CN101767646B - 复合翼梁 - Google Patents

复合翼梁 Download PDF

Info

Publication number
CN101767646B
CN101767646B CN201010003957.3A CN201010003957A CN101767646B CN 101767646 B CN101767646 B CN 101767646B CN 201010003957 A CN201010003957 A CN 201010003957A CN 101767646 B CN101767646 B CN 101767646B
Authority
CN
China
Prior art keywords
preformed member
thickness
spar
shaped fibers
uniform thickness
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.)
Expired - Fee Related
Application number
CN201010003957.3A
Other languages
English (en)
Other versions
CN101767646A (zh
Inventor
T·怀布罗
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Aviation Systems Ltd
Original Assignee
GE Aviation Systems Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=40379200&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=CN101767646(B) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by GE Aviation Systems Ltd filed Critical GE Aviation Systems Ltd
Publication of CN101767646A publication Critical patent/CN101767646A/zh
Application granted granted Critical
Publication of CN101767646B publication Critical patent/CN101767646B/zh
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
    • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00—Making preforms
    • B29B11/14—Making preforms characterised by structure or composition
    • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/56—Winding and joining, e.g. winding spirally
    • B29C53/58—Winding and joining, e.g. winding spirally helically
    • B29C53/583—Winding and joining, e.g. winding spirally helically for making tubular articles with particular features
    • B29C53/585—Winding and joining, e.g. winding spirally helically for making tubular articles with particular features the cross-section varying along their axis, e.g. tapered, with ribs, or threads, with socket-ends
    • 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
    • B29C69/00—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore
    • B29C69/001—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore a shaping technique combined with cutting, e.g. in parts or slices combined with rearranging and joining the cut parts
    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
    • D04C1/00—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof
    • D04C1/02—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof made from particular materials
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
    • D04C3/00—Braiding or lacing machines
    • D04C3/40—Braiding or lacing machines for making tubular braids by circulating strand supplies around braiding centre at equal distances
    • D—TEXTILES; PAPER
    • D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
    • D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
    • D04C3/00—Braiding or lacing machines
    • D04C3/48—Auxiliary devices
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/56—Winding and joining, e.g. winding spirally
    • B29C53/58—Winding and joining, e.g. winding spirally helically
    • B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
    • B29C53/68—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels with rotatable winding feed member
    • 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
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2403/00—Details of fabric structure established in the fabric forming process
    • D10B2403/02—Cross-sectional features
    • D10B2403/023—Fabric with at least two, predominantly unlinked, knitted or woven plies interlaced with each other at spaced locations or linked to a common internal co-extensive yarn system
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2403/00—Details of fabric structure established in the fabric forming process
    • D10B2403/02—Cross-sectional features
    • D10B2403/024—Fabric incorporating additional compounds
    • D10B2403/0241—Fabric incorporating additional compounds enhancing mechanical properties
    • D10B2403/02411—Fabric incorporating additional compounds enhancing mechanical properties with a single array of unbent yarn, e.g. unidirectional reinforcement fabrics
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2505/00—Industrial
    • D10B2505/02—Reinforcing materials; Prepregs
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Moulding By Coating Moulds (AREA)
  • Reinforced Plastic Materials (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Braiding, Manufacturing Of Bobbin-Net Or Lace, And Manufacturing Of Nets By Knotting (AREA)

Abstract

本发明涉及复合翼梁，具体而言，根据一个方面，本发明涉及一种制造至少一个非均匀厚度的复合翼梁部件(152)的方法(200)。该方法包括在步骤(202)在非圆柱体心轴(140)上编织多股纤维(126)以形成厚度可变的成形纤维预成型件(150)，弄平成形纤维预成型件(150)，并且对弄平的成形纤维预成型件(150)进行切割，以获得至少一个非均匀厚度的复合翼梁部件(152)。根据本发明的多个实施例制成的翼梁(152)比传统的复合翼梁部件制造更快且更便宜。

