stream Normally two spar construction is common in transport aircraft wing design. 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. The components can then be longitudinally telescoped together as shown in FIGS. A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial The wing for the Super 2 is built in three sections. 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. 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. Another embodiment of the invention utilizes the aluminum composite spar to form wing structure having an expanded plastic foam core. 9 is a cross-sectional view of the assembled composite wing spar taken on line 9--9 of FIG. 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. The sheet cover 61 can be fabricated from any desired materials, such as wood, fabric, plastic, metal and the like. None of the known prior art wing structures utilize an aluminum composite spar member such as that of applicant which has an I cross-sectional configuration comprised of a central web portion having opposed substantially rectangular hollow flange portions. & Terms of Use. 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 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. 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. sd-1 minisport Kits. 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. 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. 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. %%EOF 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. FIG. A composite spar wing structure assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. 754 0 obj <> endobj 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. The composite spar is configured to have an elongate central web portion provided with upper and lower hollow flange members. The hollow flange portions are adapted to receive connector elements thereinto. materials. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. 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. Figure 1 shows the construction of these rotor blades. 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. As shown in FIG. If a model aircraft kit is being assembled, the foregoing components are generally fabricated from balsa and spruce wood and are generally secured in their operative use assembled positions by appropriate glues and/or resins. 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. Privacy Policy Building a Composite Airplane Wing: This is a relatively simple guide to composite airplane wing construction. 17 is a partial schematic top view of the embodiment of the invention shown in FIG. 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. 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. 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 Another embodiment or end use of the modified composite wing spar 33 consists of its use in the foam wing structure 59 shown in FIGS. 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. The tapered wing spar is configured to define a tapered central web portion having a pair of opposed hollow flange portions. FIG. 17. 6 is a cross-sectional view of the assembled components of the aluminum composite wing spar taken on line 6--6 of FIG. Although the spars are cut from a single slab, they can be laminated of two or more pieces when perfect spar blanks of the proper length and width are difficult to obtain. 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. After the modified wing spar 60 has been fabricated as described above, the foam wing is formed therearound in accordance with known construction methods. FIG. DESIGN OPTIMIZATION OF A COMPOSITE WING BOX FOR HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT By Philip T. Arévalo. 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. It contains the main wing, elevator and fin spars, and pultruded carbon strips for fuselage reinforcements. 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. Several layouts and associated manufacturing techniques are applied in the rotor blade industry. an elongate wing spar having a substantially I cross-sectional configuration, said wing spar defining a central web portion having a pair of opposed hollow flange members provided therealong, said wing spar configured to make snap-engagement with front rib-plates of spaced-apart front ribs positioned along the front of said wing spar, said wing spar defining a pair of opposed longitudinal access slots at the junctures between each of said hollow flange members and said central web portion, said longitudinal access slots adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the said spar; a plurality of said spaced-apart front ribs positioned along the front of said wing spar, said front ribs provided with said front rib-plates which are adapted to make snap engagement with said wing spar between said hollow flange members; and. 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. The ribs are made of aluminum-lithium alloy [8]. 18 is a partial schematic cross-sectional view taken on line 18--18 of FIG. The aluminum composite spar member is also selectively provided with an elongate break groove along the central portion of the web portion thereof. FIG. A pair of opposed longitudinal snap grooves can be selectively provided along the junctures of the hollow flange members with the central web portion. 6). FIG. 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. Thereafter, the components are joined along the web portions thereof to form a composite wing spar 60 as shown in FIGS. FIG. 12. 16 is a schematic front cross-sectional view of another embodiment of the invention showing selected means for mounting the wings on the fuselage. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. Although the preferred embodiment of the spar 33 is fabricated as a rolled aluminum structure, it is within the scope of the invention that the spar 33 be fabricated as an extruded plastic structure or by use of any other metal or construction material depending on the specific intended end use of the spar 33, i.e. 