JP7268951B2 - 複合翼のための外板/ストリンガ設計 - Google Patents
複合翼のための外板/ストリンガ設計 Download PDFInfo
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Description
であり、式中、Aは積層板の引っ張り剛性と称され、Bはカップリング剛性と称され、Dは曲げ剛性と称される。剛性マトリクスA、B、及びDの生成は、複合材積層板の解析において重要な工程である。複合材積層板のA、B、及びDマトリクスを、積層板の機械的挙動の制御、ひいては設計に利用できる。
不具合基準Kは、安全余裕(MS)に近似する破壊性能指標である(即ち、MS=K-1)。不具合基準は、不具合基準Kの値が臨界値(即ち1.0)を下回るとクラックが始まり成長するであろうことを述べている。GIc、GIIc、及びGIIIcの量は、破壊モードI、II、及びIIIそれぞれについての層間破壊に対する靱性であり、印加される荷重及び本体の形状とは独立した材料特性とされる。
少なくとも1つのフランジを有する複合部材であって、前記少なくとも1つのフランジが複合材積層板を含み、前記複合材積層板が自由端を有する複合材のプライスタックを含み、前記スタックのプライが、それぞれのプライ角度に配向された繊維又はプライ内で様々な角度に配向制御された繊維を含み、前記繊維が、前記少なくとも1つのフランジが接合されている複合材外板の一部分が前記少なくとも1つのフランジの前記自由端に対して直角方向に荷重を受ける間、前記スタックの第1のプライと複合材外板の当該部分との界面における層間剥離傾向を抑制するような方式で、第1の変形モードと第2の変形モードとのカップリングを引き起こすように構成されている、複合部材。
前記第1の変形モードが軸方向変形モードであり、前記第2の変形モードが曲げ変形モードである、条項1に記載の複合部材。
前記少なくとも1つのフランジの前記複合材積層板が、非対称であり、非平衡又は平衡である、条項1に記載の複合部材。
前記非対称並びに非平衡もしくは平衡の複合材積層板が、引張荷重又は圧縮荷重に応答して特に曲げ曲率を生成する、条項3に記載の複合部材。
前記スタックの前記プライの少なくとも1つのプライが、0度、±45度及び±90度のプライ角度の何れとも等しくないプライ角度を有する、条項1に記載の複合部材。
前記少なくとも1つのフランジの前記複合材積層板の各プライ界面が、モードI、II、及びIIIエネルギー解放率の組み合わせである不具合基準値であって、自由端層間剥離の開始に関連する不具合基準の臨界値未満である不具合基準値を有する、条項1に記載の複合部材。
自由端を有する第1のプライスタックを含む第1の複合材積層板と第2のプライスタックを含む第2の複合材積層板とを備えた、複合材構造物であって、前記第1の複合材積層板と第2の複合材積層板とが前記自由端に隣接した界面で接合されており、前記第1のスタックの前記プライが、それぞれのプライ角度に配向された繊維、又はプライ内で様々な角度に配向制御された繊維を含み、前記繊維が、前記第2の複合材積層板が前記自由端に対して直角方向に荷重を受けた場合に前記界面における層間剥離の傾向を抑制するような方式で、第1変形モードと第2の変形モードとのカップリングを発生させるように構成されている、複合材構造物。
前記第1の変形モードが軸方向変形モードであり、前記第2の変形モードが曲げ変形モードである、条項7に記載の複合材構造物。
前記第1の複合材積層板はストリンガのフランジを形成し、前記第2の複合材積層板は、前記ストリンガが接合される外板を形成している、条項7に記載の複合材構造物。
前記第1の複合材積層板が、非対称であり、非平衡又は平衡である、条項7に記載の複合材構造物。
前記非対称並びに非平衡もしくは平衡の複合材積層板が、特に、引張荷重又は圧縮荷重に応答して曲げ曲率を生成する、条項10に記載の複合材構造物。
前記第1のスタックの前記プライの少なくとも1つのプライが、0度、±45度及び±90度のプライ角度の何れとも等しくないプライ角度を有する、条項7に記載の複合材構造物。
前記第1の複合材積層板の各プライ界面が、モードI、II、及びIIIエネルギー解放率の組み合わせである不具合基準値であって、自由端層間剥離の開始に関連する不具合基準の臨界値未満の不具合基準値を有する、条項7に記載の複合材構造物。
自由端を有する第1のプライスタックを含む第1の複合材積層板と第2のプライスタックを含む第2の複合材積層板とを備えた複合材構造物における、界面層間剥離を抑制する方法であって、第1の複合材積層板と第2の複合材積層板とが、当該自由端に隣接した界面で接合されており、本方法が、
第2の複合材積層板の特性を明確化するステップ、
第1の複合材積層板の望ましい特性を明確化するステップ、
予測される荷重及び層間剥離位置を明確化するステップ、
確率的戦略又は最適化戦略を選択するステップ、
選択された戦略を用いて、第1の複合材積層板のレイアップ候補のプライ角度を、当該望ましい特性を満たす方向へ調整するステップ、並びに
当該レイアップ候補が当該望ましい特性を満たすことを検証するステップ
を含み、当該望ましい特性は、第1の複合材積層板の自由端近傍の第1の複合材積層板と第2の複合材積層板との界面での層間剥離の抑制を含み、
前記調整するステップと前記検証するステップとが、コンピュータシステムによって実施される、方法。
当該望ましい特性を満たす第1の複合材積層板を製造することを更に含む、条項14に記載の方法。
前記検証するステップが、第1の複合材積層板と第2の複合材積層板との界面での層間剥離に関連するモードI、II、及びIIIエネルギー解放率の組み合わせである不具合基準値を計算することを含む、条項14に記載の方法。
前記検証するステップが、第1の複合材積層板のそれぞれのプライ界面での自由端層間剥離に関連するモードI、II、及びIIIエネルギー解放率の組み合わせである不具合基準値を計算することを含む、条項14に記載の方法。
