Aerial vehicle

An unmanned aerial vehicle, comprising:

• a fuselage;
• two front arms and two rear arms, the two front arms being symmetrically connected to a front end of the fuselage and the two rear arms being symmetrically connected to a rear end of the fuselage, wherein each of the two rear arms is coupled to the fuselage, a position where one of the two rear arms is connected to the fuselage and a position where one of the two front arms is connected to the fuselage are staggered in a height direction of the fuselage, and when the aerial vehicle is upright and placed horizontally, the position where the one of the two rear arms is connected to the fuselage is higher than the position where the one of the two front arms is connected to the fuselage;
• four propellers at ends of the two front arms away from the fuselage and ends of the two rear arms away from the fuselage respectively, each front arm including a first end connected to the fuselage, and a second end connected to one of the four propellers, and the second end being opposite to the first end;
• two brackets connected in correspondence with the two front arms, each bracket including an end connected to the second end of the corresponding one front arm, and the two brackets being configured to support the aerial vehicle when the aerial vehicle is not taking off or is landed;
• and
• four visual sensors at the ends of the two front arms away from the fuselage and the ends of the two rear arms away from the fuselage respectively;
• wherein:
• the unmanned aerial vehicle has at least a taking off or landing state and a cruise state;
• in response to the unmanned aerial vehicle being in the taking off or landing state, an angle between a longitudinal axis of the fuselage and a horizontal plane is within a first angular range;
• in response to the unmanned aerial vehicle being in the cruise state, the angle between the longitudinal axis of the fuselage and the horizontal plane is within a second angular range, and a maximum value of the second angular range is less than a minimum value of the first angular range;
• in response to the unmanned aerial vehicle switching between the taking off or landing state and the cruise state, the fuselage and the four propellers tilt as a whole;
• and
• each pair of shooting angles of the four visual sensors partially overlap and form a binocular vision module so that the four visual sensors form four binocular vision modules.

An aerial vehicle, comprising:

• a fuselage;
• a plurality of propellers coupled to the fuselage;
• at least two front arms coupled to the fuselage, each front arm including a first end connected to the fuselage, and a second end connected to one of the plurality of propellers, and the second end being opposite to the first end;
• and
• at least two brackets connected in correspondence with the at least two front arms, each bracket including an end connected to the second end of the corresponding one front arm, and the at least two brackets being configured to support the aerial vehicle when the aerial vehicle is not taking off or is landed;
• wherein:
• the aerial vehicle has at least a taking off or landing state and a cruise state;
• in response to the aerial vehicle being in the taking off or landing state, an angle between a longitudinal axis of the fuselage and a horizontal plane is within a first angular range;
• in response to the aerial vehicle being in the cruise state, the angle between the longitudinal axis of the fuselage and the horizontal plane is within a second angular range, and a maximum value of the second angular range is less than a minimum value of the first angular range;
• in response to the aerial vehicle switching between the taking off or landing state and the cruise state, the fuselage and the plurality of propellers tilt as a whole;
• the at least two front arms are each pivotably connected to the fuselage, and the at least two brackets are pivotally connected to the corresponding one of the at least two front arms;
• the at least two front arms are rotated relative to the fuselage and the at least two brackets are rotated relative to the at least two front arms to allow the aerial vehicle to be selectively in an unfolded state or a folded state;
• in the unfolded state, the at least two front arms each form an angle with the fuselage, and the at least two brackets each form an angle with the corresponding one of the at least two front arms;
• and p2 in the folded state, the at least two front arms are affixed to the fuselage and the at least two brackets each are affixed to the corresponding one of the at least two front arms.