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. We have extensive knowledge and experience in composite aircraft construction and specialize in composite wing spars employing graphite rods. 0 A fuselage is provided having a spar section transversely mounted therethrough. This composite wing spar with circular and rectangular cutouts was used in the current analysis. 12 through 15. Each of the wing spar components is configured to define a longitudinal hollow flange portion having a longitudinal correspondingly tapered web portion extending therefrom. 9 and 12 through 15. (Fig.3). FIG. Phil Lardner's Carbon Dragon Project - Laying the up Main Wing Spar Center Section - from start to finish! State of the art 777X Composite Wing Center completes parts Dec 6, 2016 | Boeing Commercial. 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. Each wing spar is configured to define a central web portion provided with a pair of opposed spaced-apart hollow wing flange portions. 17. Available sd-1 minisport kits include: The Basic sd-1 minisport Kit. Molded Wing Composite Construction Notes: The composite Apogee does not use an internal wing spar - the wing skin provides the strength. 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. 12. 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. Wing Panels for NASA WB57F Aircraft. FIG. The longitudinal slots are adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the spar. 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. In addition to our line of aircraft and wings, we offer custom spars and wings built to your specifications. 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. 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. The wing spar is comprised of a pair of opposed elongate wing spar components. My intention was to create a composite four-seat fuselage and empennage and to attach the existing metal wing to it. 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 spar with failsafe construction is shown in Figure 12. FIG. 8. This kit is necessary for construction. Various other modifications of the invention may be made without departing from the principal thereof. This paper presents the design and manufacturing process of a lightweight UAV composite wing spar, aiming at achieving a high structural efficiency. 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. The main structural member was the steel tube spar to which ribs were attached using metal collars. 9. 22. FIG. FIG. 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. Concentrated load points such as engine mounts or landing gear are attached to the main spar. 22 is a partial schematic cross-sectional view of the spring lock means assembly taken on line 22--22 of FIG. This requires quite a bit of time and work, but the finished wing is very light and has very good performance characteristics. A plurality of spring-biased lock assemblies are provided in association with the spar members. 13. This proje… 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. Aircraft Spruce sells these under 'Rutan Fiberglass cloths' - UNI = RA7715 and BID = RA7725. 1 is a perspective schematic exploded assembly view of an aircraft utilizing the aluminum composite spar wing structure. This is done because of the limited space often available to the homebuilder. & Terms of Use. 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. For comparative purposes, two composite wing spars were analyzed. endstream endobj startxref - An extra layer of cloth was used for the inner 1/3 of the span to increase the local strength near the root. UND is used on parts where the load is expected to run in a given linear direction (e.g., wing spar, canard spar, etc.) The Composite Wing Center's shell — walls, roof, doors and windows — was finished Dec. 31, 2015. 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. 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 foam body wing portion is provided which is configured to encase and be supported by the longitudinally tapered composite wing spar. 13 is a top view of the foam core wing structure embodiment of the invention shown in FIG. The spar as well as the low-load-carrying sections of the rotor blade is manufactured of composite materials. 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 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 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. 19 is a partial schematic cross-sectional view taken on line 19--19 of FIG. 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. 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. 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 real definition of composite plies is again implemented in the numerical model. 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. 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. A sheet cover is provided in association with wing spar and the ribs to define the wing structure airfoil. A spring lock assembly is selectively provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. 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. Thus positioned, the rear ribs 34 cooperate with the spar 33 and associated cover sheet 46 to form the rear airfoil configuration of the wing structure 31. The cross-sectional views of FIGS. 20 is a partial schematic cross-sectional view taken on line 20--20 of FIG. 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 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. endstream endobj 755 0 obj <>/Metadata 56 0 R/Outlines 80 0 R/PageLayout/OneColumn/Pages 752 0 R/StructTreeRoot 105 0 R/Type/Catalog>> endobj 756 0 obj <>/ExtGState<>/Font<>/XObject<>>>/Rotate 0/StructParents 0/Tabs/S/Type/Page>> endobj 757 0 obj <>stream FIG. 13. 2 and 10, an elongate rolled aluminum spar 33 is provided which has a generally I cross-sectional configuration. 