JP2020097404A - 一体的な補強パネルを含む複合材料からなるマルチリブウィングボックス(multi−ribbed wing box)を製造する方法 - Google Patents
一体的な補強パネルを含む複合材料からなるマルチリブウィングボックス(multi−ribbed wing box)を製造する方法 Download PDFInfo
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- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Abstract
Description
Claims (16)
- a1)硬化表面(22)に、第1側(16’)を有するスキン(16)と縦方向(x)に平行に延びる複数のストリンガー(18)とを備える、複合材料の第1パネル(12a)を配置するステップと、
a2)それぞれがプレート(15)、第1フランジ対(15a)、及び第2フランジ対(15b)を備え、各フランジ対(15a,15b)が前記プレート(15)の両端に配置されている、重合していない複合材料の複数のリブ(14)を提供するステップと、
a3)第1側面(25)と、前記第1側面(25)に対向する第2側面(27)とを有し、中央部品(24a)、底部部品(24b)、及び頂部部品(24c)を備え、前記中央部品(24a)は、前記底部部品(24b)と前記頂部部品(24c)との間に差し込まれており、横方向(y)に引き抜くことができる、少なくとも1つの工具(24)を提供するステップと、
b)前記第1パネル(12a)の前記第1側(16’)上に前記第1フランジ対(15a)が設置されるリブ(14)と、工具(24)とを、連続したリブ(14)の各組の間で前記工具(24)が両方のリブ(14)に接するように、横方向(y)に沿って前記第1パネル(12a)の前記第1側(16’)上に、交互に配置するステップと、
c)第1側(16’)を有するスキン(16)と、縦方向(x)に沿って延びる複数のストリンガー(18)とを備える、複合材料の第2パネル(12b)を、前記第2パネル(12b)を各リブ(14)の前記第2フランジ対(15b)に接して置くことで、配置するステップと、
d)横方向(y)に沿って、各工具(24)の前記中央部品(24a)を引き抜き、続けて、各工具(24)の前記頂部部品(24c)と前記底部部品(24b)を取り除くステップと、
e)重合していない要素を硬化するための特定の圧と温度のサイクルによる、真空バッグによるオートクレーブでの硬化工程を、前記第1パネル(12a)、前記第2パネル(12b)、及び各リブ(14)に受けさせるステップと、
を備える、航空機用のウィングボックス(10)を製造するための方法。 - f)手順c)の前に、さらなる一対の工具(24)を、前記第1パネル(12a)の前記第1側(16’)上に、最初と最後のリブ(14)にそれぞれ接して外側に提供するステップ、
をさらに備える、請求項1のいずれかに記載の方法。 - g1)第1側面(25)が下になるように、第1工具(24)を配置するステップと、
g2)前記工具(24)の前記第2外側面(27)上に前記プレート(15)が配置されるリブ(14)と、工具(24)とを、連続したリブ(14)の各組の間で前記工具(24)が両方のリブ(14)に接するように、交互に配置するステップと、
g3)各第1フランジ対(15a)が前記第1パネル(12a)の前記第1側(16’)に載るように、前記第1パネル(12a)の前記第1側(16’)上にリブ(14)と工具(24)のアッセンブリーを配置するために、前記アッセンブリーを回転させるステップと、
を手順b)の前にさらに備える、請求項1に記載の方法。 - 前記第1パネル(12a)は重合した複合材料から成り、
f1)手順b)の前に、各リブ(14)の各第1フランジ対(15a)と前記第1パネル(12a)の前記第1側(16’)との間に、高温構造用粘着剤であるそれぞれのプライを配置するステップ、
をさらに備える、請求項1から3のいずれかに記載の方法。 - 前記第2パネル(12b)は既に重合した複合材料から成り、
f2)手順c)の前に、各リブ(14)の各第2フランジ対(15b)と前記第2パネル(12b)の前記第1側(16’)との間に、高温構造用粘着剤であるそれぞれのプライを配置するステップ、
をさらに備える、請求項1から4のいずれかに記載の方法。 - f3)手順c)の前に、各リブ(14)の各第2フランジ対(15b)と前記第2パネル(12b)の前記第1側(16’)との間に、それぞれの高温離型プライを配置するステップ、
をさらに備える、請求項1から4のいずれかに記載の方法。 - 前記第1パネル(12a)及び/又は前記第2パネル(12b)の前記複数のストリンガー(18)が重合していない複合材料から成り、
h1)手順a1)の前に、中実断面の細長い安定化インサート(17)を、各ストリンガー(18)と前記第1又は第2パネル(12a,12b)のそれぞれとの間で画定された空間に配置するステップと、
