Wing spar of small and medium-sized light unmanned aerial vehicle, control method and application

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and discloses a small and medium-sized light unmanned aerial vehicle wing spar, a control method and application, a composite upper beam reinforcing structure, a front web plate, a rear web plate and a composite lower beam reinforcing structure are glued together to form a wing spar wing box, and the web plates and wing ribs in the wing spar wing box form partitions; the central wing box is partitioned into a plurality of independent wing boxes; a composite middle beam reinforcing structure is arranged at the wing root, a cavity formed by the composite middle beam reinforcing structure and the independent wing box is filled with a composite filling core structure, composite filling core guide hole web plate structures are arranged on the front web plate and the rear web plate, and an embedded fixed joint is arranged at the wing root joint of the composite upper beam reinforcing structure and the composite lower beam reinforcing structure. The reinforcing structure can be used for various unmanned aerial vehicle structures, can be used for other beam type design, is innovative and prospective, can improve the strength of the unmanned aerial vehicle in various conflict environments, and has a very high application prospect.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a small and medium-sized light unmanned aerial vehicle wing spar, a control method and an application. Background technique [0002] At present, most of the small and medium-sized UAVs use beam-type wings, and most of them are made of carbon fiber and glass fiber. However, under certain specific conditions, the above processes cannot achieve the expected goals. For example, in the projects in the China International Aircraft Design Challenge, many projects limit the weight of the aircraft and thus limit the types of materials. The balsa wood material to form the aircraft structure, the upper and lower beams, and the front and rear webs to form the girder has become the optimal solution. Furthermore, although this solution meets the weight requirements, the strength is worrying. The aircrafts of all colleges and universities have broken the aircraft an...

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Problems solved by technology

[0002] At present, most small and medium-sized UAVs use beam-type wings, and most of them are made of carbon fiber and glass fiber. However, under certain conditions, the above processes cannot achieve the expected goal.

For example, among the projects in the China International Aircraft Design Challenge, many projects limit the weight of the aircraft and thus limit the types of materials. The aircraft structure composed of light wood materials, the upper and lower beams, and the front and rear webs constitute the girder become the optimal solution. Furthermore, although this scheme meets the weight requirements, its strength is worrying. The participating aircraft of various universities have broken the aircraft and the wing spar when completing the project.

In view of the above problems, the existing solution is to cover the surface of the balsa material such as the web surface with reinforcing materials such as carbon fiber, but the cost is high and the thin layer of carbon fiber is easy to peel off the surface of the balsa wood, and the reinforcement effect is not satisfactory. Further, other existing solutions are to increase The proportion of carbon fiber, but with the increase of carbon fiber, the weight gradually fails to meet the requirements and the cost increases exponentially

[0003] Through the above analysis, the existing problems and defects of the prior art are as follows: the prior art covered the surface of the balsa material with reinforcing materials such as carbon fiber, but the cost was high and the thin layer of carbon fiber was easy to peel off the surface of the balsa wood, and the reinforcing effect was unsatisfactory; at the same time, the prior art increased The proportion of carbon fiber, but with the increase of carbon fiber, the weight gradually fails to meet the requirements and the cost increases exponentially

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