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. FIG. A sine wave wing spar can be made from aluminum or composite materials Additionally, fail-safe spar web design exists. © 2004-2020 FreePatentsOnline.com. Panels with T-shaped stringers and spars are made of composite materials. Such foams are well known in the art and will not be discussed herein. The wing is then completed to the configuration shown in FIGS. FIG. 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. 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 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. 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. The spar caps also form a boundary onto which wing skin is attached and support the wing skin against buckling. The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. Wing layup, with wing skin plies, spar cap plies, web plies, trailing edge plies, peelply, polystyrene forms and lay-flat tubing. A composite wing spar assembly is provided which is adapted for use in fabricating a longitudinally tapered foam wing structure. 4. Construction on the 1.3 million-square-foot (121,000-square-meter) building continues, as it will for the next 18 months, with the roll-in of new tools and equipment. 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. 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. 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. in composite wing spar under tensile load. 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. 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. The optimum ply orientation was obtained by conducting parametric study using ANSYS FEM package by varying the orientation sequence in the composites. 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. 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. It is ability to produce the stresses in all nodes of composite wing spar. This interrlationship is shown in FIG. h�b```����o@��(�����d☵��At²�K�Sd��8��zs�:�"�Wխ�"Ӯ�E3i�� �":8�1u0pt@�� M�g` -�B@,��Q���ហ The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. 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. h�bbd``b`Ӏ�$ ��b�$f�9 ��b��� �D���-��@"�HpE ���&�`�]L�L� ;)"��g�` Q�F 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. 11 is a schematic exploded perspective view showing one embodiment of the connector element means utilized for alignably connecting the wings to the fuselage. 1. 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. The Boeing company (Everett, WA, US) kicked off production of the 777X aircraft with a company ceremony on October 23. A composite spar wing structure aircraft assembly is provided which comprises a pair of opposed spaced-apart wing structures. As shown generally in the drawings and more particularly in FIGS. The use of composites in aircraft structures is steadily increased and now become part of daily life. 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. 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. 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. As shown generally in the drawings and more particularly in FIGS. Outboard Spar construction. Normally two spar construction is common in transport aircraft wing design. 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. Such connecting or joining methods and structures are well known in the art and will not be described herein. 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. Kids Spa Party, Brown Rice Mushroom Casserole, Why Do Slugs Climb Walls At Night, Adwoa Beauty Sale, What Is The Duty Of A Politician, Foreclosures In Cooper City, Fl, How To Install Purlins, Stihl Chainsaw Clutch Stuck, Sample Sentence For Virtue, Barbary Dove Nz, Metal Storage Sheds For Sale, " /> stream Normally two spar construction is common in transport aircraft wing design. 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. The components can then be longitudinally telescoped together as shown in FIGS. A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial The wing for the Super 2 is built in three sections. 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. 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. Another embodiment of the invention utilizes the aluminum composite spar to form wing structure having an expanded plastic foam core. 9 is a cross-sectional view of the assembled composite wing spar taken on line 9--9 of FIG. 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. The sheet cover 61 can be fabricated from any desired materials, such as wood, fabric, plastic, metal and the like. None of the known prior art wing structures utilize an aluminum composite spar member such as that of applicant which has an I cross-sectional configuration comprised of a central web portion having opposed substantially rectangular hollow flange portions. & Terms of Use. 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 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. 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. sd-1 minisport Kits. 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. 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. 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. %%EOF 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. FIG. A composite spar wing structure assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. 754 0 obj <> endobj 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. The composite spar is configured to have an elongate central web portion provided with upper and lower hollow flange members. The hollow flange portions are adapted to receive connector elements thereinto. materials. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. 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. Figure 1 shows the construction of these rotor blades. 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. As shown in FIG. If a model aircraft kit is being assembled, the foregoing components are generally fabricated from balsa and spruce wood and are generally secured in their operative use assembled positions by appropriate glues and/or resins. 