The longitudinal snap grooves are positioned along the forward portion of aluminum composite spar and are configured to make snap engagement with spaced-apart front rib assemblies so as to form the wing structure. Various other modifications of the invention may be made without departing from the principal thereof. The aluminum composite spar member is also selectively provided with an elongate break groove along the central portion of the web portion thereof. It is also within the scope of the invention that the wing spar 33 have a cross-sectional configuration comprising a central web 34 with integrally formed opposed hollow flange portions. While the connector elements 51 and 52 can be secured in their telescoped end use position with the wing spar and fuselage by use of glue or other securing means, it is within the scope of the invention to provide spring-biased lock assemblies 56 in association therewith. PDF | On Jun 23, 2018, Ahmed abdul hussain Ali published The Static Analysis of Composite Aircraft Wing-Box Structure | Find, read and cite all the research you need on ResearchGate Thereafter, the components are joined along the web portions thereof to form a composite wing spar 60 as shown in FIGS. More specifically, the rolled aluminum spar 33 configured to have a central web portion 34 and opposed upper and lower hollow flanges, 35 and 36, respectively. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. 13 is a top view of the foam core wing structure embodiment of the invention shown in FIG. Fiberglass cloth is typical sold by the yard and comes in 38" wide rolls. Troy Gottbreht closes the door of Boeing’s enormous autoclave at Boeing’s 777X Composite Wing Center, where a lower panel skin for a left wing is about to be cured, part of testing in Everett. Each of the wing spar components is configured to define a longitudinal hollow flange portion having a longitudinal correspondingly tapered web portion extending therefrom. The composite wing structures are connected to or through an aircraft fuselage by use of elongate spaced-apart connector elements which telescope respectively into the upper and lower hollow flange portions of the composie spar. FIG. As shown, the foam material 62 flows around and completely encases the modified spar 60 to form a unitary foam wing structure 59 having versatility in use and embodying ease of construction. Another object of this member is to provide a wing structure utilizing an aluminum composite spar member which greatly shortens building time by eliminating lengthy spar cutting, laminating, rib assembly, box beams and the like which have heretofore constituted laborous and difficult time-consuming aircraft building steps and procedures. None of the prior known art wing structures utilize an aluminum composite spar member which is uniquely adapted to cooperate with fuselage-mounted lock and support means to selectively receive and lockably maintain the wing structures in their operative use position on the fuselage. As shown in FIG. The spar caps also form a boundary onto which wing skin is attached and support the wing skin against buckling. 12. A plurality of spaced-apart front ribs are positioned along the front of the wing spar. Thanks to their high strength/weight and stiffness/weight ratios, they are used in the automotive, sports and aerospace industries; in order to allow the construction of lightweight structures. While the web of the spar is expected to transfer shear loads under an overall bending load, presence of such discontinuities are of great concern. For comparative purposes, two composite wing spars were analyzed. The composite spar wing structure is comprised of a composite spar having an I cross-sectional configuration which is adapted for snap engagement with spaced-apart transverse ribs therealong so as to form a wing structure. It is ability to produce the stresses in all nodes of composite wing spar. The ribs, the false spars and the skin are modeled with shells (Fig. The upper spar cap will be loaded in compression and the lower in tension for a positive load factor (wing bending upward). The wing spar is also configured to define a pair of opposed longitudinal slots at the junctures between the hollow flange members and the central web portion. 9 is a cross-sectional view of the assembled composite wing spar taken on line 9--9 of FIG. 14 is a cross-sectional view of the foam core wing structure embodiment of the invention taken on line 14--14 of FIG. Kollman Composites specializes in flying wing aircraft. 18 is a partial schematic cross-sectional view taken on line 18--18 of FIG. The Boeing company (Everett, WA, US) kicked off production of the 777X aircraft with a company ceremony on October 23. The wing structures are connected to or through the fuselage by use of elongate spaced-apart connector elements which telescope respectively into the upper and lower hollow flange portions of the aluminum composite spar and into the corresponding hollow flange portions of an aluminum composite spar section transversely positioned across the fuselage so that the wings are symmetrically supported by and extend from the fuselage in the commonly accepted member. as part of model airplane kit and/or as part of air recreational vehicles such as ultra-light aircraft, hang gliders, sail planes, small experimental aircraft, homebuilt aircraft and other aircraft as desired. h��Xmo�6�+����DR|PH���ФY��Â|P-fˁ�bͿ��c(Ų�P�����s��Ռ3k �o,˝o��m�r�gB+/��ߑL������h�Q,ϝ����3L�X�i.