fiber-reinforced plastic member | |
| US20100047549A1 (en) | Ballistic Material with Enhanced Polymer Matrix and Method for Production Thereof | |
| JP3326984B2 (en) | Organic fiber reinforced resin material | |
| WO2024176998A1 (en) | Frp | |
| JP3179971B2 (en) | Composite molding |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 19980514 |