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. Privacy Policy Building a Composite Airplane Wing: This is a relatively simple guide to composite airplane wing construction. 17 is a partial schematic top view of the embodiment of the invention shown in FIG. 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. 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. 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 Another embodiment or end use of the modified composite wing spar 33 consists of its use in the foam wing structure 59 shown in FIGS. 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. The tapered wing spar is configured to define a tapered central web portion having a pair of opposed hollow flange portions. FIG. 17. 6 is a cross-sectional view of the assembled components of the aluminum composite wing spar taken on line 6--6 of FIG. Although the spars are cut from a single slab, they can be laminated of two or more pieces when perfect spar blanks of the proper length and width are difficult to obtain. 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. After the modified wing spar 60 has been fabricated as described above, the foam wing is formed therearound in accordance with known construction methods. FIG. DESIGN OPTIMIZATION OF A COMPOSITE WING BOX FOR HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT By Philip T. Arévalo. 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. It contains the main wing, elevator and fin spars, and pultruded carbon strips for fuselage reinforcements. 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. Several layouts and associated manufacturing techniques are applied in the rotor blade industry. an elongate wing spar having a substantially I cross-sectional configuration, said wing spar defining a central web portion having a pair of opposed hollow flange members provided therealong, said wing spar configured to make snap-engagement with front rib-plates of spaced-apart front ribs positioned along the front of said wing spar, said wing spar defining a pair of opposed longitudinal access slots at the junctures between each of said hollow flange members and said central web portion, said longitudinal access slots adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the said spar; a plurality of said spaced-apart front ribs positioned along the front of said wing spar, said front ribs provided with said front rib-plates which are adapted to make snap engagement with said wing spar between said hollow flange members; and. 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. The ribs are made of aluminum-lithium alloy [8]. 18 is a partial schematic cross-sectional view taken on line 18--18 of FIG. The aluminum composite spar member is also selectively provided with an elongate break groove along the central portion of the web portion thereof. FIG. A pair of opposed longitudinal snap grooves can be selectively provided along the junctures of the hollow flange members with the central web portion. 6). FIG. 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. Thereafter, the components are joined along the web portions thereof to form a composite wing spar 60 as shown in FIGS. FIG. 12. 16 is a schematic front cross-sectional view of another embodiment of the invention showing selected means for mounting the wings on the fuselage. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. Although the preferred embodiment of the spar 33 is fabricated as a rolled aluminum structure, it is within the scope of the invention that the spar 33 be fabricated as an extruded plastic structure or by use of any other metal or construction material depending on the specific intended end use of the spar 33, i.e. 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. We have extensive knowledge and experience in composite aircraft construction and specialize in composite wing spars employing graphite rods. 0 A fuselage is provided having a spar section transversely mounted therethrough. This composite wing spar with circular and rectangular cutouts was used in the current analysis. 12 through 15. Each of the wing spar components is configured to define a longitudinal hollow flange portion having a longitudinal correspondingly tapered web portion extending therefrom. 9 and 12 through 15. (Fig.3). FIG. Phil Lardner's Carbon Dragon Project - Laying the up Main Wing Spar Center Section - from start to finish! State of the art 777X Composite Wing Center completes parts Dec 6, 2016 | Boeing Commercial. 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. Each wing spar is configured to define a central web portion provided with a pair of opposed spaced-apart hollow wing flange portions. 17. Available sd-1 minisport kits include: The Basic sd-1 minisport Kit. Molded Wing Composite Construction Notes: The composite Apogee does not use an internal wing spar - the wing skin provides the strength. 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. 12. 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. Wing Panels for NASA WB57F Aircraft. FIG. The longitudinal slots are adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the spar. 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. In addition to our line of aircraft and wings, we offer custom spars and wings built to your specifications. 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. 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. The wing spar is comprised of a pair of opposed elongate wing spar components. My intention was to create a composite four-seat fuselage and empennage and to attach the existing metal wing to it. 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 spar with failsafe construction is shown in Figure 12. FIG. 8. This kit is necessary for construction. Various other modifications of the invention may be made without departing from the principal thereof. This paper presents the design and manufacturing process of a lightweight UAV composite wing spar, aiming at achieving a high structural efficiency. 