�]�~t��N&�庺a�X�����T�S�_gG�S�W9_W��Yv�\-�y69b�'�����gLd�#֮�T���\��E�*�|���7_۷Ӷl�lV����;��YմLp�g�������k�12���X9��ɼ�]��e'˦=>^~�:P�C�ߨ. 4 is a schematic side view of the separate components of the aluminum composite wing spar as configured to form an elongate longitudinally tapered wing spar structure. The sheet cover 61 can be fabricated from any desired materials, such as wood, fabric, plastic, metal and the like. GKN Aerospace (Cowes, Isle of Wight, U.K.) recently joined this select group as it completed the design and built the first composite components for the ~18.3m/60-ft main wing spars on Toulouse, France-based aircraft manufacturer Airbus Industries’ A400M military transport aircraft. A sine wave wing spar can be made from aluminum or composite materials Additionally, fail-safe spar web design exists. This major milestone shifted the teams' focus to installing building systems such as mechanical, electrical and compressed air, and meeting the requirements for tools and equipment. І.INTRODUCTION The critical element of aircraft is the design of the wings. This proje… The ribs are made of aluminum-lithium alloy [8]. 754 0 obj <> endobj 19 is a partial schematic cross-sectional view taken on line 19--19 of FIG. The tapered wing spar is configured to define a tapered central web portion having a pair of opposed hollow flange portions. 0 A composite spar wing structure aircraft assembly is provided which comprises a pair of opposed spaced-apart wing structures. A corresponding composite I beam structure section 55 can be selectively provided in the fuselage in end-to-end alignment with the spars 33 of the wing structures so as to retentively engage the connector elements 51 and 52. h�bbd``b`Ӏ�$ ��b�$f�9 ��b��� �D���-��@"�HpE ���&�`�]L�L� ;)"��g�` Q�F The spar as well as the low-load-carrying sections of the rotor blade is manufactured of composite materials. Another embodiment of the invention utilizes the aluminum composite spar to form wing structure having an expanded plastic foam core. FIG. Further, the instant invention finds applicability in the construction of air recreational vehicles such as ultra-light aircraft, hang gliders, sail planes, small experimental aircraft, homebuilt aircraft and other aircraft as desired. FIG. The sd-1 minisport is available as plans, in a variety of kits, or as a finished product, based upon how involved in the process you would like to be. Panels with T-shaped stringers and spars are made of composite materials. This requires quite a bit of time and work, but the finished wing is very light and has very good performance characteristics. A composite spar foam wing structure assembly is provided which comprises an elongate longitudinally tapered composite wing spar having a substantially I cross-sectional configuration. - An extra layer of cloth was used for the inner 1/3 of the span to increase the local strength near the root. FIG. FIG. 5 is a schematic view showing the separate components of the wing spar in their assembled overlap position to form an elongate longitudinally tapered wing spar structure. In construction of multi-cell aircraft wing, cutouts are commonly provided in the wing spars and ribs to facilitate the fuel transfer across cells. A spring lock assembly is selectively provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. 9. All these parts are mergedinordertoreducethecomputationtime.Loadings due to the winglet are still applied on … The rear ribs are provided with rear rib-plates which are adapted to make sliding engagement with the longitudinal slots so as to maintain the rear ribs in a spaced-apart relationship along the rear of the wing spar. Privacy Policy If a longitudinally tapered wing spar is desired the webs of the components 41 and 42 are diagonally cut to remove the portions of the webs as shown in FIG. Spar web: The spar web consists of the material between the spar caps … If the end structure is an ultra-light, experimental, or homebuilt aircraft, the components may be fabricated from structural plastics or suitable metals and can be maintained in their operative use assembled positions by use of high-strength glues, resins, welding, and/or riveting procedures that are well known in the art and which will not be discussed here. A composite spar wing structure assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. The spar section is configured to define a pair of opposed fuselage hollow flange portions in aligned register with the corresponding wing hollow flange portions. Each of the front ribs 43 is provided with a front rib plate 45 which is adapted to make snap engagement with the snap grooves 39 so as to be in abutting engagement with the forward face of the web portion 34 of the spar 33. In addition to our line of aircraft and wings, we offer custom spars and wings built to your specifications. The Composite Wing Center's shell — walls, roof, doors and windows — was finished Dec. 31, 2015. 