Aircraft
An unmanned aerial vehicle (UAV) includes: a body including a nose and a tail opposite to the nose; a plurality of rotor devices respectively mounted on the body; and a rear obstacle avoidance sensor mounted on a top part of the body, the UAV has a backward flight state of flying in a direction towards the tail and a hover state of stably hovering in a wind-free environment; in the hover state, the body is tilted in a length direction relative to a horizontal direction, so that the nose is higher than the tail; the optical axis of the rear obstacle avoidance sensor is tilted at a greater angle relative to the horizontal direction when the UAV is in the hover state compared to the backward flight state. It can improve the flight efficiency, enhance the overall obstacle avoidance function, and improve the flight experience.
1 . An aircraft, comprising:
a body, including a nose and a tail opposite to the nose;
a driving power device, coupled to the body to provide driving power; and
a sensor, mounted on the body and configured to detect in a flight direction of the aircraft,
wherein in response to a horizontal flight state instruction, the driving power device provides a first flight power to enable the aircraft to fly in a horizontal direction, in response to a hover state instruction, the driving power device provides a second flight power to enable the aircraft to hover stably in an environment without wind interference,
a tilt angle between an optical axis of the sensor and the horizontal direction when the aircraft is in a hover state is greater than a tilt angle between the optical axis of the sensor and the horizontal direction when the aircraft is in a horizontal flight state.
2 . The aircraft according to claim 1 , wherein the horizontal flight state includes a backward flight state of flying toward a tail direction of the aircraft, the sensor is a rear sensor, and the rear sensor is configured to detect toward the tail direction of the aircraft.
3 . The aircraft according to claim 2 , wherein in the backward flight state, a tilt angle between the optical axis of the sensor and the horizontal direction when the aircraft is in the hover state is greater than a tilt angle between the optical axis of the sensor and the horizontal direction when the aircraft is in the backward flight state.
4 . The aircraft according to claim 2 , wherein the aircraft further comprises a front sensor configured to detect in a nose direction of the aircraft, and in the backward flight state, an optical axis of the front sensor is tilted in a forward and upward direction relative to the horizontal direction; or
the aircraft further comprises a bottom sensor configured to detect in a downward direction, and in the backward flight state, an optical axis of the bottom sensor is tilted in a forward and downward direction relative to the horizontal direction.
5 . The aircraft according to claim 2 , wherein an optical axis of the rear sensor is configured to be substantially parallel to the horizontal direction.
6 . The aircraft according to claim 2 , wherein in the hover state, an optical axis of the rear sensor is toward backward and upward relative to a horizontal direction.
7 . The aircraft according to claim 1 , wherein the aircraft further comprises a front sensor configured to detect in a nose direction of the aircraft;
in the hover state, an optical axis of the front sensor is tilted in a forward and upward direction relative to the horizontal direction.
8 . The aircraft according to claim 1 , wherein the aircraft further comprises a bottom sensor configured to detect in a downward direction;
in the hover state, an optical axis of the bottom sensor is tilted in a forward and downward direction relative to the horizontal direction.
9 . The aircraft according to claim 1 , wherein the horizontal flight state includes a forward flight state of flying in a nose direction of the aircraft;
in the forward flight state, a roll axis direction of the body is substantially parallel to the horizontal direction.
10 . The aircraft according to claim 9 , wherein in the forward flight state, the aircraft flies at a target flight speed.
11 . The aircraft according to claim 1 , wherein in the hover state, a first tilt angle of a roll axis direction of the body relative to the horizontal direction is related to the target flight speed.
12 . The aircraft according to claim 11 , wherein in the hover state, the first tilt angle of the roll axis of the body relative to the horizontal direction is between 5 degrees and 25 degrees.
13 . The aircraft according to claim 1 , wherein the aircraft further comprises a front sensor configured to detect in a nose direction of the aircraft, and a bottom sensor configured to detect in a downward direction.
14 . The aircraft according to claim 1 , wherein the horizontal flight state includes a forward flight state of flying in a nose direction, and an optical axis of a rear sensor is toward backward and upward relative to a horizontal direction.
15 . The aircraft according to claim 14 , wherein in the forward flight state, an optical axis of a front sensor is tilted toward forward and downward relative to the horizontal direction;
in the forward flight state, an optical axis of the bottom sensor is tilted backward and downward relative to the horizontal direction.
16 . The aircraft according to claim 1 , wherein a front sensor has a first perception coverage area, a bottom sensor has a second perception coverage area;
an optical axis of the bottom sensor is tilted forward and downward relative to a roll axis direction of a central body of the body to ensure that the second perception coverage area overlaps at least partially with the first perception coverage area.
17 . The aircraft according to claim 16 , wherein the first perception coverage area has a first upper boundary and a first lower boundary, the second perception coverage area has a first front boundary and a first rear boundary, and the first lower boundary overlaps at least partially with the first front boundary.
18 . The aircraft according to claim 17 , wherein an overlapping angle between the first lower boundary and the first front boundary is less than or equal to 5 degrees.
19 . The aircraft according to claim 1 , wherein an optical axis of a rear sensor is tilted upward relative to a roll axis direction of a central body of the body.