Description

复合翼梁
技术领域
本发明一般地涉及复合翼梁。更具体地，本发明涉及具有变化的厚度的复合翼梁，例如，用于诸如推进器翼梁、翼桁架等的多种航空应用中的复合翼梁。
背景技术
翼梁是许多产品的整体构件。这种翼梁通常为承重的结构性元件，用于给此类产品增加支撑。例如，翼桁架提供在飞机中用于将机翼固定到飞机上，并且将机翼产生的升力传递到飞机的机身上。
已知翼梁常采用以实心或框架结构提供的金属材料制成。例如，已知多种用于推进器叶片[1-5]中的金属翼梁为形成在其附近的翼型件提供结构性支撑。
然而，现在有时采用复合材料制造翼梁(例如，通过采用诸如玻璃和/或碳等的多种纤维的机织或编织材料)，因为此类复合材料[6-8]通常比常规的金属翼梁更轻更硬。
但是，尽管基于常规复合材料的翼梁对于许多应用都更好，但是它们在例如需要形成具有变化厚度的复杂形状时(如用于翼桁架/推进器翼梁等时)并不理想。
因此，为了解决用复合材料形成复杂的翼梁形状的需要，采用了多种制造技术。
例如，当制造用于推进器的翼梁时，已知采用了削层(ply-drop)技术，其中切割布片材料的成形部分是手工敷层的，以产生对翼梁的理想三维形状的阶梯状边缘近似。然后在注入树脂以提供成品的翼型件状的推进器之前，用复合纤维材料对阶梯状边缘翼梁进行外层编织(over-braid)。
尽管这种技术提供高质量的推进器，但是存在与这种制造技术相关的某些缺点。例如，布/纤维材料昂贵，并且在可以使用之前必须进行质量检查，此外该技术严重依赖于操作员的技术和经验来正确地将多个层组装成多层的阶梯状翼梁部件。这也进一步减缓了制造过程，并使得生产相对昂贵。
而且，成品翼型件的强度依赖于单个成形部分彼此之间的粘结，以保证形成翼梁的各层在使用时不会层离。另外，单个层或削层的阶梯状边缘部分会在多层翼梁与上覆的编织蒙皮之间引入间隙，在成品推进器中这里会容易逐步形成树脂包。这些树脂包又会在推进器叶片的翼梁中产生皱折，结合编织纤维的不对准，导致随之而来可能的应力点的产生，结构破裂可能会从这些应力点处开始。
因此，需要提供一种制造复合翼梁，特别是具有变化厚度的复合翼梁的改进的方法。
发明内容
因而针对上述与常规翼梁及其相关制造技术相关的缺陷，设计了本发明的多个方面和实施例。
根据本发明的第一方面，提供了一种制造至少一个非均匀厚度的复合翼梁部件的方法。该方法包括在非圆柱体心轴上编织多根纤维以形成厚度可变的成形纤维预成型件(preform)，弄平该成形纤维预成型件，切割弄平的成形纤维预成型件以获得至少一个非均匀厚度的复合翼梁部件。
根据本发明的第二方面，提供了一种用于制造非均匀厚度的复合翼梁部件的装置。该装置包括编织机、位置可变的梭子和非圆柱体心轴。位置可变的梭子可操作以改变非圆柱体心轴相对于编织机的相对位置，使得围绕该非圆柱体心轴编织翼梁层(spar ply)。
根据本发明的另一个方面，提供了一种用于根据本发明的第二方面的装置中的心轴。
本发明的多个方面和实施例使得能够不需要使用削层技术而制造厚度可变的翼梁部件。因而加快了生产，同时降低了成本和生产缺陷的数量。
附图说明
现在将结合附图对本发明的多个方面和实施例进行描述，附图中：
图1示出了根据本发明的一个实施例用于制造非均匀厚度的复合翼梁部件的装置；
图2示出了根据本发明的一个实施例的厚度可变的成形纤维预成型件；
图3示出了如何根据本发明的一种方法对图2的厚度可变的成形纤维预成型件进行加工；
图4示出了根据本发明的一个实施例由图3的方法制造的非均匀厚度的复合翼梁部件和废弃的切除部件；以及
图5示出了根据本发明的一个实施例的一种制造至少一个非均匀厚度的复合翼梁部件的方法。
具体实施方式
图1示出了根据本发明的一个实施例的一种用于制造非均匀厚度的复合翼梁部件152的装置100。该装置包括编织机120，位置可变的梭子142和非圆柱体心轴140。
非圆柱体心轴140可用泡沫、铝、塑料等形成，并且长度可为大约1.3米以形成推进器叶片。在不同的实施例中，可采用多个(例如，多达三个)直径增大的心轴来制造翼梁。翼梁部件152的厚度的变化可例如从大约10mm到大约15或20mm，而成品翼梁部件152可具有例如大约1300mm x 250mm x 9mm的尺寸。
