Vertical takeoff and landing aerial vehicle
View Patent ↗A vertical takeoff and landing aerial vehicle, including a plurality of lift propellers. A rotating shaft of each lift propeller from among the multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the aerial vehicle perpendicular to a horizontal plane of the aerial vehicle. The aerial vehicle of the present disclosure improves the heading axis control capacity of the aerial vehicle and reduces the restriction to the design size of the aerial vehicle.
1. A vertical takeoff and landing unmanned aerial vehicle, comprising:
a main body;
a left main wing and a right main wing which are respectively engaged with the main body;
a left front wing and a right front wing which are respectively engaged with the main body;
a left linear supporting piece arranged on the left main wing;
a right linear supporting piece arranged on the right main wing;
a first group of multiple lift propellers arranged on the left linear supporting piece; and
a second group of multiple lift propellers arranged on the right linear supporting piece;
wherein an outwards deflecting included angle less than 90 degrees is provided between a rotating shaft of each of the first group of multiple lift propellers and a plane in a lengthwise direction of the unmanned aerial vehicle; and an outwards deflecting included angle less than 90 degrees is provided between a rotating shaft of each of the second group of multiple lift propellers and the plane in the lengthwise direction of the unmanned aerial vehicle;
wherein the included angle between the rotating shaft of each lift propeller from among the first group of multiple lift propellers and the second group of multiple lift propellers and the plane in the lengthwise direction of the unmanned aerial vehicle is 5 degrees to 15 degrees; and
wherein included angles between two adjacent lift propellers in the first group of multiple lift propellers and the plane in the lengthwise direction of the unmanned aerial vehicle are different, and included angles between two adjacent lift propellers in the second group of multiple lift propellers and the plane in the lengthwise direction of the unmanned aerial vehicle are different.
2. The vertical takeoff and landing unmanned aerial vehicle according to claim 1 , wherein an end part of the left main wing away from the main body is provided with a left wing tip vertical stabilizer; an end part of the right main wing away from the main body is provided with a right wing tip vertical stabilizer; and
tops of the left wing tip vertical stabilizer and the right wing tip vertical stabilizer are respectively provided with wing tip lift propellers.
3. The vertical takeoff and landing unmanned aerial vehicle according to claim 2 , wherein the rotating shaft of the wing tip lift propeller outwards deflects 5 to 15 degrees relative to the plane in the lengthwise direction of the unmanned aerial vehicle.
4. A vertical takeoff and landing unmanned aerial vehicle, comprising:
a main body;
a left main wing and a right main wing which are respectively engaged with the main body;
a left front wing and a right front wing which are respectively engaged with the main body;
a left linear supporting piece arranged on the left main wing;
a right linear supporting piece arranged on the right main wing;
a first group of multiple lift propellers arranged on the left linear supporting piece; and
a second group of multiple lift propeller arranged on the right linear supporting piece;
a rotating shaft of each lift propeller from among the first group of multiple lift propellers and the second group of multiple lift propellers outwards forms an angle of 5 degrees to 15 degrees relative to a vertical plane of the unmanned aerial vehicle perpendicular to a horizontal plane of the unmanned aerial vehicle;
a left vertical stabilizer arranged at the rear part of the left linear supporting piece and a right vertical stabilizer arranged at the rear part of the right linear supporting piece;
a left additional lift propeller arranged on a top terminal of the left vertical stabilizer and a right additional lift propeller arranged on a top terminal of the right vertical stabilizer; and
wherein a rotating shaft of each of the left additional lift propeller and the right additional lift propeller outwards forms an angle of 5 degrees to 15 degrees relative to the vertical plane of the unmanned aerial vehicle perpendicular to the horizontal plane of the unmanned aerial vehicle.
5. The vertical takeoff and landing unmanned aerial vehicle according to claim 4 , wherein the rotating shafts of the left additional lift propeller, the right additional lift propeller, and each lift propeller from among the first group of multiple lift propellers and the second group of multiple lift propellers outwards form angles of 5 degrees to 15 degrees relative to the vertical plane of the unmanned aerial vehicle perpendicular to the horizontal plane of the unmanned aerial vehicle.
6. The vertical takeoff and landing unmanned aerial vehicle according to claim 5 , wherein the rotating shafts of the left additional lift propeller, the right additional lift propeller, and each lift propeller from among the first group of multiple lift propellers and the second group of multiple lift propellers outwards form angles of 8 degrees relative to the vertical plane of the unmanned aerial vehicle perpendicular to the horizontal plane of the unmanned aerial vehicle.
7. The vertical takeoff and landing unmanned aerial vehicle according to claim 6 , further comprising a detachable cabin attached to a bottom side of the main body.
8. The vertical takeoff and landing unmanned aerial vehicle according to claim 7 , wherein the cabin is a passenger cabin.
9. The vertical takeoff and landing unmanned aerial vehicle according to claim 7 , wherein the cabin is a cargo space.
10. The vertical takeoff and landing unmanned aerial vehicle according to claim 5 , wherein the outward angle causes lift force loss of 0.5 to 3%.
11. The vertical takeoff and landing unmanned aerial vehicle according to claim 10 , wherein the outward angle causes a yawing moment to be increased by 8 to 20%.
12. The vertical takeoff and landing unmanned aerial vehicle according to claim 5 , wherein the outward angle causes the lift force loss of 0.97%.
13. The vertical takeoff and landing unmanned aerial vehicle according to claim 10 , wherein the outward angle causes the yawing moment to be increased by 13.92%.
14. The vertical takeoff and landing unmanned aerial vehicle according to claim 6 , wherein the left linear supporting piece is configured to connect the left main wing with the left front wing.