確率的戦略が選択される場合、前記調整するステップが、確率密度関数を用いて第1の複合材積層板のランダムレイアップを生成することを含み、前記検証するステップが、当該望ましい特性のうちの一又は複数を満たさないランダムに生成されたレイアップを放棄することを含む、条項14に記載の方法。
最適化戦略が選択される場合、前記調整するステップが、違反された制約が考慮されるように最適化問題を調整することを含む、条項14に記載の方法。
残ったレイアップ候補を更にスクリーニングするために、付加的な解析を実施することを更に含み、前記付加的な解析は、切欠き強度、下位積層板の安定性、熱残留応力、及び相互貫通の解析のうちの一又は複数を含むがこれらに限定されない、条項14に記載の方法。
Claims (3)
- 少なくとも1つのフランジ(10a、10b)を有する複合部材であって、前記少なくとも1つのフランジ(10a、10b)が支持装填部(6)を介して複合材外板(4)の一部分に接合されており、前記複合部材は複合材積層板を含み、前記複合材積層板は自由端(30a、30b)を有する複合材のプライスタックを含み、前記プライスタックのプライ(20、22)は繊維を含み、単一のプライ内の全ての繊維が同じプライ角度に配向されるか、又は単一のプライ内の繊維が様々な角度に配向するように制御されており、前記プライ(20、22)の前記繊維の配向は、前記複合材外板(4)の前記一部分が前記少なくとも1つのフランジ(10a、10b)の前記自由端(30a、30b)の端面に対して直角方向に荷重を受ける間に、前記複合材積層板の前記プライスタックのうちの第1のプライと前記支持装填部(6)との界面における層間剥離傾向を抑制するように、開口モードに対するエネルギー解放率G I 、開口モードについての層間破壊に対する靱性G Ic 、面内せん断モードに対するエネルギー解放率G II 及び面内せん断モードについての層間破壊に対する靱性G IIc に対する不具合基準
が1以上であって、前記荷重の方向に平行な軸方向変形モードと前記界面に直角な曲げ変形モードとの組み合わせを引き起こすように構成されている、複合部材。 - 前記複合材積層板の前記プライスタックが、前記荷重の方向に平行な軸方向の引張荷重又は圧縮荷重に応答して曲げを生じる、請求項1に記載の複合部材。
- 前記プライスタックの前記プライの少なくとも1つのプライが、前記荷重の方向に対して、0度、±45度及び±90度のプライ角度の何れとも等しくないプライ角度を有する、請求項1に記載の複合部材。
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JP2021149193A JP2022020616A (ja) | 2015-01-02 | 2021-09-14 | 複合翼のための外板/ストリンガ設計 |
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US14/588,536 | 2015-01-02 | ||
US14/588,536 US10195817B2 (en) | 2015-01-02 | 2015-01-02 | Skin-stringer design for composite wings |
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Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10723436B2 (en) * | 2017-08-14 | 2020-07-28 | The Boeing Company | Methods and apparatus to increase strength and toughness of aircraft structural components |
US10933595B2 (en) | 2018-02-15 | 2021-03-02 | The Boeing Company | Laminated composite structures with interlaminar corrugations to improve impact damage resistance, and system and method of forming the same |
US10786955B2 (en) | 2018-07-16 | 2020-09-29 | The Boeing Company | Apparatuses and methods for fabricating a composite structure and reacting to a placement force |
US11230072B2 (en) | 2018-07-16 | 2022-01-25 | The Boeing Company | Apparatuses for fabricating a composite structure and reacting to a placement force |
CN109583040B (zh) * | 2018-11-07 | 2022-11-18 | 中国航空工业集团公司西安飞机设计研究所 | 一种考虑复合材料结构参数连续性的优化方法 |
JP7112950B2 (ja) * | 2018-12-05 | 2022-08-04 | 三菱重工業株式会社 | 複合材の設計方法および複合材 |
US11247413B2 (en) * | 2018-12-17 | 2022-02-15 | The Boeing Company | Composite parts including hybrid plies, methods of forming the composite parts, and systems for forming the composite parts |
