| CPC B64C 29/02 (2013.01) [B64C 3/40 (2013.01); B64C 39/08 (2013.01); B64U 10/20 (2023.01); B64U 30/12 (2023.01); B64U 50/13 (2023.01); B64U 60/70 (2023.01); B64U 10/25 (2023.01)] | 3 Claims |
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1. An aerial vehicle comprising:
a thrust unit;
a tail;
a fuselage that connects the thrust unit and the tail;
a main wing connected to the fuselage; and
a control unit for controlling at least the main wing,
wherein the main wing comprises a first wing and a second wing,
wherein, when in an initial state of the aerial vehicle, the fuselage is configured to stand in a vertical direction, and when the aerial vehicle ascends to a predetermined height, the aerial vehicle is configured to transition from an ascending posture to a horizontal posture, the fuselage being oriented in the vertical direction in the ascending posture and oriented in a horizontal direction in the horizontal posture,
wherein, when the aerial vehicle descends to make a landing, the aerial vehicle is oriented so that the thrust unit and the tail are an upper end and a lower end of the aerial vehicle, respectively, with respect to the ground, and the control unit is configured to control the first wing and the second wing to tilt toward the tail and to bring the first wing and the second wing closer together by rotating the first wing and the second wing about a longitudinal axis of the fuselage, so that the first wing and the second wing form an inverted V shape, and
wherein, when the aerial vehicle lands on the ground, the tail, an end of the first wing, and an end of the second wing are the lower end of the aerial vehicle contacting the ground.
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