The invention relates to a micro solar reconnaissance flight vehicle incorporated with a Coanda effect. The micro solar reconnaissance flight vehicle comprises a propeller, a plurality of solar cell panels, a power control unit and a balance control unit, wherein the plurality of solar cell panels are symmetrically erected with a rotating shaft as center; an edge frame of each solar cell panel is fixedly arranged on a carbon fiber ring; the gaps of the solar cell panels are uniform and connected with a bottom circular framework of the flight vehicle; the axis of the propeller coincides with the rotating shaft on which the plurality of solar cell panels are erected; the propeller is positioned at the top; the areas of the erected solar cell panels are greater than that of the surface of the propeller; the plurality of solar cell panels are erected beyond an airflow area generated by the propeller; and total center-of-mass of motors in the power control unit and the balance control unit coincides with a symmetric line of a frame. The micro solar reconnaissance flight vehicle incorporated with the Coanda effect, provided by the invention, is advantaged in that full solar endurance is realized; the volume of the micro solar reconnaissance flight vehicle is small; the weight of the micro solar reconnaissance flight vehicle is light; the heat value of the micro solar reconnaissance flight vehicle in operation process is less; and the micro solar reconnaissance flight vehicle flies stably, hovers in the air for a long time and can be used for transmitting passenger flow and traffic flow in real time.
Micro solar reconnaissance flight vehicle incorporated with Coanda effect
2015-11-04
Patent
Electronic Resource
English
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