US11519816B2 (en) | 2019-02-18 | 2022-12-06 | The Boeing Company | Composite ply-by-ply damage assessment using correlation factors between finite element models (FEMs) and non-destructive evaluations (NDEs) |
US10913215B2 (en) * | 2019-05-09 | 2021-02-09 | The Boeing Company | Composite structure having a variable gage and methods for forming a composite structure having a variable gage |
US10919256B2 (en) | 2019-05-09 | 2021-02-16 | The Boeing Company | Composite structure having a variable gage and methods for forming a composite structure having a variable gage |
US11325689B2 (en) | 2019-05-09 | 2022-05-10 | The Boeing Company | Composite stringer and methods for forming a composite stringer |
US10857751B2 (en) | 2019-05-09 | 2020-12-08 | The Boeing Company | Composite stringer and methods for forming a composite stringer |
US10919260B2 (en) * | 2019-05-09 | 2021-02-16 | The Boeing Company | Composite structure having a variable gage and methods for forming a composite structure having a variable gage |
US11325688B2 (en) | 2019-05-09 | 2022-05-10 | The Boeing Company | Composite stringer and methods for forming a composite stringer |
CN110588878B (zh) * | 2019-09-20 | 2021-06-22 | 辽宁壮龙无人机科技有限公司 | 一种螺旋桨的制作方法及螺旋桨 |
US11379628B2 (en) * | 2019-09-26 | 2022-07-05 | The Boeing Company | Reinforced composite structure analysis system |
CN113049360B (zh) * | 2019-12-27 | 2023-11-21 | 中国航空工业集团公司西安飞机设计研究所 | 一种飞机复合材料加筋壁板压缩许用应变值的确定方法 |
US11242127B2 (en) | 2020-04-22 | 2022-02-08 | The Boeing Company | Composite stringer assembly and methods for transmitting a load through a composite stringer assembly |
CN111942518A (zh) * | 2020-08-24 | 2020-11-17 | 中国人民解放军海军工程大学 | 一种功能型复合材料新型帽型筋材结构 |
CN114227152B (zh) * | 2021-11-25 | 2023-02-07 | 杰瑞石油天然气工程有限公司 | 筒状件及其加工方法 |
CN114572380B (zh) * | 2022-04-15 | 2023-10-20 | 北京航空航天大学 | 一种基于刚柔耦合机构的柔性后缘机翼 |
CN114770977B (zh) * | 2022-06-17 | 2022-10-25 | 成都飞机工业(集团)有限责任公司 | 一种自动铺丝工装的设计方法、装置、设备及存储介质 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009541092A (ja) | 2006-06-19 | 2009-11-26 | ザ・ボーイング・カンパニー | 軸外れ複合プレプレグの製造方法及び装置 |
JP2013256119A (ja) | 2012-06-08 | 2013-12-26 | Boeing Co:The | 複合積層板内の最適化されたクロスプライ配向 |
WO2014055168A1 (en) | 2012-10-04 | 2014-04-10 | The Boeing Company | Composite structure having a stabilizing element |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9802597D0 (en) * | 1998-02-07 | 1998-04-01 | Hurel Dubois Uk Ltd | Panels and structures |
AU2001262912A1 (en) * | 2000-02-25 | 2001-09-03 | The Boeing Company | Laminated composite radius filler |