h2)手順e)の後に、前記細長い安定化インサート(17)を取り除くステップと、
をさらに備える、請求項1から6のいずれかに記載の方法。 - 前記細長い安定化インサート17は、ベーシックVMQエラストマーのグループのゴム(つまり、ISO 1629による、Qグループの、ビニル−メチル−ポリシロキサン)から成る、請求項7に記載の方法。
- 前記第1パネル(12a)、前記第2パネル(12b)、及び前記複数のリブ(14)の中の少なくとも1つの複合材料が、熱硬化性又はビスマレイミド樹脂マトリックス、及び/又は、炭素及び/又はガラス繊維強化材を備える、請求項1から8のいずれかに記載の方法。
- m)手順b)の前に、硬化バッグで各工具(24)を覆うステップ、
をさらに備える、請求項1から9のいずれかに記載の方法。 - 各リブ(14)が、前記第1パネル(12a)及び/又は前記第2パネル(12b)のそれぞれの強化ストリンガー(18)に対応して配置されている開口(14’)を有する、請求項1から10のいずれかに記載の方法。
- n)オートクレーブでの硬化工程の特定の圧と温度に耐えるようなプラスチック素材から成る補助インサート(20)を、前記補強用ストリンガー(18)のそれぞれに接して、各リブ(14)の各開口(14’)に提供するステップ、
を備える、請求項11に記載の方法。 - p)手順d)の前に、各工具(24)の前記底部部品(24b)、前記中央部品(24a)、及び前記頂部部品(24c)の中の少なくとも2つを相互に固定するのに適している着脱可能な拘束要素(32)を、各工具(24)から取り除くステップ、
をさらに備える、請求項1から12のいずれかに記載の方法。 - 各工具(24)の中央部品(24a)が、横方向(y)に沿ってテーパー部を有する、請求項1から13のいずれかに記載の方法。
- 各工具(24)が、1.7g/cm3以下の質量密度を有する素材から成り、曲げ歪が各メートルに対して1mm以内に制限されるような曲げ剛性を有する形状である、請求項1から14のいずれかに記載の方法。
- 各工具(24)の前記中央部品(24a)、前記頂部部品(24c)、及び前記底部部品(24b)の中の少なくとも1つが、容易な取り扱いに適した面取り(34)を有する、請求項1から15のいずれかに記載の方法。
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IT102018000010328A IT201800010328A1 (it) | 2018-11-14 | 2018-11-14 | Procedimento per la fabbricazione di un cassone multi-centina in materiale composito con pannelli irrigiditi integrati |
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CN113844672B (zh) * | 2020-06-28 | 2023-04-11 | 航天特种材料及工艺技术研究所 | 一种复合材料无人机垂尾的装配型架及其装配方法 |
CN114193789B (zh) * | 2021-12-01 | 2023-06-27 | 长春长光宇航复合材料有限公司 | 一种加纵向加强筋、环框复合材料壳体一体成型制备方法 |
CN114919210A (zh) * | 2022-04-22 | 2022-08-19 | 南京聚隆复合材料技术有限公司 | 一种复合材料机翼骨架的成型方法 |
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EP2889214B1 (en) * | 2013-12-31 | 2020-02-05 | Airbus Operations, S.L. | Highly integrated infused box made of composite material and method of manufacturing |
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CN111186591A (zh) | 2020-05-22 |
IT201800010328A1 (it) | 2020-05-14 |
BR102019024083A2 (pt) | 2020-06-02 |
US11292577B2 (en) | 2022-04-05 |
ES2887823T3 (es) | 2021-12-28 |
EP3653371A1 (en) | 2020-05-20 |
CA3059852A1 (en) | 2020-05-14 |
JP7412136B2 (ja) | 2024-01-12 |
US20200148328A1 (en) | 2020-05-14 |
EP3653371B1 (en) | 2021-07-28 |
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