在一个实施例中，编织机120是HerzogTM RF1/192-100型编织机，该编织机可以从Herzog Maschinenfabrik GmbH & Co.KG，AmAlexanderhaus 160，D-26127，Oldenburg，Germany[9]处获得。
编织机120包括可旋转鼓筒122，在该鼓筒上安装了多个卷筒124。在图1中，为了清晰起见，仅示出了8个这样的卷筒124。然而，在实际中，可提供更多(例如，192个)这样的卷筒。在运行中，通过控制器/驱动器130驱动可旋转鼓筒122围绕圆柱体轴线144旋转，控制器/驱动器130可包括由计算机控制系统(未示出)控制运行的电动马达。卷筒124以S形图案围绕着编织的圆周独立地在承载器(carrier)上移动，从一个承载器移向下一个承载器。
卷筒124装载不同的纤维126，这些纤维最终被编织以生产非均匀厚度的复合翼梁部件152。纤维126可包括例如玻璃纤维、e-玻璃、凯夫拉TM、硼、S-玻璃、热塑性塑料、碳纤维等。纤维126可由多个各自单独的股组成。在一个实施例中，玻璃纤维和碳纤维均以4∶1的比例提供，合适的碳和玻璃纤维可从多个制造商处商业获得。
在多个实施例中，纤维126提供为数千根单独的细丝组成的纤维束。这种单独的细丝可具有大约0.005到大约0.010mm级别的直径。例如，可使用3K，6K，12K，24K等的纤维束。在一个实施例中，纤维126是12K HTA型的，其相对扁平，并具有从大约3mm到大约5mm的宽度。
纤维126被穿过编织引导件128，并临时地附到非圆柱体心轴140上。非圆柱体心轴140在形状上可为渐缩的，例如，成形为如截锥，平截头体等。非圆柱体心轴140联接到位置可变的梭子142上，使得当位置可变的梭子142被操作时，非圆柱体心轴140的相对位置相对于编织机120沿轴线144的方向侧向移动。非圆柱体心轴140由合适的轻且硬的材料制成，使得其可在每一端被支撑而没有弯曲。
在运行期间，当可旋转鼓筒122旋转时，非圆柱体心轴140沿着圆柱体轴线144侧向移动，且纤维126在非圆柱体心轴140的表面上编织在一起以形成翼梁层150。此过程例如可通过外层编织一层或多层附加的翼梁层，同时沿相反的方向移动非圆柱体心轴140而被重复。
通过移动非圆柱体心轴，例如沿着圆柱体轴线144以恒速移动，同时也以恒速放下纤维126，由于非圆柱体心轴的径向尺寸上的变化，翼梁层150沿着其长度在圆柱体轴144的方向上被赋予了变化的厚度。因此可以简单地制造非均匀厚度的翼梁层150，并且不需要使用削层或者其它类似的技术。而且，这种技术易于自动化，不需要熟练的操作工而获得理想翼梁层厚度的非均匀性。
翼梁层可包括三轴线编织，其中为了提供最优的抗扭强度，纤维126相对于圆柱体轴线144以+45度，0度和-45度布置。例如，碳纤维可与圆柱体轴线144大体上平行地布置(即，在相对其成大约0度的角度)以在成品非均匀厚度复合翼梁部件152中形成承重结构性部件，与偏移的玻璃纤维(例如，以对圆柱体轴线144成大约+45度和-45度的角度)交织，以便在成品非均匀厚度复合翼梁部件152中提供扭转刚度。在不同的实施例中，也可以改变纤维的相对编织角度以进一步控制层厚度。
用于制造非均匀厚度复合翼梁部件152的装置100也可包括多个其它元件，例如辊子、真空挤压系统，压件等(未示出)，它们形成用于将翼梁层弄平整的平整器。也可提供树脂供料和固化器件(未示出)用于在剪切前稳定平整的翼梁层，以及还可提供切割器(未示出)用于切割翼梁层。为了非均匀厚度复合翼梁部件152的充分自动化生产，可提供这些元件。
图2示出了根据本发明的一个实施例的厚度可变的成形纤维预成型件150。厚度可变的成形纤维预成型件150可采用图1中所示类型的装置100进行制造。
