JP7231392B2 - 衝撃損傷耐性を改善するための層間波形を有する積層複合構造体、ならびにそれを形成するシステムおよび方法 - Google Patents
衝撃損傷耐性を改善するための層間波形を有する積層複合構造体、ならびにそれを形成するシステムおよび方法 Download PDFInfo
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- B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
- B29K2995/0037—Other properties
- B29K2995/0089—Impact strength or toughness
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
- B32B2260/023—Two or more layers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/54—Yield strength; Tensile strength
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/558—Impact strength, toughness
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
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- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
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- 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
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- 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
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Description
実施例
11 積層複合試験クーポン
12 ビークル
12a 航空機
14 胴体
16 ノーズ
18 翼部
20 エンジン
22 尾翼
24 水平スタビライザ
26 垂直スタビライザ
28 積層複合仕上げ部品
28a 積層複合ブレードストリンガ
28b 積層複合スキンパネル
28c 積層複合スパー
28d 積層複合飛行制御面
30 航空機の製造および保守点検方法
32 仕様および設計
34 材料調達
36 構成要素および部分組立品の製造
38 システム統合
40 認証および搬送
42 就航、就航中
44 整備および保守点検
46 航空機
48 機体
50 システム
52 内部
54 推進システム
56 電気システム
58 油圧システム
60 環境システム
62 航空機翼部パネル
62a 航空機複合翼部パネル
64 翼端
65 中央翼部ボックス
66 ストリンガ
66a ブレードストリンガ
66b ハットストリンガ
68 下面
70 スキンパネル
70a 上側スキンパネル
70b 下側スキンパネル
72 スパー
72a 前方スパー
74 内部取り付け位置
76 ウェブ
76a 第1のウェブ部分
76b 第2のウェブ部分
78 基部
80 露出した縁部
80a 露出した垂直外側縁部
82 フランジ
82a 第1のフランジ部分
82b 第2のフランジ部分
84 下側基部部分
86 フィラー部分
88 衝撃力
88a 衝撃力
88b 衝撃力
90 衝撃箇所
92 積層されたプライ層
94 衝撃損傷領域
96 長さ
98 深さ
100 層間波形
100a 大きい層間波形
100b 中程度の層間波形
100c 小さい層間波形
101 実質的に正弦波形状の輪郭
102 複数の積層された層
102a 第1の複数の積層された層
102b 第2の複数の積層された層
102c 第3の複数の積層された層
103 サイズ
104 縁部被覆
106 複合材料
107 繊維材料
108 樹脂材料
109 ピークと谷部分
110 ピーク
112 谷
112a 第1の谷部分
112b 第2の谷部分
114 深さ
114a ピーク高さ
116 長さ
116a 歪み長
117 幅
118a 第1の接点
118b 第2の接点
119 所定の比(L/D)
120 積層体アセンブリ
121 対向する側面
121a 第1の側面
121b 第2の側面
122 積層体
122a 第1の積層体
122b 第2の積層体
124 積層体半部
126a 第1の側面
126b 第1の側面
128a 第2の側面
128b 第2の側面
130a 第1の端部
130b 第2の端部
132a 第1の側端部
132b 第2の側端部
133 積層構成
134 ギャップ要素
134a 第1のギャップ要素
134b 第2のギャップ要素
135 積層シム
136 複数の積層された層
136a 第1の複数の積層された層
136b 第2の複数の積層された層
138a 第1の側面
138b 第1の側面
140a 第2の側面
140b 第2の側面
142a 第1の端部
142b 第2の端部
144a 第1の側端部
144b 第2の側端部
145 ギャップ領域
146 長手方向縁部
147a 第1の長手方向縁部
147b 第2の長手方向縁部
148a 第1の長手方向縁部
148b 第2の長手方向縁部
150 ツールプレート
150a 第1のツールプレート
150b 第2のツールプレート
151 コールプレート
152a 第1の側面
152b 第1の側面
154a 第2の側面
154b 第2の側面
156a 第1の端部
156b 第2の端部
158a 第1の側端部
158b 第2の側端部
