Manufacturing method for full-height multi-rotor unmanned aerial vehicle of foam structure

Abstract

The invention discloses a full-height multi-rotor unmanned aerial vehicle of a foam structure and a manufacturing method thereof. A body of the unmanned aerial vehicle is made through an integrated forming mode and comprises a composite skin, a foam core body interlayer and a plastic frame body skeleton. The composite skin wraps the foam core body interlayer and the plastic frame body skeleton in an adhesive mode, so that the body of the unmanned aerial vehicle is formed. According to the manufacturing method, low-density PMI foam, carbon fibers good in rigidity and strength and a glass fiber reinforced epoxy resin skin are connected together by combining an upper mold with a lower mold, so that a multi-rotor unmanned aerial vehicle body structure good in performance and complex in appearance is formed, and help is offered to the electric multi-rotor unmanned aerial vehicle with large loads during long-endurance flying.

Description

technical field [0001] The invention relates to a manufacturing method of a full-height foam structure multi-rotor unmanned aerial vehicle. The molds are connected together to form a multi-rotor unmanned aerial vehicle body structure with good performance and complex appearance and a manufacturing method thereof. Background technique [0002] With the development of electronic technology, the control of multi-rotor aircraft has become simple. With its huge advantages and broad application prospects, multi-rotor UAVs have become one of the research hotspots in the UAV industry in recent years. [0003] Compared with fixed-wing UAVs, multi-rotor UAVs have great advantages in flight mode and site requirements. Multi-rotors can realize vertical take-off and landing and fixed-point hovering, which is difficult for fixed-wing UAVs to achieve. At the same time, multi-rotors have less stringent requirements for flight space than fixed-wing, and are suitable for flying in relatively...

AI Technical Summary

Problems solved by technology

Therefore, this kind of aircraft cannot use the rudder surface swing to control the attitude of the aircraft like a fixed-wing aircraft, and consumes more power. It needs a large-capacity battery to meet the flight needs. The increase in battery capacity also brings about an increase in battery weight. Weight, flight time, and structure The three strengths restrict each other. At this time, in order to optimize the design of the aircraft, ensure that the airframe has sufficient strength during long-endurance flight, and at the same time, the airframe must have sufficient rigidity to prevent the vibration caused by the motor rotation from causing obvious deformation of the airframe structure. Under the above conditions, the structural weight should be controlled to the minimum

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