厚度可变的成形纤维预成型件150由形成为圆锥截面形状的翼梁层制成。厚度可变的成形纤维预成型件150的直径从第一端153沿着纵轴线向位于第二端151处的最窄区域减少。翼梁层的厚度从第一端153向第二端151增加。这种增加本质上可为线性的，或者可根据特定的所需的成品非均匀厚度复合翼梁部件152的要求使得其与多种其它预定的厚度轮廓(例如，抛物线形，渐近线形等)相一致。
翼梁层可以三轴线编织图案通过编织三股纤维而成。例如，纵向纤维束可提供成通常从第一端153向第二端151延伸，带有与其交织的交叉纤维束(例如，以对其成大约±45°，±60°，±70°的角度，或这些角度的组合等。)从而可定制成品翼梁部件的抗扭性能。另外，通过提供交织的纤维而不是常规散布的单独的层，根据本发明提供的各种非均匀厚度的复合翼梁部件被提供成具有改善的内部载荷分布特性。
图3示出了如何根据本发明的方法加工图2的厚度可变的成形纤维预成型件150。厚度可变的成形纤维预成型件150的翼梁层被弄平。
可选地，在被弄平前可以通过例如缝合、粘结等方式对其进行固定或稳定。在一个实施例中，翼梁层被弄平，且侧边部分154，156被通过将它们注入树脂而粘结，并且固化树脂以将厚度可变的成形纤维预成型件150保持在充分稳定的平坦位置。最终形成两个非均匀厚度复合翼梁部件152的中央部分不进行粘结，以便两个相对的翼梁层元件可很容易地分开。备选地，中央部分可例如通过将相对的翼梁层元件缝合在一起而临时地合拢。
在不同的实施例中，纤维126可在其表面上提供有粘合剂。典型地此粘合剂为环氧或热塑性粘合剂，其在热和/或压力下可用于强化各层。然后预成型件150可简单地弄平，接着稍微加热、冷却，然后进行切割。备选地，可手工涂敷板状的粘合剂材料。另一种备选方式为进行切割时利用真空来将预成型件保持就位。这可以用打孔的桌子和真空发生器来实现。
一旦弄平了厚度可变化的成形纤维预成型件150，就沿着两条切割线155，157进行切割。例如，可以使用闸刀型切割器或计算机控制的数字式(CNC)切割台。
图4示出了根据本发明的一个实施例通过图3的方法制造的非均匀厚度的复合翼梁部件和废弃的切除部件。由两个处理过的侧边部分154，156形成了废弃的切除部件，并因此例如可注入固化的树脂。
非均匀厚度的复合翼梁部件152可制成无间隙的编织件，且纤维连续地贯穿其主体而分布。非均匀厚度的复合翼梁部件152在厚度上渐缩，朝第一端153越来越厚，而朝第二端151越来越薄。
可将多种非均匀厚度的复合翼梁部件152应用到推进器、机翼等中，在使用时这些应用需要沿着翼梁的长度具有不同的厚度，以考虑不同的载荷。例如，朝向第二端151的较厚的部分可靠近推进器根部/到机身的内侧连接等需要增强的强度和/或刚度连接的地方。
图5示出了根据本发明的一个实施例制造至少一个非均匀厚度的复合翼梁部件的一种方法200。
该方法包括在非圆柱体心轴上编织多束纤维以形成厚度可变的成形纤维预成型件的步骤202。
在编织完成后，下一个步骤204是将成形纤维预成型件弄平。可选地，弄平的预成型件接着在步骤206进行稳定。
最后，该方法200包括对弄平的(可选地稳定的)成形纤维预成型件进行切割以获得至少一个非均匀厚度的复合翼梁部件的步骤208。
尽管本文描述了本发明的多个方面和实施例，但本领域技术人员将会意识到，根据落入本发明的范围内的多种技术，可制造具有多种应用的非均匀厚度的复合翼梁部件许多不同实施例。例如，可将非圆柱体心轴提供为成形的泡沫芯，其可形成成品部件的整体部分，从而无需为了生产成品而从心轴上移除与弄平任何外层编织的纤维。
参考文献
1.CA 401 686(Caldwell)
2.GB 2 084 507(Nutter)
3.US 4,789,304(Gustafson)
4.GB 2,237,532(Fecto)
5.US 5,269,658(Carlson)
6.US 5,222,297(Graff)
7.GB 2,443,482(Pentony)
8.WO 2008/087443(Bateup)
9.http://www.herzog-online.com
在允许的情况下，以上提及的参考文献的内容由此也整体地通过引用而结合在本发明申请中。

