| 摘要 |
A composite spar wing assembly for use in model aircraft and/or air recreational vehicle construction. 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 spar is configured to have an elongate central web portion provided with upper and lower hollow flange members. The composite wing structures are connected to or through an aircraft fuselage by use of elongate spaced-apart connector elements which telescope respectively into the upper and lower hollow flange portions of the composie spar. A fuselage blade box assembly is selectively transversely provided through the fuselage and is provided with a segment of the composite spar so as to selectively receive the connector elements as previously described. A spring lock assembly is selectively provided in association with the aforementioned fuselage blade box assembly and the wing spar elements. 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. 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.
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