Unmanned aerial systems having out of phase gimballing axes
An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.
1. An unmanned aerial system comprising:
an elongated fuselage having forward and aft ends and first and second rotational degrees of freedom;
a forward propulsion assembly disposed at the forward end of the fuselage, the forward propulsion assembly including a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom; and
an aft propulsion assembly disposed at the aft end of the fuselage, the aft propulsion assembly including an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom;
wherein, the first gimballing axis is out of phase with the second gimballing axis to control an orientation of the fuselage in the first and second rotational degrees of freedom.
2. The unmanned aerial system as recited in claim 1 wherein the unmanned aerial system is operable to transition between a vertical takeoff and landing flight mode and a forward flight mode, the fuselage having a substantially vertical orientation in the vertical takeoff and landing flight mode and a substantially horizontal orientation in the forward flight mode.
3. The unmanned aerial system as recited in claim 2 wherein in the vertical takeoff and landing flight mode the first rotational degree of freedom further comprises one of a pitch or a roll rotational degree of freedom and the second rotational degree of freedom further comprises the other of the pitch or the roll rotational degree of freedom.
4. The unmanned aerial system as recited in claim 2 wherein in the vertical takeoff and landing flight mode differential torque between the forward and aft rotor hub assemblies provides a third moment on the fuselage in a yaw rotational degree of freedom.
5. The unmanned aerial system as recited in claim 2 wherein in the forward flight mode the first rotational degree of freedom further comprises one of a pitch or a yaw rotational degree of freedom and the second rotational degree of freedom further comprises the other of the pitch or the yaw rotational degree of freedom.
6. The unmanned aerial system as recited in claim 2 wherein in the forward flight mode differential torque between the forward and aft rotor hub assemblies provides a third moment on the fuselage in a roll rotational degree of freedom.
7. The unmanned aerial system as recited in claim 1 wherein the fuselage further comprises a substantially cylindrical fuselage.
8. The unmanned aerial system as recited in claim 1 wherein the fuselage further comprises a polygonal cross sectional shape.
9. The unmanned aerial system as recited in claim 1 wherein the forward propulsion assembly further comprises an actuator operable to rotate the forward rotor hub assembly about the first gimballing axis and the aft propulsion assembly further comprises an actuator operable to rotate the aft rotor hub assembly about the second gimballing axis.
10. The unmanned aerial system as recited in claim 1 wherein differential torque between the forward and aft rotor hub assemblies provides a third moment on the fuselage in a third rotational degree of freedom.
11. The unmanned aerial system as recited in claim 1 wherein the forward and aft rotor hub assemblies are counter rotating.
12. The unmanned aerial system as recited in claim 1 wherein the forward and aft rotor hub assemblies are rotatable to provide thrust in the same direction.
13. The unmanned aerial system as recited in claim 1 wherein the forward and aft rotor hub assemblies further comprise variable speed forward and aft rotor hub assemblies.
14. The unmanned aerial system as recited in claim 1 wherein the forward and aft rotor hub assemblies further comprise fixed pitch rotor blades.
15. The unmanned aerial system as recited in claim 1 wherein the forward and aft rotor hub assemblies further comprise foldable rotor blades folded toward the fuselage in a storage mode.
16. The unmanned aerial system as recited in claim 1 wherein the forward and aft rotor hub assemblies rotate about a common axis when the forward and aft rotor hub assemblies are in a nongimballed position.
17. The unmanned aerial system as recited in claim 1 wherein the first gimballing axis is orthogonal to the second gimballing axis.
18. The unmanned aerial system as recited in claim 1 further comprising a power system including a battery housed in the fuselage.
19. The unmanned aerial system as recited in claim 1 further comprising one or more wings extending radially from the fuselage.
20. A rotorcraft comprising:
an elongated fuselage having forward and aft ends and first and second rotational degrees of freedom, the fuselage having a substantially vertical orientation in a vertical takeoff and landing flight mode and a substantially horizontal orientation in a forward flight mode;
a forward propulsion assembly disposed at the forward end of the fuselage, the forward propulsion assembly including a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom; and
an aft propulsion assembly disposed at the aft end of the fuselage, the aft propulsion assembly including an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom;
wherein, the first gimballing axis is orthogonal to the second gimballing axis to control an orientation of the fuselage in the first and second rotational degrees of freedom;
wherein, in the vertical takeoff and landing flight mode, the first rotational degree of freedom is one of a pitch or a roll rotational degree of freedom and the second rotational degree of freedom is the other of the pitch or the roll rotational degree of freedom; and
wherein, in the forward flight mode, the first rotational degree of freedom is one of the pitch or a yaw rotational degree of freedom and the second rotational degree of freedom is the other of the pitch or the yaw rotational degree of freedom.