Vertical take-off and landing aircraft with rotor thrust yaw control
A vertical take-off and landing aircraft includes a fixed wing airframe having opposed first and second wings extending from first and second sides, respectively, of a fuselage having opposed leading and trailing extremities, and a tail assembly located behind the trailing extremity. Vertical take-off and landing (VTOL) thrust rotors are mounted to the airframe providing vertical lift to the aircraft, and a forward thrust rotor is mounted to the airframe for providing forward thrust to the aircraft. At least one of VTOL thrust rotors is laterally tilted with respect to the airframe for providing vertical lift and yaw control authority to the aircraft.
1. A vertical take-off and landing aircraft, comprising:
a fixed wing airframe having first and second wings extending from first and second sides, respectively, of a fuselage having a leading extremity and a trailing extremity, and a tail assembly located behind the trailing extremity;
a forward thrust rotor mounted to the airframe for providing forward thrust to the aircraft;
vertical take-off and landing (VTOL) thrust rotors mounted to the airframe for providing vertical lift to the aircraft, the VTOL thrust rotors include a first set of VTOL thrust rotors proximate to the first side of the fuselage and a second set of VTOL thrust rotors proximate to the second side of the fuselage;
the VTOL thrust rotors of the first set of VTOL thrust rotors are identically laterally tilted to a lateral tilt with respect to the fuselage;
the VTOL thrust rotors of the second set of VTOL thrust rotors are identically laterally tilted to a lateral tilt with respect to the fuselage; and
the lateral tilt of the VTOL thrust rotors of the first set of VTOL thrust rotors is the mirror image of the lateral tilt of the VTOL thrust rotors of the second set of VTOL thrust rotors;
wherein the VTOL thrust rotors receive control inputs to increase or decrease the thrust of one or more of the VTOL thrust rotors independently of the other VTOL thrust rotors and the forward thrust rotor to effect independent control of the roll, pitch, yaw, and vertical thrust of the aircraft independent of differential torque between pairs of the VTOL thrust rotors that is augmented by lateral thrust components associated with the lateral tilt of the VTOL thrust rotors during lifting of the aircraft to increase yaw control, and further wherein the forward thrust rotor is activated independently of the VTOL thrust rotors to provide forward thrust of the aircraft during flight.
2. The vertical take-off and landing aircraft according to claim 1 , wherein the first set of VTOL thrust rotors includes a first front VTOL thrust rotor and a first rear VTOL thrust rotor each located outboard of the first side of the fuselage between the leading extremity of the fuselage and the tail assembly, and the second set of VTOL thrust rotors includes a second front VTOL thrust rotor and a second rear VTOL thrust rotor each located outboard of the second side of the fuselage between the leading extremity of the fuselage and the tail assembly.
3. The vertical take-off and landing aircraft according to claim 2 , wherein the first front VTOL thrust rotor and the second front VTOL thrust rotor are diametrically opposed, and are equidistant with respect to the first and second wings, respectively, and the fuselage.
4. The vertical take-off and landing aircraft according to claim 3 , wherein the first rear VTOL thrust rotor and the second rear VTOL thrust rotor are diametrically opposed, and are equidistant with respect to the first and second wings, respectively, and the fuselage.
5. The vertical take-off and landing aircraft according to claim 4 , wherein the first front VTOL thrust rotor is in-line with respect to the first rear VTOL thrust rotor, and the second front VTOL thrust rotor is in-line with respect to the second rear VTOL thrust rotor.
6. The vertical take-off and landing aircraft according to claim 1 , wherein the VTOL thrust rotors are laterally tilted inwardly with respect to the fuselage so as to direct their respective thrusts downwardly under the fuselage and inwardly towards the fuselage.
7. The vertical take-off and landing aircraft according to claim 1 , wherein the VTOL thrust rotors are laterally tilted outwardly with respect to the fuselage so as to direct their respective thrusts downwardly under the fuselage and outwardly away from the fuselage.
8. The vertical take-off and landing aircraft according to claim 1 , wherein the VTOL thrust rotors are laterally tilted four degrees from horizontal with respect to the fuselage.
9. The vertical take-off and landing aircraft according to claim 1 , wherein the VTOL thrust rotors are open thrust rotors.
10. The vertical take-off and landing aircraft according to claim 1 , wherein the VTOL thrust rotors are each driven for rotation by an electric motor, the electric motor receiving electrical power from a battery pack onboard the aircraft.
11. The vertical take-off and landing aircraft according to claim 1 , wherein the vertical take-off and landing aircraft is an unmanned aerial vehicle.
12. The vertical take-off and landing aircraft according to claim 1 , wherein the first set of VTOL thrust rotors have the same direction of rotation and the second set of VTOL thrust rotors have an opposition direction of rotation relative to the direction of rotation of the first set of VTOL thrust rotors.
13. The vertical take-off and landing aircraft according to claim 1 , further comprising at least one pivoting engine pod configured to adjust the lateral tilt of a VTOL thrust rotor.
14. The vertical take-off and landing aircraft according to claim 1 , wherein the first set of VTOL thrust rotors rotate in a first direction and the second set of VTOL thrust rotors rotate in a second direction opposite the first direction such that yaw control is accomplished by a combination of different torque and lateral thrust components of the VTOL thrust rotors.
15. A vertical take-off and landing aircraft, comprising:
a fixed wing airframe having first and second wings extending from first and second sides, respectively, of a fuselage having a leading extremity and a trailing extremity, and an empennage provided behind the trailing extremity;
a forward thrust rotor mounted to the trailing extremity of the fuselage, disposed between the trailing extremity and the empennage, the forward thrust rotor providing forward thrust to the aircraft;
vertical take-off and landing (VTOL) thrust rotors mounted to the airframe comprising: a first set of VTOL thrust rotors proximate to the first side of the fuselage; and
a second set of VTOL thrust rotors proximate to the second side of the fuselage;
wherein the VTOL thrust rotors of the first set of VTOL thrust rotors are identically laterally tilted to a lateral tilt with respect to the fuselage;
wherein the VTOL thrust rotors of the second set of VTOL thrust rotors are identically laterally tilted to a lateral tilt with respect to the fuselage; and
wherein the lateral tilt of the VTOL thrust rotors of the first set of VTOL thrust rotors is the mirror image of the lateral tilt of the VTOL thrust rotors of the second set of VTOL thrust rotors;
wherein the VTOL thrust rotors receive control inputs to increase or decrease the thrust of one or more of the VTOL thrust rotors independently of the other VTOL thrust rotors and the forward thrust rotor to effect independent control of the roll, pitch, yaw, and vertical thrust of the aircraft independent of differential torque between pairs of the VTOL thrust rotors that is augmented by lateral thrust components associated with the lateral tilt of the VTOL thrust rotors during lifting of the aircraft to increase yaw control, and further wherein the forward thrust rotor is activated independently of the VTOL thrust rotors to provide forward thrust of the aircraft during flight.
16. The vertical take-off and landing aircraft according to claim 15 , wherein the first set of VTOL thrust rotors rotate in a first direction and the second set of VTOL thrust rotors rotate in a second direction opposite the first direction such that yaw control is accomplished by a combination of different torque and lateral thrust components of the VTOL thrust rotors.