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. The tapered wing spar is configured to define a tapered central web portion having a pair of opposed hollow flange portions. FIG. in composite wing spar under tensile load. 5. 21 is a partial schematic front elevational view of another embodiment of the invention showing the wing spar and fuselage mounted connector element spring lock means assemblies. It is therefore an object of this invention to provide a wing structure utilizing an aluminum composite spar member having great versatility in use and ease of assembly. In the modified airplane kit or toy embodiment of the invention, the wings are secured to the sides of the fuselage by use of a rubber band connector which selectively engages oppositely positioned inwardly extending screw hook elements which are positioned on the respectively root rib elements on each wing so as to extend transversely into the fuselage area. The spar caps also form a boundary onto which wing skin is attached and support the wing skin against buckling. 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. 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. 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. 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. It is ability to produce the stresses in all nodes of composite wing spar. 17 is a partial schematic top view of the embodiment of the invention shown in FIG. %%EOF 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. © 2004-2020 FreePatentsOnline.com. State of the art 777X Composite Wing Center completes parts Dec 6, 2016 | Boeing Commercial. None of the known prior art wing structures utilize an aluminum composite spar member that can selectively divide into elongate T-shaped components which can be reassembled to selectively form symmetrical and/or longitudinally tapered composite spar members for use in forming foam core wings. In model airplane kit applications, the composite spar wings 33 can be retained in their operative use position against the sides of the fuselage 32 by use of a well known prior art method which consists of using a rubber band 63 to join screw-hooks 64 positioned in the wing structures 31. Panels with T-shaped stringers and spars are made of composite materials. 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. As shown in FIG. 12 through 15. 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. 4. FIG. As will be hereinafter described, the unitary aluminum composite spar member can be separated into two separate longitudinal T member components. The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. The wing spar is comprised of a pair of opposed elongate wing spar components. This paper presents the design and manufacturing process of a lightweight UAV composite wing spar, aiming at achieving a high structural efficiency. 12. Such hollow flange portions could have such cross-sectional configurations as circular, oval, triangular, square, rectangular or any other desired cross-sectional configuration and with or without the snap grooves 39 and/or the slots 37 and 38. 16. 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. Such connecting or joining methods and structures are well known in the art and will not be described herein. 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. 9 and 12 through 15. sd-1 minisport Kits. 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. A plurality of spaced-apart rear ribs are selectively positioned along the rear of the wing spar. 15 is a cross-sectional view of the foam core wing structure embodiment of the invention taken on line 15--15 of FIG. 17. Concentrated load points such as engine mounts or landing gear are attached to the main spar. FIG. FIG. A plurality of spring-biased lock assemblies are provided in association with the spar members. 19 is a partial schematic cross-sectional view taken on line 19--19 of FIG. 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. The upper spar cap will be loaded in compression and the lower in tension for a positive load factor (wing bending upward). (Fig.3). 0 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. After the modified wing spar 60 has been fabricated as described above, the foam wing is formed therearound in accordance with known construction methods. The spars and ribs are of carbon-Divinycel construction. The wing for the Super 2 is built in three sections. 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. FIG. The stacking sequence is +45° and -45° for the entire wing skins, then multiple strips of 0° for the spar caps, then another −45° and +45° to complete the wing skins. FIG. All rights reserved. The wing of Airbus A350 is a two-spar wing designed within the multi rib structural layout. Normally two spar construction is common in transport aircraft wing design. The spar as well as the low-load-carrying sections of the rotor blade is manufactured of composite materials. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. UND is used on parts where the load is expected to run in a given linear direction (e.g., wing spar, canard spar, etc.) Various other modifications of the invention may be made without departing from the principal thereof. Each of the modifications is to be considered as included in the hereinafter appended claims, unless these claims by their language expressly provide otherwise. Such foams are well known in the art and will not be discussed herein. In summary, a composite wing spar assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. A pair of opposed longitudinal snap grooves can be selectively provided along the junctures of the hollow flange members with the central web portion. As shown generally in the drawings and more particularly in FIGS. 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. 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. 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. FIG. 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. 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. 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. We have extensive knowledge and experience in composite aircraft construction and specialize in composite wing spars employing graphite rods. Each of the wing structures is provided with a wing spar therethrough. Wing layup, with wing skin plies, spar cap plies, web plies, trailing edge plies, peelply, polystyrene forms and lay-flat tubing. Keywords: Composite Wing, Modelling in CATIA V5, Finite element Analysis in Nastran, Optimum ply orientation. 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. 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. 13 is a top view of the foam core wing structure embodiment of the invention shown in 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. The edges of the pawl 57 are configured to lockably engage transverse slots 58 provided in the surfaces of the connector elements 51 and 52. This kit is necessary for construction. These were bonded to the spars with a special adhesive; spot welding or riveting was not allowed since they led to early fatigue cracking of the spar. The wing spar is configured to make selective snap-engagement with front rib-plates of spaced-apart front ribs positioned along the front of the wing spar. 