A lightweight rudder surface and hinge structure suitable for solar-powered drones

Abstract

The invention discloses a lightweight rudder surface and a hinge structure suitable for a solar unmanned aerial vehicle, which belongs to the field of aircraft design and includes structures such as a composite light rudder surface and an adjustable hinge mechanism. Among them, the main beam, leading edge, wing rib, and trailing edge of the rudder surface are all made of carbon fiber-PMI foam composite material structure, which has a lighter structural weight than the traditional rudder surface. The rudder surface is subjected to bending and torsion through the main beam with a square section of composite material, and the shape is maintained by using a flexible skin, which saves the extra weight brought by the rigid skin; under the action of the adjustable hinge mechanism, the rudder surface can be within the range of ±45° around the rotation axis It rotates smoothly, and through the designed adjustable hinge mechanism, it can eliminate the dimensional error caused by composite material processing, and meet the coaxiality requirements of multiple hinge shafts of the rudder surface with large aspect ratio; save the maintenance cover of the rudder surface, and pass the vertical The bolts on the rudder surface can be quickly disassembled and assembled on the rudder surface.

Description

technical field [0001] The invention belongs to the field of aircraft design, and relates to a lightweight rudder surface and hinge structure suitable for solar unmanned aerial vehicles. Background technique [0002] The feasibility of the overall scheme of solar UAV is highly sensitive to the structural weight. Usually, the structural weight coefficient must be controlled within 35% to realize the closed loop of the scheme. Due to the need to reduce cruising power consumption and increase the light-receiving area, the wing load of solar-powered UAVs is usually between 2.4 and 6.3kg / m2, and its wing area is larger than that of traditional UAVs with the same take-off quality. In addition, in order to reduce the structural quality, solar-powered UAVs usually adopt composite material airfoil structures. During the thermal curing process, the dimensional accuracy and straightness errors are large, and the installation accuracy is difficult to guarantee. The structural skeleton ...

AI Technical Summary

Problems solved by technology

In addition, in order to reduce the structural quality, solar-powered UAVs usually adopt composite material airfoil structures. During the thermal curing process, the dimensional accuracy and straightness errors are large, and the installation accuracy is difficult to guarantee.

The structural skeleton of the traditional UAV rudder surface is mainly made of solid carbon fiber structure, which has a large structural mass; the skin is made of rigid material to ensure the structural rigidity under high wing loads, the surface density is high, and the maintenance cost is high; the hinge is usually a hidden structure. The range is small, it is difficult to disassemble and assemble, and it is difficult to adjust the distance between the rudder surface and the wing surface

This kind of rudder surface and hinge structure is not conducive to the reduction of structural quality, but also requires high processing precision of composite materials and difficult maintenance, so it is not conducive to the improvement of the performance and processing technology of solar drones.

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