Wing spar of composite wing aircraft

Abstract

The invention discloses a wing spar of a composite wing aircraft, which comprises two transverse integral beams which are horizontally arranged oppositely, a crossed bearing beam for bearing bending torque is arranged between the two transverse integral beams, and the inside of the crossed bearing beam is of a hollow structure; the end parts of the crossed bearing beams are fixedly connected with the two transverse integral beams; the two ends of the two transverse integral beams are each provided with one end rib plate used for bearing bending and torsional moment, the two transverse integral beams are connected and fixed through the two end rib plates, the whole cross type bearing beam is of a hollow structure, the structural weight of the wing is greatly reduced, meanwhile, the bending and torsional resistance of the bearing beam is greatly improved through the cross type bearing beam, and the bearing beam is suitable for being popularized and applied. The water passing grooves are formed in the crossed bearing beams, so that the problem that water stored in the wing spar is discharged is simply and effectively solved, and lighter weight can be obtained on the premise that certain bending and torsional strength is determined by adding the end rib plates.

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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