160 エンドプレート
160a 第1のエンドプレート
160b 第2のエンドプレート
161 アルミニウムバー
162a 上面
162b 上面
164a 底面
164b 底面
166a 第1の端部
166b 第2の端部
168a 第1の側面
168b 第2の側面
170 フィルム層
170a 第1のフィルム層
170b 第2のフィルム層
171 フッ素化エチレンプロピレン(FEP)フィルム層
172 システム
174 加圧システム
174a 真空シールシステム
175 真空バッグアセンブリ
176 ブリーザ材料層
176a 第1のブリーザ材料層
176b 第2のブリーザ材料層
178 真空バッグフィルム
178a ナイロンフィルム
180 シーラント材料
180a シーラントテープ
182 平坦な表面装置
182a テーブル
183 真空ポンプアセンブリ
184 真空ポート
184a 第1の真空ポート
184b 第2の真空ポート
186 真空ライン
188 トラップ部材
190 ゲージ部材
192 制御バルブ
194 真空ポンプ
196 高圧領域
198 低圧領域
200 改善された衝撃損傷耐性
202 改善された強度
204 圧密化
206 硬化
208 有効圧力
210 有効温度
212 有効期間
214 流れ方向
250 方法
Claims (20)
- 改善された衝撃損傷耐性(200)および改善された強度(202)を有する積層複合構造体(10)であって、前記積層複合構造体(10)は、
複合材料(106)からなる複数の積層された層(102)であって、前記複数の積層された層(102)内に形成された1つまたは複数の層間波形(100)を有し、各層間波形(100)は、実質的に正弦波形状の輪郭(101)を有し、かつ、形成された前記積層複合構造体(10)のサイズ(103)に応じた深さ(114)および長さ(116)を有する、複数の積層された層(102)を含み、
前記1つまたは複数の層間波形(100)を有する前記積層複合構造体(10)は、前記積層複合構造体(10)の露出した縁部(80)が衝撃力(88)を受けた場合に、前記露出した縁部(80)において改善された強度(202)および改善された衝撃損傷耐性(200)を有する、積層複合構造体(10)。 - 各層間波形(100)の前記深さ(114)は、0.01インチ~0.35インチ(0.254mm~8.89mm)の範囲にある、請求項1に記載の積層複合構造体(10)。
- 各層間波形(100)の前記長さ(116)は、第1の谷部分(112a)の第1の接点(118a)と第2の谷部分(112b)の第2の接点(118b)との間の歪み長(116a)を含み、前記第1の谷部分(112a)と前記第2の谷部分(122b)との間にピーク(110)が形成される、請求項1または2に記載の積層複合構造体(10)。
- 各層間波形(100)の前記長さ(116)は、0.20インチ~0.60インチ(5.08mm~15.24mm)の範囲にある、請求項3に記載の積層複合構造体(10)。
- 各層間波形(100)は、前記深さ(114)に対する前記長さ(116)の所定の比(119)を有する、請求項1から4のいずれか一項に記載の積層複合構造体(10)。
- 前記積層複合構造体(10)は、積層複合ブレードストリンガ(28a)、積層複合スキンパネル(28b)、積層複合スパー(28c)、積層複合飛行制御面(28d)、および積層複合試験クーポン(11)のうちの1つを含む、請求項1から5のいずれか一項に記載の積層複合構造体(10)。
- 前記積層複合構造体(10)は、前記積層複合ブレードストリンガ(28a)を含み、さらに、前記1つまたは複数の層間波形(100)は、前記積層複合ブレードストリンガ(28a)のウェブ(76)を横切っている、請求項6に記載の積層複合構造体(10)。
- 1つまたは複数の層間波形(100)を有し、改善された衝撃損傷耐性(200)および改善された強度(202)を有する積層複合構造体(10)を形成するためのシステム(172)であって、前記システム(172)は、
積層体アセンブリ(120)であって、
第2の積層体(122b)に結合された第1の積層体(122a)であって、前記第1の積層体(122a)は第1のツールプレート(150a)に結合され、前記第2の積層体(122b)は第2のツールプレート(150b)に結合されている、第1の積層体(122a)と、
前記第1の積層体(122a)と前記第2の積層体(122b)との間に結合された1つまたは複数のギャップ要素であって、前記1つまたは複数のギャップ要素(134)は前記第1の積層体(122a)と前記第2の積層体(122b)との間にギャップ領域(145)を形成する、1つまたは複数のギャップ要素(134)と、を含む積層体アセンブリ(120)と、
前記積層体アセンブリ(120)に結合され、前記積層体アセンブリ(120)の圧密化(204)および硬化(206)の間に、前記1つまたは複数の層間波形(100)を形成するための低圧領域(198)を前記ギャップ領域(145)に形成し、かつ、前記1つまたは複数の層間波形(100)を有する前記積層複合構造体(10)を形成するための、加圧システム(174)と、を含み、
前記1つまたは複数の層間波形(100)を有する前記積層複合構造体(10)は、前記積層複合構造体(10)の露出した縁部(80)が衝撃力(88)を受けた場合に、前記露出した縁部(80)において改善された強度(202)および改善された衝撃損傷耐性(200)を有する、システム(172)。 - 前記積層体アセンブリ(120)を前記加圧システム(174)内に固定し、かつ、前記積層体アセンブリ(120)の圧密化(204)および硬化(206)の間に、前記積層体アセンブリ(120)の樹脂材料(108)および繊維材料(107)の前記ギャップ領域(145)内への流れ方向(214)を容易にするために、前記積層体アセンブリ(120)の対向する側面(121)に対してそれぞれ配置された第1のエンドプレート(160a)および第2のエンドプレート(160b)をさらに含む、請求項8に記載のシステム(172)。
