Fixed-wing UAV with lifting propellers and traction propellers

1. A fixed-wing unmanned aerial vehicle (UAV) comprising:

a left hind wing and a right hind wing;

a left forewing coupled to a right forewing;

a cabin coupled to the left hind wing and the right hind wing;

a left linear support coupled to at least one of said left hind wing and said left forewing;

a right linear support coupled to at least one of said right hind wing and said right forewing;

the left linear support has a first, a second, a third lifting propellers disposed thereon;

the right linear support has a fourth, a fifth, a sixth lifting propellers disposed thereon;

a left traction propeller disposed at a front end of the left linear support;

a right traction propeller disposed at a front end of the right linear support;

wherein the left linear support is parallel to the right linear support, and there are no other linear supports disposed parallel to said left and right linear supports; and

wherein when the UAV is in an upright position on a ground, the left and right linear supports are disposed from the ground at a distance longer than a distance of a top of said cabin to said ground.

2. The fixed-wing UAV according to claim 1 , further comprising a first vertical stabilizer disposed on a rear end of the left linear support.

3. The fixed-wing UAV according to claim 2 , further comprising a rudder disposed on said first vertical stabilizer to control an active yaw of the fixed-wing UAV.

4. The fixed-wing UAV according to claim 2 , further comprising a second vertical stabilizer directly coupled to a rear end of the right linear support.

5. The fixed-wing UAV as recited in claim 1 , wherein the fixed-wing UAV does not have any control surfaces.

6. The fixed-wing UAV as recited in claim 5 , wherein the left traction propeller or the right traction propeller is disposed on a same horizontal plane as a longitudinal axis of the left linear support.

7. The fixed-wing UAV as recited in claim 1 , wherein the left linear support directly couples to both the left forewing and the left hindwing.

8. A fixed-wing unmanned aerial vehicle (UAV) comprising:

a left hind wing and a right hind wing;

a left forewing and a right forewing;

a main body coupled to the left hind wing and the right hind wing;

a left linear support connecting the left hind wing to the left forewing;

a right linear support connecting the right hind wing to the right forewing;

the left linear support has a first, a second, a third lifting propellers disposed thereon;

the right linear support has a fourth, a fifth, a sixth lifting propellers disposed thereon;

wherein the left linear support is parallel to the right linear support, and there are no other linear supports disposed parallel to the left and right linear supports;

at least one of a) having a left propulsion propeller and a right propulsion propeller disposed on the UAV, and b) having a left traction propeller and a right traction propeller disposed on the UAV;

wherein a thrust ratio of the left and right traction propellers or a thrust ratio of the two propulsion propellers is changed to generate an asymmetric thrust, which controls an active yaw of the UAV; and

wherein when the UAV is in an upright position, the left and right linear supports are disposed from a ground at a distance longer than a distance of a top of said cabin to said ground.

9. The fixed-wing UAV according to claim 8 , further comprising a first vertical stabilizer disposed on a rear end of the left linear support.

10. The fixed-wing UAV according to claim 9 , further comprising a rudder disposed on the first vertical stabilizer.

11. The fixed-wing UAV according to claim 8 , wherein there are no control surfaces on the UAV.

12. The fixed-wing UAV according to claim 8 , wherein the cabin is detachably attached to a bottom side of the UAV.

13. The fixed-wing UAV as recited in claim 8 , further comprising a microprocessor to change the thrust ratio.