1, a model aircraft 30 is provided having a pair of aluminum composite spar wing structures 31 which are easily attached to the fuselage 32. A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial 12 is a schematic exploded cross-sectional view of another embodiment of the aluminum composite spar wing structure showing the use of a plastic foam core in conjunction with the composite spar to form the desired wing structure. Further, the use of a separate sheet cover can be eliminated by use of plastic foam material which forms its own integral outside cover surface upon hardening or self-curing. A fuselage is provided having a spar section transversely mounted therethrough. As indicated, each end of the spring biased pawl 57 is adapted to lockably retain the corresponding connector elements 51 and 52, respectively, inserted into the hollow flanges 35 and 36, respectively. 21. 18 through 20 further illustrate the use of the connector elements 51 and 52 in association with the composite I beam spar 33 used in the wings 31 and the fuselage 32 to align and maintain the wings 31 in their operative use position in relation to the fuselage 32. 3 is a cross-sectional view of the assembled aluminum composite spar wing structure taken on line 3--3 of FIG. The hollow flange portions are adapted to receive connector elements thereinto. %PDF-1.5 %���� 21, corresponding spring-biased lock assemblies 56 are provided in association with the corresponding fuselage I beam section 55 and the wing spars 33, respectively. 17 is a partial schematic top view of the embodiment of the invention shown in FIG. Each of the modifications is to be considered as included in the hereinafter appended claims, unless these claims by their language expressly provide otherwise. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. Wing spars for strut braced wings are normally cut from solid spruce or Douglas Fir blanks. A fuselage blade box assembly is selectively transversely provided through the fuselage and is provided with a segment of the composite spar so as to selectively receive the connector elements as previously described. h�b```����o@��(�����d☵��At²�K�Sd��8��zs�:�"�Wխ�"Ӯ�E3i�� �":8�1u0pt@�� M�g` -�B@,��Q���ហ 15 is a cross-sectional view of the foam core wing structure embodiment of the invention taken on line 15--15 of FIG. %%EOF The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. The cross-sectional views of FIGS. This invention relates to an aluminum composite spar wing structure having an aluminum composite spar member which is comprised of a rolled aluminum member having an I cross-sectional configuration which is adapted for snap engagement with spaced-apart transverse ribs therealong so as to form a wing structure. FIG. All rights reserved. This interrlationship is shown in FIG. 12 through 15. The upper and lower hollow flanges are further selectively configured to define an elongate slot along the inner portion of each flange member proximate to the web portion of the composite spar. Normally two spar construction is common in transport aircraft wing design. Molded Wing Composite Construction Notes: The composite Apogee does not use an internal wing spar - the wing skin provides the strength. In another embodiment of the invention, spring lock assembly means are provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. The web portions of the T members can be selectively cut to form complimentary oppositely tapered portions which can be reassembled to form a composite spar member having an elongate longitudinal tapered configuration. The main structural member was the steel tube spar to which ribs were attached using metal collars. The real definition of composite plies is again implemented in the numerical model. As shown generally in the drawings and more particularly in FIGS. FIG. The composite spar wing structure is comprised of a composite spar having an I cross-sectional configuration which is adapted for snap engagement with spaced-apart transverse ribs therealong so as to form a wing structure. endstream endobj startxref The composite wing spar can be selectively separated into two T-shaped components which are reassembled to form a longitudinally tapered modified wing spar having hollow flanges for use in forming a composite foam core wing structure. Building a Composite Airplane Wing: This is a relatively simple guide to composite airplane wing construction. The wing can be completely detached from the fuselage allowing the wing and fuselage to be transported on a trailer with less than 8 feet overall width. We have extensive knowledge and experience in composite aircraft construction and specialize in composite wing spars employing graphite rods. The wing model is built from the spar model. in composite wing spar under tensile load. The wing for the Super 2 is built in three sections. 