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. The main structural member was the steel tube spar to which ribs were attached using metal collars. 9. 22. FIG. FIG. 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. Concentrated load points such as engine mounts or landing gear are attached to the main spar. 22 is a partial schematic cross-sectional view of the spring lock means assembly taken on line 22--22 of FIG. This requires quite a bit of time and work, but the finished wing is very light and has very good performance characteristics. A plurality of spring-biased lock assemblies are provided in association with the spar members. 13. This proje… 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. Aircraft Spruce sells these under 'Rutan Fiberglass cloths' - UNI = RA7715 and BID = RA7725. 1 is a perspective schematic exploded assembly view of an aircraft utilizing the aluminum composite spar wing structure. This is done because of the limited space often available to the homebuilder. & Terms of Use. 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. For comparative purposes, two composite wing spars were analyzed. endstream endobj startxref - An extra layer of cloth was used for the inner 1/3 of the span to increase the local strength near the root. UND is used on parts where the load is expected to run in a given linear direction (e.g., wing spar, canard spar, etc.) The Composite Wing Center's shell — walls, roof, doors and windows — was finished Dec. 31, 2015. 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. 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 foam body wing portion is provided which is configured to encase and be supported by the longitudinally tapered composite wing spar. 13 is a top view of the foam core wing structure embodiment of the invention shown in FIG. The spar as well as the low-load-carrying sections of the rotor blade is manufactured of composite materials. 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 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 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. 19 is a partial schematic cross-sectional view taken on line 19--19 of FIG. 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. 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. 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 real definition of composite plies is again implemented in the numerical model. 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. 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. A sheet cover is provided in association with wing spar and the ribs to define the wing structure airfoil. A spring lock assembly is selectively provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. 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. Thus positioned, the rear ribs 34 cooperate with the spar 33 and associated cover sheet 46 to form the rear airfoil configuration of the wing structure 31. The cross-sectional views of FIGS. 20 is a partial schematic cross-sectional view taken on line 20--20 of FIG. 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 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. endstream endobj 755 0 obj <>/Metadata 56 0 R/Outlines 80 0 R/PageLayout/OneColumn/Pages 752 0 R/StructTreeRoot 105 0 R/Type/Catalog>> endobj 756 0 obj <>/ExtGState<>/Font<>/XObject<>>>/Rotate 0/StructParents 0/Tabs/S/Type/Page>> endobj 757 0 obj <>stream FIG. 13. 2 and 10, an elongate rolled aluminum spar 33 is provided which has a generally I cross-sectional configuration. 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. FIG. A sine wave wing spar can be made from aluminum or composite materials Additionally, fail-safe spar web design exists. © 2004-2020 FreePatentsOnline.com. Panels with T-shaped stringers and spars are made of composite materials. Such foams are well known in the art and will not be discussed herein. The wing is then completed to the configuration shown in FIGS. FIG. 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. 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 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. 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. The spar caps also form a boundary onto which wing skin is attached and support the wing skin against buckling. The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. Wing layup, with wing skin plies, spar cap plies, web plies, trailing edge plies, peelply, polystyrene forms and lay-flat tubing. A composite wing spar assembly is provided which is adapted for use in fabricating a longitudinally tapered foam wing structure. 4. Construction on the 1.3 million-square-foot (121,000-square-meter) building continues, as it will for the next 18 months, with the roll-in of new tools and equipment. 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. 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. 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. in composite wing spar under tensile load. 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. 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. The optimum ply orientation was obtained by conducting parametric study using ANSYS FEM package by varying the orientation sequence in the composites. 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. 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. It is ability to produce the stresses in all nodes of composite wing spar. This interrlationship is shown in FIG. h�b```����o@��(�����d☵��At²�K�Sd��8��zs�:�"�Wխ�"Ӯ�E3i�� �":8�1u0pt@�� M�g` -�B@,��Q���ហ The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. 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. h�bbd``b`Ӏ�$ ��b�$f�9 ��b��� �D���-��@"�HpE ���&�`�]L�L� ;)"��g�` Q�F 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. 