Solar drone

Abstract

The invention relates to the field of drone design, in particular to a solar drone. The solar drone comprises a front wing, a rear wing, power systems, an energy system, task load pods and the like, wherein the front wing and the rear wing are connected with each other through a left drone body and a right drone body; and the power systems, the energy system and the task load pods are disposed on the drone bodies. The solar drone has the advantages that the drone adopts a serial-wing double-drone-body layout, front wing stress features are improved favorably, and structural weight is reduced; a lifting layout is used, all lifting faces provide positive lifting force, the pneumatic efficiency of the pneumatic layout can be increased, and high lifting force and high lift-drag ratio are achieved easily; a full-motion operating face is used, the area of the lifting faces where solar cells can be laid is maximized, and a large amount of energy conversion is achieved; and further, the front wing is not provided with the operating face, influence on structural design can be eliminated, and structural weight is reduced.

Description

technical field [0001] The invention relates to the field of UAV design, in particular to a solar-powered UAV. Background technique [0002] Most of the solar-powered UAVs adopt conventional layouts, such as Solar Impulse in Switzerland, Zephyr from Qinetiq in the United Kingdom, and Titan from Google in the United States. Solar-powered aircraft with conventional layouts have the following disadvantages: [0003] First, the horizontal tail achieves pitch trim and pitch control through negative lift, which reduces the available lift of the whole machine, and finally reduces the lift-to-drag ratio of the whole machine; in addition, due to the increase of the wetted area of ​​the whole machine, it leads to the zero-liter of the whole machine The increase of resistance will also reduce the lift-to-drag ratio of the whole machine; [0004] Second, because ailerons need to be arranged on the wings to achieve roll control, the area of ​​the wings that can be used to lay solar cell...

AI Technical Summary

Problems solved by technology

[0003] First, the horizontal tail achieves pitch trim and pitch control through negative lift, which reduces the available lift of the whole machine, and finally reduces the lift-to-drag ratio of the whole machine; in addition, due to the increase of the wetted area of ​​the whole machine, it leads to the zero-liter of the whole machine The increase of resistance will also reduce the lift-to-drag ratio of the whole machine;

[0004] Second, because ailerons need to be arranged on the wings to achieve roll control, the area of ​​the wings that can be used to lay solar cells is reduced; in addition, the deflection mechanism of the ailerons and the concentrated load when the ailerons deflect cause the wing structure Requires reinforcement, resulting in increased wing weight;

[0005] Third, there are many steering surfaces, the number of steering gears required is large, and the total weight is large

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