US7249512B2 (en) | 2005-01-24 | 2007-07-31 | The Boeing Company | Non-destructive stringer inspection apparatus and method |
US8444087B2 (en) * | 2005-04-28 | 2013-05-21 | The Boeing Company | Composite skin and stringer structure and method for forming the same |
GB0614087D0 (en) * | 2006-07-14 | 2006-08-23 | Airbus Uk Ltd | Composite manufacturing method |
DE102008008386A1 (de) * | 2008-02-09 | 2009-08-13 | Airbus Deutschland Gmbh | Verfahren zur Herstellung eines FVW-Bauteils |
US8551382B2 (en) | 2008-05-28 | 2013-10-08 | The Boeing Company | Modified blade stiffener and fabrication method therefor |
US8074694B2 (en) * | 2009-05-28 | 2011-12-13 | The Boeing Company | Stringer transition method |
GB0912015D0 (en) * | 2009-07-10 | 2009-08-19 | Airbus Operations Ltd | Stringer |
ES2397875B1 (es) | 2010-03-15 | 2014-01-27 | Airbus Operations, S.L. | Método multi-daños para la optimización de un diseño estructural. |
GB201005308D0 (en) * | 2010-03-30 | 2010-05-12 | Airbus Operations Ltd | Composite structural member |
US8862437B1 (en) | 2010-03-30 | 2014-10-14 | The Boeing Company | Multi-scale modeling of composite structures |
US8776375B2 (en) * | 2011-05-19 | 2014-07-15 | The Boeing Company | Aircraft structure for high capacity pull off |
US8763253B2 (en) | 2011-05-19 | 2014-07-01 | The Boeing Company | Vertical laminate noodle for high capacity pull-off for a composite stringer |
US20130231902A1 (en) | 2012-03-05 | 2013-09-05 | Siemens Product Lifecycle Management Software Inc. | Spine-based rosette and simulation in fiber-composite materials |
US8758879B2 (en) * | 2012-06-24 | 2014-06-24 | The Boeing Company | Composite hat stiffener, composite hat-stiffened pressure webs, and methods of making the same |
ES2619478T3 (es) * | 2012-10-31 | 2017-06-26 | Airbus Operations S.L. | Larguerillo |
EP2749405B1 (en) * | 2012-12-26 | 2016-03-23 | Airbus Operations S.L. | Reinforced stringer and method of manufacture thereof |
US9463880B2 (en) | 2013-02-07 | 2016-10-11 | The Boeing Company | Method and system of making composite structures having gap fillers with chopped fiber material |
-
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Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009541092A (ja) | 2006-06-19 | 2009-11-26 | ザ・ボーイング・カンパニー | 軸外れ複合プレプレグの製造方法及び装置 |
JP2013256119A (ja) | 2012-06-08 | 2013-12-26 | Boeing Co:The | 複合積層板内の最適化されたクロスプライ配向 |
WO2014055168A1 (en) | 2012-10-04 | 2014-04-10 | The Boeing Company | Composite structure having a stabilizing element |
JP2016500586A (ja) | 2012-10-04 | 2016-01-14 | ザ・ボーイング・カンパニーTheBoeing Company | 安定化要素を有する複合構造物 |
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