Unmanned aerial vehicle

An unmanned aerial vehicle, comprising:

• a fuselage body provided with a first accommodating cavity and a second accommodating cavity, wherein positions of the first accommodating cavity and the second accommodating cavity are different, the fuselage body defining a forward nose, an aft tail, and an axis extending from the forward nose to the aft tail, the streamlined fuselage body being configured to move through the air resulting in the air moving in the direction of the axis from the forward nose to the aft tail in relation to the fuselage body;
• a first wing disposed on one side of the fuselage body and configured to generate lift when the fuselage body is moving in a direction where the relative wind moves from the forward portion of the fuselage body to the aft portion of the fuselage body;
• a second wing disposed on an other side of the fuselage body and configured to generate lift when the fuselage body is moving in a direction where the relative wind moves from the forward portion of the fuselage body to the aft portion of the fuselage body;
• a first rotor assembly, mounted to the first wing and capable of rotating relative to the fuselage body;
• a second rotor assembly, mounted to the second wing and capable of rotating relative to the fuselage body;
• a third rotor assembly including a third motor and a third propeller connected to the third motor, the third motor being embedded in the first accommodating cavity and the third propeller being mounted outside and above the fuselage body;
• a fourth rotor assembly including a fourth motor and a fourth propeller connected to the fourth motor, the fourth motor being embedded in the second accommodating cavity and the fourth propeller being mounted outside and above the fuselage body;
• a first air vent positioned at a bottom portion of the fuselage body corresponding to the first accommodating cavity, the first air vent being in communication with the first accommodating cavity, wherein the first air vent defines an opening at the intersection of the first air vent and the fuselage body, and wherein the surface of the fuselage body at the opening is inclined, wherein a vector perpendicular to the surface of the fuselage body at the opening and directed away from the fuselage body includes a component parallel to the fuselage axis and directed rearward toward the aft tail;
• and
• a second air vent is positioned at a bottom portion of the fuselage body corresponding to the second accommodating cavity, the second air vent being in communication with the second accommodating cavity;
• and
• a main control board fixed to the fuselage body, enclosed within the fuselage body, and connected to the first rotor assembly, the second rotor assembly, the third rotor assembly and the fourth rotor assembly.