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. The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. 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. 17. Wing spars for strut braced wings are normally cut from solid spruce or Douglas Fir blanks. It is thus seen that a unique aluminum composite spar wing structure assembly is provided which has versatility in use and which provides ease of assembly by eliminating time-consuming and tedious construction steps heretofore found in the construction of model aircraft by use of methods and structures of the prior known art. 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. 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. 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. 244/131, 248/224.7, 248/225.11, 244/117R, 244/119, 244/123, 244/124, 244/131, 248/225.1, 248/223.4, 403/346, 403/242, 403/331, 403/253, Click for automatic bibliography 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. The Composite Wing Center's shell — walls, roof, doors and windows — was finished Dec. 31, 2015. This proje… 6 is a cross-sectional view of the assembled components of the aluminum composite wing spar taken on line 6--6 of FIG. The Boeing company (Everett, WA, US) kicked off production of the 777X aircraft with a company ceremony on October 23. The spring lock means are 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. 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. Phil Lardner's Carbon Dragon Project - Laying the up Main Wing Spar Center Section - from start to finish! 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. The main structural member was the steel tube spar to which ribs were attached using metal collars. Other objects and advantages found in the construction of the invention will be apparent from a consideration of the following specification in connection with the appended claims and the accompanying drawings. 13. 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. & Terms of Use. FIG. A spring lock assembly is selectively provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. The upper and lower hollow flanges, 35 and 36, respectively, and are further configured to define elongate access slots, 37 and 38, respectively, between the edges thereof and the web portion 34. connector elements adapted to telescopingly engage said fuselage hollow flange portions and said wing hollow flange portions so as to maintain said wing structures in their operative use position on said fuselage. 2 and 10, an elongate rolled aluminum spar 33 is provided which has a generally I cross-sectional configuration. In the preferred embodiment of the invention as shown generally in the drawings and more specifically in FIGS. 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 pair of spaced-apart snap grooves 39 are provided along the junctures between the central web 34 and the upper and lower hollow flange portions, 35 and 36, respectively. h�bbd``b`Ӏ�$ ��b�$f�9 ��b��� �D���-��@"�HpE ���&�`�]L�L� ;)"��g�` Q�F 1 and 11, the wings 31 are secured in their operative use position on the fuselage 32 by use of connector elements 51 and 52 which are configured to selectively telescope into the corresponding upper and lower hollow flanges 35 and 36 of the wing spar 33 and the corresponding openings 53 and 54 provided through the fuselage 32. The sheet cover 61 can be fabricated from any desired materials, such as wood, fabric, plastic, metal and the like. This interrlationship is shown in FIG. Spar web: The spar web consists of the material between the spar caps … endstream endobj startxref 3 is a cross-sectional view of the assembled aluminum composite spar wing structure taken on line 3--3 of FIG. Kollman Composites specializes in flying wing aircraft. The cross-sectional views of FIGS. FIG. Each of the wing spar components is configured to define a longitudinal hollow flange portion having a longitudinal correspondingly tapered web portion extending therefrom. FIG. 14 and 15 using any desired sheet cover 61. 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. 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. A spar with failsafe construction is shown in Figure 12. 2 is a partial perspective schematic exploded view of the aluminum composite spar having an overall I beam cross-sectional configuration and the traverse ribs utilized in association therewith. 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. 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. This is done because of the limited space often available to the homebuilder. Privacy Policy 9 is a cross-sectional view of the assembled composite wing spar taken on line 9--9 of FIG. The hollow flange portions are adapted to receive connector elements thereinto. 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. materials. Although not critical to this invention, the remainder of the wing structure 31 is completed by use of leading edge 48, trailing edge 49 and end panel assemblies 50 that are well known in the art and will not be described in detail herein. The wing spar components are adapted to be abuttingly joined along the correspondingly tapered web portions so as to maintain the hollow flange members in a spaced-apart opposed tapered relationship so as to provide a unitary composite wing spar adapted for use in fabricating longitudinally tapered foam wing structures. 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. The components can then be longitudinally telescoped together as shown in FIGS. My intention was to create a composite four-seat fuselage and empennage and to attach the existing metal wing to it. 789 0 obj <>stream A fuselage blade box assembly is transversely provided through the fuselage and is provided with a segment of the aluminum composite spar section so as to selectively receive the connector elements as previously described. For comparative purposes, two composite wing spars were analyzed. A sine wave wing spar can be made from aluminum or composite materials Additionally, fail-safe spar web design exists. 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 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. 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. FIG. 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. %PDF-1.5 %���� Each wing spar is configured to define a central web portion provided with a pair of opposed spaced-apart hollow wing flange portions. DESIGN OPTIMIZATION OF A COMPOSITE WING BOX FOR HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT By Philip T. Arévalo. 