11 is a schematic exploded perspective view showing one embodiment of the connector element means utilized for alignably connecting the wings to the fuselage. 1. 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. The Boeing company (Everett, WA, US) kicked off production of the 777X aircraft with a company ceremony on October 23. A composite spar wing structure aircraft assembly is provided which comprises a pair of opposed spaced-apart wing structures. As shown generally in the drawings and more particularly in FIGS. The use of composites in aircraft structures is steadily increased and now become part of daily life. 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. 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. 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. As shown generally in the drawings and more particularly in FIGS. Outboard Spar construction. Normally two spar construction is common in transport aircraft wing design. 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. Such connecting or joining methods and structures are well known in the art and will not be described herein. 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. Kids Spa Party, Brown Rice Mushroom Casserole, Why Do Slugs Climb Walls At Night, Adwoa Beauty Sale, What Is The Duty Of A Politician, Foreclosures In Cooper City, Fl, How To Install Purlins, Stihl Chainsaw Clutch Stuck, Sample Sentence For Virtue, Barbary Dove Nz, Metal Storage Sheds For Sale, " />

composite wing spar construction Posts

quarta-feira, 9 dezembro 2020

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 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 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. In the preferred embodiment of the invention as shown generally in the drawings and more specifically in FIGS. Each of the modifications is to be considered as included in the hereinafter appended claims, unless these claims by their language expressly provide otherwise. 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. The wing of Airbus A350 is a two-spar wing designed within the multi rib structural layout. 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 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. Privacy Policy Each of the wing structures is provided with a wing spar therethrough. c�z�}B�#G�V?� ,��^���s��!�+ X"n�t}�H2�D�iv��`q� @ʊ�eJ.D�2@� 9 789 0 obj <>stream Normally two spar construction is common in transport aircraft wing design. 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. The components can then be longitudinally telescoped together as shown in FIGS. A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial The wing for the Super 2 is built in three sections. 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. 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. Another embodiment of the invention utilizes the aluminum composite spar to form wing structure having an expanded plastic foam core. 9 is a cross-sectional view of the assembled composite wing spar taken on line 9--9 of FIG. 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. The sheet cover 61 can be fabricated from any desired materials, such as wood, fabric, plastic, metal and the like. None of the known prior art wing structures utilize an aluminum composite spar member such as that of applicant which has an I cross-sectional configuration comprised of a central web portion having opposed substantially rectangular hollow flange portions. & Terms of Use. 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 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. 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. sd-1 minisport Kits. 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. 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. 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. %%EOF 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. FIG. A composite spar wing structure assembly is provided comprising an elongate wing spar having a substantially I cross-sectional configuration. 754 0 obj <> endobj 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. The composite spar is configured to have an elongate central web portion provided with upper and lower hollow flange members. The hollow flange portions are adapted to receive connector elements thereinto. materials. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. 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. Figure 1 shows the construction of these rotor blades. 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. As shown in FIG. If a model aircraft kit is being assembled, the foregoing components are generally fabricated from balsa and spruce wood and are generally secured in their operative use assembled positions by appropriate glues and/or resins. 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. Privacy Policy Building a Composite Airplane Wing: This is a relatively simple guide to composite airplane wing construction. 17 is a partial schematic top view of the embodiment of the invention shown in FIG. 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. 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. 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 Another embodiment or end use of the modified composite wing spar 33 consists of its use in the foam wing structure 59 shown in FIGS. 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. The tapered wing spar is configured to define a tapered central web portion having a pair of opposed hollow flange portions. FIG. 17. 6 is a cross-sectional view of the assembled components of the aluminum composite wing spar taken on line 6--6 of FIG. Although the spars are cut from a single slab, they can be laminated of two or more pieces when perfect spar blanks of the proper length and width are difficult to obtain. 