- 前記積層複合構造体(10)の前記1つまたは複数の層間波形(100)の各々は、実質的に正弦波形状の輪郭(101)を有し、各々は、形成された前記積層複合構造体(10)のサイズ(103)に応じた深さ(114)および長さ(116)を有する、請求項8または9に記載のシステム(172)。
- 前記システム(172)によって形成された前記積層複合構造体(10)の各層間波形(100)の前記深さ(114)は、0.01インチ~0.35インチ(0.254mm~8.89mm)の範囲にあり、前記システム(172)によって形成された前記積層複合構造体(10)の各層間波形(100)の前記長さ(116)は、0.20インチ~0.60インチ(5.08mm~15.24mm)の範囲にある、請求項10に記載のシステム(172)。
- 前記積層体アセンブリ(120)の前記1つまたは複数のギャップ要素(134)は、前記積層体アセンブリ(120)の圧密化(204)および硬化(206)の間に形成された前記1つまたは複数の層間波形(100)の深さ(114)および長さ(116)を制御するために、前記第1の積層体(122a)の長手方向縁部(146)に沿って互いに対向して配置された2つの積層シム(135)を含む、請求項8から11のいずれか一項に記載のシステム(172)。
- 前記加圧システム(174)は、真空バッグアセンブリ(175)および真空ポンプアセンブリ(183)を有する真空シールシステム(174a)を含み、前記真空バッグアセンブリ(175)は、第1のフィルム層(170a)、第2のフィルム層(170b)、第1のブリーザ材料層(176a)、真空バッグフィルム(178)、およびシーラント材料(180)を含む、請求項8から12のいずれか一項に記載のシステム(172)。
- 前記積層複合構造体(10)は、積層複合試験クーポン(11)、積層複合ブレードストリンガ(28a)、積層複合スキンパネル(28b)、積層複合スパー(28c)、および積層複合飛行制御面(28d)のうちの1つを含む、請求項8から13のいずれか一項に記載のシステム(172)。
- 1つまたは複数の層間波形(100)を有し、改善された衝撃損傷耐性(200)および改善された強度(202)を有する積層複合構造体(10)を形成する方法(250)であって、前記方法(250)は、
第1の積層体(122a)と第2の積層体(122b)との間にギャップ領域(145)を形成するために、前記第2の積層体(122b)に結合された前記第1の積層体(122a)と、前記第1の積層体(122a)と前記第2の積層体(122b)との間に結合された1つまたは複数のギャップ要素(134)と、を少なくとも含む積層体アセンブリ(120)を形成するステップ(252)と、
前記積層体アセンブリ(120)を圧密化し、かつ、前記1つまたは複数の層間波形(100)を形成するために前記ギャップ領域(145)に低圧領域(198)を形成するために、加圧システム(174)を使用するステップ(254)と、
前記1つまたは複数の層間波形(100)を有する前記積層複合構造体(10)を形成するために、前記積層体アセンブリ(120)を硬化するステップ(256)と、を含み、
前記形成された積層複合構造体(10)は、改善された衝撃損傷耐性(200)および改善された強度(202)を有する、方法(250)。 - 前記積層体アセンブリ(120)を形成するステップ(252)の後であって、前記加圧システム(174)を使用するステップ(254)の前に、前記積層体アセンブリ(120)の圧密化(204)および硬化(206)の間に、前記積層体アセンブリ(120)の樹脂材料(108)および繊維材料(107)の前記ギャップ領域(145)内への流れ方向(214)を容易にするために、第1のエンドプレート(160a)および第2のエンドプレート(160b)を前記積層体アセンブリ(120)の対向する側面(121)に対してそれぞれ配置するステップ(258)を含む、請求項15に記載の方法(250)。
- 前記積層体アセンブリ(120)を形成するステップ(252)は、前記第1の積層体(122a)を前記第2の積層体(122b)に結合する前に、前記第1の積層体(122a)を第1のツールプレート(150a)に結合し、前記第2の積層体(122b)を第2のツールプレート(150b)に結合するステップをさらに含む、請求項15または16に記載の方法(250)。
- 前記積層体アセンブリ(120)を形成するステップ(252)は、前記積層体アセンブリ(120)の圧密化(204)および硬化(206)の間に形成された前記1つまたは複数の層間波形(100)の深さ(114)および長さ(116)を制御するために、2つのギャップ要素(134)を前記第1の積層体(122a)の長手方向縁部(146)に沿って互いに対向して配置し結合するステップをさらに含む、請求項15から17のいずれか一項に記載の方法(250)。
- 前記加圧システム(174)を使用するステップ(254)は、前記加圧システム(174)を前記積層体アセンブリ(120)に、または前記積層体アセンブリ(120)の周囲に、結合させるステップを含み、前記加圧システム(174)は、真空バッグアセンブリ(175)および真空ポンプアセンブリ(183)を有する真空シールシステム(174a)を含む、請求項15から18のいずれか一項に記載の方法(250)。
- 前記積層複合構造体(10)を形成するために前記積層体アセンブリ(120)を硬化させるステップ(256)は、積層複合試験クーポン(11)、積層複合ブレードストリンガ(28a)、積層複合スキンパネル(28b)、積層複合スパー(28c)、および積層複合飛行制御面(28d)のうちの1つを含む前記積層複合構造体(10)を形成するために、前記積層体アセンブリ(120)を硬化させるステップ(256)をさらに含む、請求項15から19のいずれか一項に記載の方法(250)。
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