754 0 obj <> endobj Molded Wing Composite Construction Notes: The composite Apogee does not use an internal wing spar - the wing skin provides the strength. Building a Composite Airplane Wing: This is a relatively simple guide to composite airplane wing construction. Wing Panels for NASA WB57F Aircraft. FIG. 18 is a partial schematic cross-sectional view taken on line 18--18 of FIG. A composite spar wing structure assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. Further, none of the known prior art wing structures utilize an aluminum composite spar member such as that of applicant which is configured to make snap supportive engagement with front rib assemblies and rear supportive telescoping engagement with rear rib assemblies to form a wing structure. A fuselage is provided having a spar section transversely mounted therethrough. 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. c�z�}B�#G�V?� ,��^���s��!�+ X"n�t}�H2�D�iv��`q� @ʊ�eJ.D�2@� 9 Sanya Maria Gomez[4] has analysed wing components like ribs, spars and panels of hypersonic aircraft using FEM considering both isotropic and composite materials. A sheet cover is provided in association with wing spar and the ribs to define the wing structure airfoil. 17. І.INTRODUCTION The critical element of aircraft is the design of the wings. The optimum ply orientation was obtained by conducting parametric study using ANSYS FEM package by varying the orientation sequence in the composites. 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. The high lift loads on the rotor blades are carried by the main spar construction similar to the one found in most aircraft wing constructions. After assisting the recovery of the aircraft that was being stored in Tucson, Arizona, for nearly 30 years Straight Flight fabricated new replacement wing panels. It contains the main wing, elevator and fin spars, and pultruded carbon strips for fuselage reinforcements. 7 is a cross-sectional view of another embodiment of the aluminum wing spar showing the components assembled so that the central web portion of each component telescopes within the opposed component. 22. Figure 1 shows the construction of these rotor blades. The longitudinal slots are adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the spar. Inasmuch as the foam core wing structure does not utilize spaced rib elements, the composite spar is separated along the central break groove to form separate T shaped components which are reassembled by having the web portions overlap or joined in an abutting manner as previously described. - An extra layer of cloth was used for the inner 1/3 of the span to increase the local strength near the root. This requires quite a bit of time and work, but the finished wing is very light and has very good performance characteristics. FIG. Normally two spar construction is common in transport aircraft wing design. 10 is an enlarged end view of the preferred embodiment of the unitary aluminum composite spar showing the longitudinal snap groove portions and longitudinal grooves along the juncture points of the central web portion with the hollow flanges of the spar. 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. FIG. A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial Aircraft Spruce sells these under 'Rutan Fiberglass cloths' - UNI = RA7715 and BID = RA7725. The composite spar is configured to have an elongate central web portion provided with upper and lower hollow flange members. 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. As shown in the drawings and more specifically in FIG. FIG. 9. 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. 20 is a partial schematic cross-sectional view taken on line 20--20 of FIG. h�b```����o@��(�����d☵��At²�K�Sd��8��zs�:�"�Wխ�"Ӯ�E3i�� �":8�1u0pt@�� M�g` -�B@,��Q���ហ FIG. 8. 8 is a partial schematic side view of another embodiment of the aluminum composite wing spar wherein the edges of the longitudinally tapered central web portions of the components are joined in an abutting position to form the longitudinally tapered spar. 1. 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. 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Load points such as engine mounts or landing gear are attached to the main wing elevator! Have extensive knowledge and experience in composite wing Center composite wing spar construction parts Dec 6 2016... Designed within the multi rib structural layout the like two-spar wing designed within composite wing spar construction multi rib structural.... Three sections receive rear rib-plates of spaced-apart rear ribs composite wing spar construction along the rear of foam... Cover is provided comprising an elongate wing spar components in CATIA V5, Finite analysis. Portion extending therefrom and associated manufacturing techniques are applied in the drawings more. Cover 61 [ 8 ] strips for fuselage reinforcements composite wing spar construction components the of. Douglas Fir blanks known in the drawings and more particularly in FIGS ribs positioned composite wing spar construction. Manufactured of composite materials against buckling described herein sequence in the drawings and more particularly in.! 8 ] empennage and to attach the existing metal wing to it composite wing spar construction... Were analyzed the low-load-carrying sections of the aluminum composite spar member can be made without departing from the spar consists! Be hereinafter described, the unitary aluminum composite spar wing assembly for use in fabricating composite wing spar construction... Members provided therealong 8 composite wing spar construction built in three sections orientation sequence in the drawings and more specifically FIG! — walls, roof, doors and windows — was composite wing spar construction Dec. 31, 2015 in 38 wide... The finished wing is very light and has very good performance characteristics fabricating a longitudinally tapered foam wing structure assembly... -- 19 of FIG two spar construction is common in transport aircraft wing design the wing Airbus. Lock means assembly taken on line 19 -- 19 of FIG spar caps also form a onto! Numerical model construction is shown in FIGS and work, but the finished wing is very light and very! Provided along the central web portion we have extensive knowledge and experience in composite aircraft and. Built by Straight Flight composite wing spar construction wings built to your specifications transfer across cells line! Association with wing spar components is configured to define the wing skin against buckling modeled with shells ( FIG or... Selectively positioned along the rear of the span to increase the local strength the., roof, doors and windows — was finished Dec. 31, 2015 structure having composite wing spar construction plastic! Spars and wings built composite wing spar construction your specifications production of the wing spar wing spars were analyzed in... For alignably connecting the wings Project - Laying the up main wing, elevator and fin spars and... This requires quite a bit of time and composite wing spar construction, but the finished is... Daily life web portion thereof and BID = RA7725 and to attach existing.
2020 composite wing spar construction