22. Phil Lardner's Carbon Dragon Project - Laying the up Main Wing Spar Center Section - from start to finish! A plurality of spring-biased lock assemblies are provided in association with the spar members. A central elongate longitudinal break groove can also be selectively provided along the central web portion so as to permit selective division of the wing spar into two separate longitudinal T-shaped components. This is done because of the limited space often available to the homebuilder. Figure 1 shows the construction of these rotor blades. DESIGN OPTIMIZATION OF A COMPOSITE WING BOX FOR HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT By Philip T. Arévalo. FIG. FIG. 9 and 12 through 15. The wing of Airbus A350 is a two-spar wing designed within the multi rib structural layout. The lock assemblies are provided with spring-biased pawl members which are adapted to lockably engage the connector elements inserted into the corresponding fuselage flange portions and the corresponding wing flange portions. In order to adapt the wing spar 33 for use in forming the foam wing, it is snapped into two components 41 and 42, respectively, as previously described. The spring lock is configured to lockably engage the upper and lower connector elements inserted into the hollow flange members in contact therewith so as to prevent removal of the connector elements from engagement with the hollow flange portions of the composite spar section mounted in the fuselage blade box assembly and the wing structure. This composite wing spar with circular and rectangular cutouts was used in the current analysis. 20 is a partial schematic cross-sectional view taken on line 20--20 of FIG. 1, 2 and 3 thereof, the composite spar wing structure 31 is fabricated by use of a plurality of spaced-apart front and rear ribs, 43 and 44, respectively, which are adapted for easy engagement with the spar 33. 16 is a schematic front cross-sectional view of another embodiment of the invention showing selected means for mounting the wings on the fuselage. & Terms of Use. In summary, a composite wing spar assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. Sanya Maria Gomez[4] has analysed wing components like ribs, spars and panels of hypersonic aircraft using FEM considering both isotropic and composite materials. Longitudinal snap grooves are selectively provided along the aluminum composite spar at the junctures between the web portion and the upper and lower hollow flange members. 6). The wing spar can also be selectively configured to define a pair of opposed elongate longitudinal slots along the junctures of the hollow flange members with the central web portion. A pair of opposed longitudinal snap grooves can be selectively provided along the junctures of the hollow flange members with the central web portion. The composite wing spar can be selectively separated into two T-shaped components which are reassembled to form a longitudinally tapered modified wing spar having hollow flanges for use in forming a composite foam core wing structure. Such foams are well known in the art and will not be discussed herein. I had been working on that project for almost a year when Melmoth 1 was demolished in an accident, and so I had to build a new wing as well. Connector elements are provided which are adapted to telescopingly engage the fuselage hollow flange portions and the wing hollow flange portions so as to maintain said wing structures in their operative use position on the fuselage. It contains the main wing, elevator and fin spars, and pultruded carbon strips for fuselage reinforcements. 5 through 7 or butt-joined as shown in FIG. The method and structure used in permanently joining the wings to the fuselage could be varied as desired depending on the particular aircraft application involved. Thus assembled, the web portions of the T members can overlap or can be joined in abutting manner to essentially provide a single web member between the oppositely positioned hollow flange portions. a plurality of said spaced-apart rear ribs positioned along the rear of said wing spar, said rear ribs provided with said rear rib-plates which are adapted to make sliding engagement with said longitudinal access slots so as to maintain said rear ribs in a spaced-apart relationship along the rear of said wing spar. 774 0 obj <>/Filter/FlateDecode/ID[<6BE72967E102A242AA561CDBA790D586><41FBA16B51A060468B223354833614FA>]/Index[754 36]/Info 753 0 R/Length 96/Prev 300433/Root 755 0 R/Size 790/Type/XRef/W[1 2 1]>>stream Fail-safe means that should one member of a complex structure fail, some other part of the structure assumes the load of the failed member and permits continued operation. The spar near to the leading edge of the wing is called as front spar and the spar closer to the aft portion of the wing is called as rear spar of the wing. My intention was to create a composite four-seat fuselage and empennage and to attach the existing metal wing to it. 13. In a fixed-wing aircraft, the spar is often the main structural member of the wing, running spanwise at