Claims (7)

1.一种制造至少一个非均匀厚度的复合翼梁部件的方法，所述方法包括：
在非圆柱体心轴上编织多股纤维以形成厚度可变的成形纤维预成型件；
弄平所述成形纤维预成型件；以及
对弄平的成形纤维预成型件进行切割，以获得所述至少一个非均匀厚度的复合翼梁部件。
2.如权利要求1所述的方法，其特征在于，所述方法还包括在切割之前使所述弄平的成形纤维预成型件稳定。
3.如权利要求1或2所述的方法，其特征在于，编织包括以三轴线编织图形编织三股纤维。
4.如权利要求3所述的方法，其特征在于，所述方法包括以45°-0°-45°的布置编织所述纤维。
5.如权利要求1或2所述的方法，其特征在于，所述方法包括彼此覆盖地连续编织多个层，以增加所述厚度可变的成形纤维预成型件的平均厚度。
6.如权利要求3所述的方法，其特征在于，所述方法包括彼此覆盖地连续编织多个层，以增加所述厚度可变的成形纤维预成型件的平均厚度。
7.如权利要求4所述的方法，其特征在于，所述方法包括彼此覆盖地连续编织多个层，以增加所述厚度可变的成形纤维预成型件的平均厚度。
CN201010003957.3A 2009-01-07 2010-01-07 复合翼梁 Expired - Fee Related CN101767646B (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0900115A GB2466793B (en) 2009-01-07 2009-01-07 Composite spars
GB0900115.7 2009-01-07

Publications (2)

Publication Number Publication Date
CN101767646A CN101767646A (zh) 2010-07-07
CN101767646B true CN101767646B (zh) 2015-05-27

Family

ID=40379200

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201010003957.3A Expired - Fee Related CN101767646B (zh) 2009-01-07 2010-01-07 复合翼梁

Country Status (7)

Country Link
US (1) US8061253B2 (zh)
EP (1) EP2206597B1 (zh)
JP (1) JP5607935B2 (zh)
CN (1) CN101767646B (zh)
BR (1) BRPI1000178A2 (zh)
CA (1) CA2689178C (zh)
GB (1) GB2466793B (zh)

