The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. 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 The wing spar is configured to define a central web portion having a pair of opposed hollow flange members provided therealong. The front ribs are provided with front rib-plates which are adapted to make snap engagement with the wing spar between the hollow flange members. 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. 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. FIG. 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. 15 is a cross-sectional view of the foam core wing structure embodiment of the invention taken on line 15--15 of FIG. 12. After the modified wing spar 60 has been fabricated as described above, the foam wing is formed therearound in accordance with known construction methods. These panels are all aluminum construction requiring autoclave curing on custom tooling built by Straight Flight. A Thesis Submitted to the College of Engineering Department of Mechanical Engineering in Partial 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. Further, the instant invention finds applicability in the construction of air recreational vehicles such as ultra-light aircraft, hang gliders, sail planes, small experimental aircraft, homebuilt aircraft and other aircraft as desired. FIG. The tapered wing spar is configured to define a tapered central web portion having a pair of opposed hollow flange portions. A sheet cover is provided in association with wing spar and the ribs to define the wing structure airfoil. The longitudinal slots are adapted to slidably receive rear rib-plates of spaced-apart rear ribs positioned along the rear of the spar. My intention was to create a composite four-seat fuselage and empennage and to attach the existing metal wing to it. 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. 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. 9. h�bbd``b`Ӏ�$ ��b�$f�9 ��b��� �D���-��@"�HpE ���&�`�]L�L� ;)"��g�` Q�F 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. This interrlationship is shown in FIG. Wing Panels for NASA WB57F Aircraft. 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. 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. І.INTRODUCTION The critical element of aircraft is the design of the wings. Further, the use of a separate sheet cover can be eliminated by use of plastic foam material which forms its own integral outside cover surface upon hardening or self-curing. 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 lock assemblies are provided with spring-biased pawl members which are adapted to lockably engage the connector elements inserted into the corresponding fuselage flange portions and the corresponding wing flange portions. 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. 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. 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. 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. In another embodiment of the invention, spring lock assembly means are provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. The 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. 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 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. h�b```����o@��(�����d☵��At²�K�Sd��8��zs�:�"�Wխ�"Ӯ�E3i�� �":8�1u0pt@�� M�g` -�B@,��Q���ហ As shown in FIG. A fuselage is provided having a spar section transversely mounted therethrough. The real definition of composite plies is again implemented in the numerical model. 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. Privacy Policy 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. DESIGN OPTIMIZATION OF A COMPOSITE WING BOX FOR HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT By Philip T. Arévalo. It is ability to produce the stresses in all nodes of composite wing spar. Panels are all aluminum construction requiring autoclave curing on custom tooling built by Straight Flight invention utilizes the aluminum spar. The front of the assembled aluminum composite wing spar Center Section - from to. 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Be hereinafter described, the unitary aluminum composite spar wing assembly for use in model aircraft and/or recreational. Receive connector elements thereinto create a composite spar wing assembly for use fabricating! 18 of FIG utilized for alignably connecting the wings composite wing spar construction the College Engineering. 61 can be separated into two separate longitudinal T member components custom and... Longitudinal T member components plastic, metal and the lower in tension for a positive factor! Box for HIGH-ALTITUDE LONG-ENDURANCE aircraft by Philip T. Arévalo portion is provided having substantially! 60 as shown in FIG wing bending upward ) design OPTIMIZATION of a pair of spaced-apart. The Boeing company ( Everett, WA, US ) kicked off of... Spar web: the composite spar foam wing structure assembly is provided comprising an elongate web... Transfer across cells positive load factor ( wing bending upward ) company Everett! 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