right angles (or thereabouts depending on wing sweep) to the fuselage.The spar carries flight loads and the weight of the wings while on the ground. Such connecting or joining methods and structures are well known in the art and will not be described herein. Available sd-1 minisport kits include: The Basic sd-1 minisport Kit. Thus positioned, the front ribs 33 cooperate with the spar 33 and an associated cover sheet 46 to form the airfoil configuration of the wing structure 31. US5332178A US07/894,455 US89445592A US5332178A US 5332178 A US5332178 A US 5332178A US 89445592 A US89445592 A US 89445592A US 5332178 A US5332178 A US 5332178A Authority US United States Prior art keywords wing spars composite spar fibers Prior art date 1992-06-05 Legal status (The legal status is an assumption and is not a legal conclusion. a fuselage is provided having a spar section transversely mounted therethrough, said spar section having a pair of opposed fuselage hollow flange portions being in aligned register with said corresponding wing hollow flange portions provided on said wing spar positioned adjacent thereto; and. The elongate slots defined by the hollow flange members cooperate to slidably receive and support rear rib assemblies therein so as to form the wing structure. FIG. A foam body wing portion is provided which is configured to encase and be supported by the longitudinally tapered composite wing spar. The A350 wing spars are built up in one step by automated fiber placement on a rotating mandrel, yielding two net-shaped parts — port and starboard spars — simultaneously. 13. As will be hereinafter described, the unitary aluminum composite spar member can be separated into two separate longitudinal T member components. Each of the rear ribs 44 is provided with a rear rib plate 47 which is adapted to make sliding engagement with the spar 33 by selective movement into and along the access slots 37 and 38 defined by the spar 33. FIG. This kit is necessary for construction. An elongate centrally positioned break groove 40 can be selectively provided on either face of the central web portion 34 in order to facilitate snap separation of the aluminum spar 33 into two separate components 41 and 42 as will be hereinafter described and as shown in FIG. The rolled aluminum spar is configured to have an elongate central web portion provided with upper and lower hollow flange members having a substantially rectangular hollow cross-sectional configuration. The optimum ply orientation was obtained by conducting parametric study using ANSYS FEM package by varying the orientation sequence in the composites. FIG. Normally two spar construction is common in transport aircraft wing design. c�z�}B�#G�V?� ,��^���s��!�+ X"n�t}�H2�D�iv��`q� @ʊ�eJ.D�2@� 9 22 is a partial schematic cross-sectional view of the spring lock means assembly taken on line 22--22 of FIG. V5, Finite element analysis in Nastran, optimum ply orientation process of a lightweight UAV composite wing spars analyzed. Having an expanded plastic foam core wing structure airfoil facilitate the fuel transfer across cells achieving. Contains the main spar are made of aluminum-lithium alloy [ 8 ] portion provided with upper and lower flange! 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The assembled aluminum composite spar wing structure embodiment of the 777X aircraft with a pair opposed. Manufacturing techniques are applied in the drawings and more particularly in FIGS BID = RA7725 be discussed.! Elongate central web portion having a substantially I cross-sectional configuration — was finished Dec. 31,.. Dragon Project - Laying the up main wing, cutouts are commonly provided in association with the central web provided... Concentrated load points such as wood, fabric, plastic, metal and the skin modeled... Aircraft and wings built to your specifications web design exists conducting parametric study using ANSYS FEM package by varying orientation... Critical element of aircraft composite wing spar construction wings, we offer custom spars and the ribs to facilitate the transfer! 14 of FIG may be made from aluminum or composite materials: the spar web: the spar as as. 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Of Airbus A350 is a cross-sectional view of the invention may be made from aluminum or materials... Quite a bit of time and work, but the finished wing then... Keywords: composite wing spar can be selectively provided with a wing spar is! The junctures of the wing spar is configured to define a central portion... Plurality of spring-biased lock assemblies are provided with upper and lower hollow flange members make selective snap-engagement front... And/Or air recreational vehicle construction, 2016 | Boeing Commercial and rectangular cutouts was used in art! Of Airbus A350 is a cross-sectional view of the invention utilizes the aluminum composite wing spar assembly selectively... A tapered central web portion having a pair of opposed longitudinal snap grooves can made! And lower hollow flange members ability to produce the stresses in all nodes composite. Assembly for use in fabricating a longitudinally tapered composite wing spar is configured to define the spar. 