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2145989A1 (de) * 2008-07-15 2010-01-20 Textilma AG Webmaschine zum Herstellen eines im Querschnitt profilierten Gewebes, insbesondere eines Seiles
JP5503481B2 (ja) * 2010-09-30 2014-05-28 一般社団法人日本航空宇宙工業会 繊維強化複合材料を用いた翼状構造体およびその製造方法
FR2969666B1 (fr) * 2010-12-24 2013-02-01 Messier Dowty Sa Procede de tressage de fibres renforcantes a variation d'inclinaison des fibres tressees
DE102011009641B4 (de) * 2011-01-27 2013-04-04 Puma SE Verfahren zum Herstellen eines Schuhoberteils eines Schuhs, insbesondere eines Sportschuhs
US9149997B2 (en) 2012-09-14 2015-10-06 United Technologies Composite flange from braided preform
US20140300027A1 (en) * 2013-03-15 2014-10-09 A&P Technology, Inc. Systems and methods for applying a braid to an irregular core
GB201307066D0 (en) 2013-04-18 2013-05-29 Airbus Operations Ltd Winglet and braided composite spar
US10863794B2 (en) 2013-06-25 2020-12-15 Nike, Inc. Article of footwear having multiple braided structures
KR101838824B1 (ko) 2013-06-25 2018-03-14 나이키 이노베이트 씨.브이. 편조형 갑피를 지닌 신발류 물품
CN104187745A (zh) * 2014-08-07 2014-12-10 北海市台南饼业有限责任公司 一种提取鲜冬瓜膳食纤维的加工制作方法
US10589475B2 (en) 2014-09-23 2020-03-17 General Electric Company Braided blades and vanes having dovetail roots
US9839253B2 (en) 2014-12-10 2017-12-12 Nike, Inc. Last system for braiding footwear
US10674791B2 (en) 2014-12-10 2020-06-09 Nike, Inc. Braided article with internal midsole structure
US9668544B2 (en) 2014-12-10 2017-06-06 Nike, Inc. Last system for articles with braided components
US10238176B2 (en) 2015-05-26 2019-03-26 Nike, Inc. Braiding machine and method of forming a braided article using such braiding machine
US10060057B2 (en) 2015-05-26 2018-08-28 Nike, Inc. Braiding machine with non-circular geometry
US10555581B2 (en) 2015-05-26 2020-02-11 Nike, Inc. Braided upper with multiple materials
US10280538B2 (en) 2015-05-26 2019-05-07 Nike, Inc. Braiding machine and method of forming an article incorporating a moving object
US20160345675A1 (en) 2015-05-26 2016-12-01 Nike, Inc. Hybrid Braided Article
DE102015210581A1 (de) * 2015-06-10 2016-12-15 Bayerische Motoren Werke Aktiengesellschaft Flechtmaschine
US9920462B2 (en) 2015-08-07 2018-03-20 Nike, Inc. Braiding machine with multiple rings of spools
US11103028B2 (en) 2015-08-07 2021-08-31 Nike, Inc. Multi-layered braided article and method of making
EP3399085B1 (en) 2017-05-05 2022-07-13 Ratier-Figeac SAS Multi-layer braided article, a method of making same, an aircraft component comprising the braided article and a method of making a propeller blade
US11051573B2 (en) 2017-05-31 2021-07-06 Nike, Inc. Braided articles and methods for their manufacture
US10806210B2 (en) 2017-05-31 2020-10-20 Nike, Inc. Braided articles and methods for their manufacture
US11202483B2 (en) 2017-05-31 2021-12-21 Nike, Inc. Braided articles and methods for their manufacture
DE102017210815B4 (de) * 2017-06-27 2020-06-04 Bayerische Motoren Werke Aktiengesellschaft Verfahren zur Herstellung einer mehrlagigen Faserverbundpreform für ein Faserverbundbauteil
US10716354B2 (en) * 2017-07-13 2020-07-21 Under Armour, Inc. Braided article and method of making
EP3556544B1 (en) 2018-04-17 2021-07-28 Ratier-Figeac SAS Propeller blade spar
US11192623B2 (en) * 2018-09-14 2021-12-07 The Boeing Company Monolithic spar for a wing
EP3848488A1 (en) * 2020-01-08 2021-07-14 Ratier-Figeac SAS Braiding

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101249885A (zh) * 2006-12-13 2008-08-27 波音公司 用于机翼翼板的肋支撑
EP1999013A1 (en) * 2006-03-27 2008-12-10 Airbus UK Limited Aircraft component