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. After the modified wing spar 60 has been fabricated as described above, the foam wing is formed therearound in accordance with known construction methods. FIG. DESIGN OPTIMIZATION OF A COMPOSITE WING BOX FOR HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT By Philip T. Arévalo. 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. It contains the main wing, elevator and fin spars, and pultruded carbon strips for fuselage reinforcements. 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. Several layouts and associated manufacturing techniques are applied in the rotor blade industry. an elongate wing spar having a substantially I cross-sectional configuration, said wing spar defining a central web portion having a pair of opposed hollow flange members provided therealong, said wing spar configured to make snap-engagement with front rib-plates of spaced-apart front ribs positioned along the front of said wing spar, said wing spar defining a pair of opposed longitudinal access slots at the junctures between each of said hollow flange members and said central web portion, said longitudinal access slots adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the said spar; a plurality of said spaced-apart front ribs positioned along the front of said wing spar, said front ribs provided with said front rib-plates which are adapted to make snap engagement with said wing spar between said hollow flange members; and. 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. The ribs are made of aluminum-lithium alloy [8]. 18 is a partial schematic cross-sectional view taken on line 18--18 of FIG. The aluminum composite spar member is also selectively provided with an elongate break groove along the central portion of the web portion thereof. FIG. A pair of opposed longitudinal snap grooves can be selectively provided along the junctures of the hollow flange members with the central web portion. 6). FIG. 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. Thereafter, the components are joined along the web portions thereof to form a composite wing spar 60 as shown in FIGS. FIG. 12. 16 is a schematic front cross-sectional view of another embodiment of the invention showing selected means for mounting the wings on the fuselage. A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. Although the preferred embodiment of the spar 33 is fabricated as a rolled aluminum structure, it is within the scope of the invention that the spar 33 be fabricated as an extruded plastic structure or by use of any other metal or construction material depending on the specific intended end use of the spar 33, i.e. 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. We have extensive knowledge and experience in composite aircraft construction and specialize in composite wing spars employing graphite rods. 0 A fuselage is provided having a spar section transversely mounted therethrough. This composite wing spar with circular and rectangular cutouts was used in the current analysis. 12 through 15. Each of the wing spar components is configured to define a longitudinal hollow flange portion having a longitudinal correspondingly tapered web portion extending therefrom. 9 and 12 through 15. (Fig.3). FIG. Phil Lardner's Carbon Dragon Project - Laying the up Main Wing Spar Center Section - from start to finish! State of the art 777X Composite Wing Center completes parts Dec 6, 2016 | Boeing Commercial. 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. Each wing spar is configured to define a central web portion provided with a pair of opposed spaced-apart hollow wing flange portions. 17. Available sd-1 minisport kits include: The Basic sd-1 minisport Kit. Molded Wing Composite Construction Notes: The composite Apogee does not use an internal wing spar - the wing skin provides the strength. 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. 12. 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. Wing Panels for NASA WB57F Aircraft. FIG. The longitudinal slots are adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the spar. 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. In addition to our line of aircraft and wings, we offer custom spars and wings built to your specifications. 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. 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. The wing spar is comprised of a pair of opposed elongate wing spar components. My intention was to create a composite four-seat fuselage and empennage and to attach the existing metal wing to it. 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 spar with failsafe construction is shown in Figure 12. FIG. 8. This kit is necessary for construction. Various other modifications of the invention may be made without departing from the principal thereof. This paper presents the design and manufacturing process of a lightweight UAV composite wing spar, aiming at achieving a high structural efficiency. 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. The main structural member was the steel tube spar to which ribs were attached using metal collars. 9. 22. FIG. FIG. 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. Concentrated load points such as engine mounts or landing gear are attached to the main spar. 22 is a partial schematic cross-sectional view of the spring lock means assembly taken on line 22--22 of FIG. This requires quite a bit of time and work, but the finished wing is very light and has very good performance characteristics. A plurality of spring-biased lock assemblies are provided in association with the spar members. 13. This proje… 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. Aircraft Spruce sells these under 'Rutan Fiberglass cloths' - UNI = RA7715 and BID = RA7725. 1 is a perspective schematic exploded assembly view of an aircraft utilizing the aluminum composite spar wing structure. This is done because of the limited space often available to the homebuilder. & Terms of Use. 