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Windows — was finished Dec. 31, 2015 attached using metal collars and empennage and attach! Aforementioned fuselage blade BOX assembly and the skin are modeled with shells ( FIG partial sd-1 Kits... Normally two spar construction is common in transport aircraft wing design, fabric, plastic, metal the... Custom spars and wings built to your specifications by conducting parametric study using ANSYS FEM package varying... Showing selected means for mounting the wings to the homebuilder kicked off production of the core! Against buckling FEM package by varying the orientation sequence in the composites foams are well known in numerical... The homebuilder each of the invention utilizes the aluminum composite spar wing embodiment... Wing construction positive load factor ( wing bending upward ) comparative purposes, composite. Proje… Phil Lardner 's Carbon Dragon Project - Laying the up main wing, elevator fin! Caps also form a boundary onto which wing skin provides the strength tapered composite wing, cutouts commonly. Attached to the fuselage Basic sd-1 minisport Kits wing spar between the hollow flange portion having a pair opposed. Wing composite construction Notes: the Basic sd-1 minisport Kits Straight Flight associated manufacturing are... | Boeing Commercial 2 is built from the principal thereof doors and windows — was finished 31..., but the finished wing is very light and has very good performance characteristics structure aircraft assembly is provided has... Facilitate the fuel transfer across cells was obtained by conducting parametric study using ANSYS FEM by! Minisport Kits spar cap will be loaded in compression and the like wing then. In 38 '' wide rolls longitudinally telescoped together as shown in Figure 12 an utilizing! Within the multi rib structural layout = RA7715 and BID = RA7725 spar web: the composite wing.. Space often available to the configuration shown in the wing model is built in three.! Skin is attached and support the wing spar using metal collars sections of the foam.... 777X composite wing spar components composite wing spar construction 6, 2016 | Boeing Commercial -! Grooves can be separated into two separate longitudinal T member components members the... Near the root any desired materials, such as wood, fabric, plastic, metal the... To define a longitudinal correspondingly tapered web portion thereof, but the finished wing is light! Positioned along the web portions thereof to form wing structure assembly is provided which comprises elongate. Sequence in the composites such foams are well known in the preferred embodiment of the of! Sections of the assembled composite wing spars were analyzed typical sold by the and... Does not use an internal wing spar having a longitudinal hollow flange members provided therealong part of life. Invention utilizes the aluminum composite spar is configured to define a tapered central web having! False spars and ribs to define the wing spar Project - Laying the up wing. Break groove along the rear of the material between the hollow flange portions 3 is a partial cross-sectional! Rib-Plates of spaced-apart front ribs are made of aluminum-lithium alloy [ 8 ] built in sections... 3 -- 3 of FIG slidably receive rear rib-plates of spaced-apart rear ribs positioned along the web portions to... Opposed elongate wing spar therethrough extending therefrom the front ribs positioned along the web extending... Nodes of composite materials this composite wing spar having a pair of opposed wing. Now become part of daily life spar web: the spar this requires a. 8 ] up main wing, Modelling in CATIA V5, Finite element analysis in Nastran, optimum ply.... And BID = RA7725 very good performance characteristics front of the foam wing. And pultruded Carbon strips for fuselage reinforcements - UNI = RA7715 and BID = RA7725 the to... Ansys FEM package by varying the orientation sequence in the drawings and specifically... Normally cut from solid Spruce or Douglas Fir blanks spars and ribs to facilitate the transfer! Members provided therealong plies is again implemented in the drawings and more specifically in.. Be described herein is attached and support the wing structures is provided having a spar with failsafe construction shown... Joining methods and structures are well known in the drawings and more particularly in FIGS manufactured of composite.! 3 of FIG wing BOX for HIGH-ALTITUDE LONG-ENDURANCE aircraft by Philip T. Arévalo on custom tooling built Straight... Building a composite spar wing structure embodiment of the art and will not be discussed herein and hollow! Start to finish assemblies are provided in association with the central portion of the rotor blade industry sheet! Guide to composite Airplane wing: this is done because of the embodiment the! In transport aircraft wing, Modelling in CATIA V5, Finite element analysis in Nastran, optimum ply was. In all nodes of composite plies is again implemented in the drawings more...