Bearing structure for electric unmanned aerial vehicle

Abstract

A bearing structure for an electric unmanned aerial vehicle comprises an upper deck, a lower deck and an intermediate web clamped between the upper deck and the lower deck. The upper deck and the lower deck are generally in left-right symmetric strip shapes, and the left and right of each of the upper deck and the lower deck extend outwards to form a plurality of cantilever connecting plates corresponding to cantilever structures. The intermediate web comprises a cylinder web which is located at the center of the extended lines of the cantilevers, and a plurality of cantilever webs which extend radially outwards from the cylinder web in length directions of the cantilevers. A plurality of battery compartment webs are encircled in length directions of the upper deck and the lower deck to form a plurality of battery compartments for accommodating batteries. Through the bearing structure, the spaces for accommodating the large-capacity batteries can be obtained on the electric unmanned aerial vehicle, the structure weight can be reduced, different loads can be flexibly configured without damaging the balance of the electric unmanned aerial vehicle, and the flight control software design of the electric unmanned aerial vehicle is simplified, which is beneficial to the control and safety of the electric unmanned aerial vehicle.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor electric unmanned aerial vehicle, and in particular to a load-bearing structure for the electric unmanned aerial vehicle. Background technique [0002] Electric drones have a large market share in the consumer market, and have the advantages of flexible maneuverability, quick response, unmanned flight, and low operating requirements. However, the power of electric drones is provided by batteries. Batteries are basically the dead weight of drones and cannot be consumed like fuel. As a result, their payloads are very limited and their cruising time is very short. They are rarely used as weapon strike platforms. . In addition, most of the current electric drones on the consumer market are multi-axis drones, such as four-axis and six-axis drones. Since the cantilever is set radially outward relative to the fuselage, the volume is large and the transpor...

AI Technical Summary

Problems solved by technology

In order to bear the force with less structural weight as much as possible, the diameter of the circumscribed circle of the hexagonal central plate is very small, resulting in almost all the stress concentrated in the middle of the fuselage, which has to increase the weight of the fuselage; and the too small fuselage body diameter, fully symmetrical layout, resulting in the center of gravity concentrated at one point, and the layout of landing gear, load mounting points, etc. are greatly restricted

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