Distributed multi-rotor-wing unmanned aerial vehicle system with heavy load and long endurance

Abstract

The invention belongs to the fields of structural design and flight control of a multi-rotor-wing aircraft, and particularly relates to a distributed multi-rotor-wing unmanned aerial vehicle system with a heavy load and long endurance. The distributed multi-rotor-wing unmanned aerial vehicle system comprises an independent fuselage and distributed vehicle bodies, wherein the independent fuselage comprises standard boxes and box arms; each stand box is at least provided with three box arms; the distributed vehicle bodies are fixed on the box arms of the independent fuselage; each of the distributed vehicle bodies comprises a power system, a vehicle arm and an electronic system, wherein the power systems are mounted at the upper ends of the vehicle arms, and the electronic systems are mounted at the lower ends of the vehicle arms; each of the power systems comprises rotor wings, an engine, an oil pump, an oil tank and a steering engine; each of the electronic systems comprises a flight control system and a power supply module. The independent fuselage and the distributed vehicle bodies are designed in a high-modularized way, so that quick matching, disassembling and assembling can be realized; the unmanned aerial vehicle system is convenient to repair, maintain, transport and produce in batches; the power systems adopt direct oil-driving structures, and the engines directly drive the rotor wings, so that the structure is simplified, the weight is reduced, the endurance is greatly prolonged, and the load is enlarged.

Description

technical field [0001] The invention belongs to the field of structural design and flight control of multi-rotor aircraft, in particular to a distributed heavy-load long-endurance multi-rotor UAV system. Background technique [0002] At present, most civilian multi-rotor aircraft are driven by motors. Because the energy density of batteries is much lower than that of fossil fuels such as gasoline, the flight time and load capacity of current multi-rotor aircraft are very limited. The longest flight time does not exceed 30 minutes, and the maximum load is not More than 20Kg, which greatly limits the application and development of multi-rotor drones. In addition, current drones generally adopt rigid connection or integral structure design, which is difficult to disassemble and assemble, and is not convenient for maintenance, transportation and mass production. Contents of the invention [0003] In order to overcome the shortcomings and deficiencies in the prior art, the pre...

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Problems solved by technology

[0002] At present, most civilian multi-rotor aircraft are driven by motors. Because the energy density of batteries is much lower than that of fossil fuels such as gasoline, the flight time and load capacity of current multi-rotor aircraft are very limited. The longest flight time does not exceed 30 minutes, and the maximum load is not More than 20Kg, which greatly limits the application and development of multi-rotor drones

In addition, the current drones generally adopt rigid connection or integral structure design, which is difficult to disassemble and assemble, and is not convenient for maintenance, transportation and batch production

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