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. For comparative purposes, two composite wing spars were analyzed. endstream endobj startxref - An extra layer of cloth was used for the inner 1/3 of the span to increase the local strength near the root. UND is used on parts where the load is expected to run in a given linear direction (e.g., wing spar, canard spar, etc.) The Composite Wing Center's shell — walls, roof, doors and windows — was finished Dec. 31, 2015. 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. 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 foam body wing portion is provided which is configured to encase and be supported by the longitudinally tapered composite wing spar. 13 is a top view of the foam core wing structure embodiment of the invention shown in FIG. The spar as well as the low-load-carrying sections of the rotor blade is manufactured of composite materials. 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 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 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. 19 is a partial schematic cross-sectional view taken on line 19--19 of FIG. 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. 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. 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 real definition of composite plies is again implemented in the numerical model. 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. 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. A sheet cover is provided in association with wing spar and the ribs to define the wing structure airfoil. A spring lock assembly is selectively provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. 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. Thus positioned, the rear ribs 34 cooperate with the spar 33 and associated cover sheet 46 to form the rear airfoil configuration of the wing structure 31. The cross-sectional views of FIGS. 20 is a partial schematic cross-sectional view taken on line 20--20 of FIG. 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 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. endstream endobj 755 0 obj <>/Metadata 56 0 R/Outlines 80 0 R/PageLayout/OneColumn/Pages 752 0 R/StructTreeRoot 105 0 R/Type/Catalog>> endobj 756 0 obj <>/ExtGState<>/Font<>/XObject<>>>/Rotate 0/StructParents 0/Tabs/S/Type/Page>> endobj 757 0 obj <>stream FIG. 13. 2 and 10, an elongate rolled aluminum spar 33 is provided which has a generally I cross-sectional configuration. 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. FIG. A sine wave wing spar can be made from aluminum or composite materials Additionally, fail-safe spar web design exists. © 2004-2020 FreePatentsOnline.com. Panels with T-shaped stringers and spars are made of composite materials. Such foams are well known in the art and will not be discussed herein. The wing is then completed to the configuration shown in FIGS. FIG. 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. 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 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. 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. The spar caps also form a boundary onto which wing skin is attached and support the wing skin against buckling. The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. Wing layup, with wing skin plies, spar cap plies, web plies, trailing edge plies, peelply, polystyrene forms and lay-flat tubing. A composite wing spar assembly is provided which is adapted for use in fabricating a longitudinally tapered foam wing structure. 4. Construction on the 1.3 million-square-foot (121,000-square-meter) building continues, as it will for the next 18 months, with the roll-in of new tools and equipment. 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. 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. 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. in composite wing spar under tensile load. 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. 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. The optimum ply orientation was obtained by conducting parametric study using ANSYS FEM package by varying the orientation sequence in the composites. 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. 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. It is ability to produce the stresses in all nodes of composite wing spar. This interrlationship is shown in FIG. h�b```����o@��(�����d☵��At²�K�Sd��8��zs�:�"�Wխ�"Ӯ�E3i�� �":8�1u0pt@�� M�g` -�B@,��Q���ហ The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. 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. h�bbd``b`Ӏ�$ ��b�$f�9 ��b��� �D���-��@"�HpE ���&�`�]L�L� ;)"��g�` Q�F 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. 11 is a schematic exploded perspective view showing one embodiment of the connector element means utilized for alignably connecting the wings to the fuselage. 1. 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. The Boeing company (Everett, WA, US) kicked off production of the 777X aircraft with a company ceremony on October 23. A composite spar wing structure aircraft assembly is provided which comprises a pair of opposed spaced-apart wing structures. As shown generally in the drawings and more particularly in FIGS. The use of composites in aircraft structures is steadily increased and now become part of daily life. 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. 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. 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. As shown generally in the drawings and more particularly in FIGS. Outboard Spar construction. Normally two spar construction is common in transport aircraft wing design. 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. Such connecting or joining methods and structures are well known in the art and will not be described herein. 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.

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