Wing spar of a compound wing aircraft

Abstract

The invention discloses a wing spar of a compound-wing aircraft, which comprises two transverse integral beams arranged horizontally opposite to each other, and a cross-type load-bearing beam for carrying bending and torsional moments is arranged between the two transverse integral beams. The interior of the cross-type load-bearing beam is a hollow structure, and the ends of the cross-type load-bearing beam are fixedly connected with two transverse integral beams; both ends of the two transverse integral beams are provided with an end rib for carrying bending and torsional moments. The two transverse integral beams are connected and fixed by two end ribs. The cross-type load-bearing beam has a hollow structure as a whole, which greatly reduces the structural weight of the wing. At the same time, the cross-type load-bearing beam greatly improves the resistance of the load-bearing beam Bending and torsional performance, the cross-type load-bearing beam is equipped with a water channel, which simply and effectively solves the problem of water storage and drainage inside the wing spar, and the addition of end ribs can obtain a lighter weight under the premise of determining a certain bending and torsional strength. the weight of.

Description

technical field [0001] The invention relates to the technical field of aircraft wing structures, in particular to a wing spar of a composite wing aircraft. Background technique [0002] At present, there are few researches on composite-wing UAVs at home and abroad, and the research on the fixed-wing spar form of composite-wing aircraft is even rarer. For the fixed-wing aircraft with the skin skeleton as the structural form: the wing spar is the main bearing structure of the aircraft, one of the important parts of the aircraft, and the premise to ensure the excellent performance of the aircraft. Wing spar, as the large main stress component of the aircraft wing, although it occupies a small proportion in the whole aircraft manufacturing, the wing spar of the aircraft, especially the wing spar of the large aircraft, has excellent performance due to its complex structure and stress condition. The technology of the spar appears crucial. [0003] The skin skeleton structure is ...

AI Technical Summary

Problems solved by technology

Among them, the mechanical properties of the beam-type wing are poor, the structure is prone to stress concentration, and the utilization rate of materials is not sufficient. For compound wing aircraft, the beam structure of the wing needs to have better bending and torsion performance , which is not available in the existing beam structure; relatively speaking, the monolithic structure improved on the basis of the beam structure overcomes the above shortcomings, and has better mechanical properties against bending and torsion. performance, but in order to obtain better bending and torsion performance, the wing skin is too thick, which increases the weight of the wing, which is not allowed by an aircraft with excellent performance

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