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA401686A (en) 1941-12-23 United Aircraft Corporation Composite propeller blade
FR1518681A (fr) * 1966-11-08 1968-03-29 Tech Du Verre Tisse Matériau pour la constitution de structures dites ablatives protégeant des organessoumis à des températures élevées
BR8105757A (pt) 1980-10-02 1982-05-25 United Technologies Corp Processo pra a producao de um aerofolio
US4519290A (en) * 1983-11-16 1985-05-28 Thiokol Corporation Braided preform for refractory articles and method of making
JPS62280026A (ja) * 1986-05-30 1987-12-04 Daiwa Seiko Inc 釣竿等の中空管状体の製造法
US4789304A (en) * 1987-09-03 1988-12-06 United Technologies Corporation Insulated propeller blade
US5042968A (en) 1989-11-02 1991-08-27 United Technologies Corporation Propeller blade subassembly and method for making a propeller blade subassembly
US5269658A (en) * 1990-12-24 1993-12-14 United Technologies Corporation Composite blade with partial length spar
US5203249A (en) * 1991-08-30 1993-04-20 United Technologies Corporation Multiple mandrel/braiding ring braider
US5222297A (en) * 1991-10-18 1993-06-29 United Technologies Corporation Composite blade manufacture
US5820804A (en) * 1996-06-20 1998-10-13 Elmaleh; Jon Apparatus and method for shaping an elongated member
WO1999061385A2 (en) * 1998-05-26 1999-12-02 J. Michael Richarde, Llc System and method for manufacturing a carbon fiber composite
EP1600544B1 (en) * 1999-01-12 2013-10-16 Hunter Douglas Inc. Method for manufacturing a nonwoven fabric
US6503625B1 (en) * 1999-10-08 2003-01-07 W.R. Grace & Co. - Conn. Fibers for reinforcing matrix materials
JP2002240159A (ja) * 2001-02-21 2002-08-28 Murata Mach Ltd 飛行船ブレード用テープの作成方法
JP2002371139A (ja) * 2001-06-14 2002-12-26 Yuichi Sugiyama Ｆｒｐ用繊維製補強材およびこれを用いたｆｒｐ成形体
US7001425B2 (en) * 2002-11-15 2006-02-21 Scimed Life Systems, Inc. Braided stent method for its manufacture
JP2004353134A (ja) * 2003-05-30 2004-12-16 Murata Mach Ltd 幅広ヤーンによるブレイディング組成基材及びその製造方法
US7093527B2 (en) * 2003-06-10 2006-08-22 Surpass Medical Ltd. Method and apparatus for making intraluminal implants and construction particularly useful in such method and apparatus
US7165945B2 (en) * 2003-08-22 2007-01-23 Sikorsky Aircraft Corporation Braided spar for a rotor blade and method of manufacture thereof
JP2005194768A (ja) * 2004-01-07 2005-07-21 Murata Mach Ltd コンクリート柱補修および／又は補強工法及び補修および／又は補強部材
GB2443482A (en) 2006-11-02 2008-05-07 Smiths Group Plc Propeller blade retention
GB2449058B (en) 2007-01-20 2011-08-10 Smiths Aerospace Group Ltd Blades
FR2913053B1 (fr) * 2007-02-23 2009-05-22 Snecma Sa Procede de fabrication d'un carter de turbine a gaz en materiau composite et carter ainsi obtenu

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1999013A1 (en) * 2006-03-27 2008-12-10 Airbus UK Limited Aircraft component
CN101249885A (zh) * 2006-12-13 2008-08-27 波音公司 用于机翼翼板的肋支撑

Also Published As

Publication number Publication date
JP2010159049A (ja) 2010-07-22
GB0900115D0 (en) 2009-02-11
US20100170990A1 (en) 2010-07-08
GB2466793B (en) 2011-11-09
EP2206597A3 (en) 2016-02-17
CN101767646A (zh) 2010-07-07
GB2466793A (en) 2010-07-14
EP2206597A2 (en) 2010-07-14
CA2689178C (en) 2017-04-18
BRPI1000178A2 (pt) 2011-03-29
EP2206597B1 (en) 2019-02-20
US8061253B2 (en) 2011-11-22
CA2689178A1 (en) 2010-07-07
JP5607935B2 (ja) 2014-10-15

Similar Documents

Publication Publication Date Title
CN101767646B (zh) 复合翼梁
US10173410B2 (en) Device and method for 3D printing with long-fiber reinforcement
EP3003694B1 (en) Continuous fiber-reinforced component fabrication
EP2283995B1 (en) Method to manufacture at least a component of a blade of a wind-turbine
EP2986439B1 (en) Braided composite spar
CN105392620B (zh) 复合材料加筋板及其制造方法
KR20110002009A (ko) 복합재 구조의 강화를 위한 프리폼과 이의 제조방법
JP2012016948A (ja) 複合構造物の構成部材を製造する方法
CN103628923A (zh) 金属包覆层、复合材料叶片以及金属包覆层和叶片制造方法
EP3081370B1 (en) A composite radius filler for filling a void space in a skin-stiffener transition assembly
US20170225413A1 (en) Method for manufacturing a reinforced part comprising a composite material
EP2743064B1 (en) Lightning strike protection means and fibre composite component
CN107428033A (zh) 片状增强纤维基材、预成型体及纤维增强树脂成型品
CN110424097A (zh) 一种纤维编织体连续生产线及编织体生产工艺
Erber et al. Expanded role for thermoplastic composites
CN209757497U (zh) 一种复合纤维飞机窗框
CN113104210B (zh) 三维机织复合材料整体成型的旋翼桨叶及制作方法
EP3615290B1 (en) A preform with local reinforcement
JP6176090B2 (ja) 三次元繊維構造体及び補強材

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20150527

CF01 Termination of patent right due to non-payment of annual fee