Six degree of freedom aerial vehicle
This disclosure describes an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), which includes a plurality of maneuverability propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). The aerial vehicle may also include a lifting propulsion mechanism that operates to generate a force sufficient to maintain the aerial vehicle at an altitude.
1. An aerial vehicle apparatus, comprising:
a lifting propulsion mechanism configured to generate a lift sufficient to maintain the aerial vehicle apparatus at an altitude;
a first maneuverability propulsion mechanism;
a second maneuverability propulsion mechanism;
a third maneuverability propulsion mechanism;
a fourth maneuverability propulsion mechanism;
a fifth maneuverability propulsion mechanism;
a sixth maneuverability propulsion mechanism; and
wherein:
the first maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, and the fifth maneuverability propulsion mechanism are aligned in a plane and oriented in a first direction; and
the second maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, and the sixth maneuverability propulsion mechanism are aligned in the plane and oriented in a second direction that is approximately perpendicular to the first direction.
2. The aerial vehicle apparatus of claim 1 , wherein the lifting propulsion mechanism is in the plane and oriented in the first direction.
3. The aerial vehicle apparatus of claim 1 , wherein generating with the second maneuverability propulsion mechanism a first force having a first magnitude and a first direction, and generating with the fourth maneuverability propulsion mechanism a second force having the first magnitude and a second direction results in a combined force having a third magnitude and a third direction that surges the aerial vehicle apparatus in the third direction.
4. The aerial vehicle apparatus of claim 1 , wherein generating with the second maneuverability propulsion mechanism a first force having a first magnitude and a first direction, generating with the fourth maneuverability propulsion mechanism a second force having the first magnitude and a second direction, and generating with the sixth maneuverability propulsion mechanism a third force having a second magnitude and a third direction results in a combined force having a third magnitude and the third direction that sways the aerial vehicle apparatus in the third direction.
5. The aerial vehicle apparatus of claim 1 , wherein each of the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, the fifth maneuverability propulsion mechanism, and the sixth maneuverability propulsion mechanism, are arranged radially around a central portion of the aerial vehicle apparatus.
6. The aerial vehicle apparatus of claim 5 , wherein the lifting propulsion mechanism is at the central portion of the aerial vehicle apparatus.
7. An aerial vehicle apparatus, comprising:
a lifting propulsion mechanism configured to generate a force that is approximately equal in magnitude and opposite in direction from a gravitational force acting on the aerial vehicle apparatus;
a first maneuverability propulsion mechanism;
a second maneuverability propulsion mechanism;
a third maneuverability propulsion mechanism;
a fourth maneuverability propulsion mechanism;
a fifth maneuverability propulsion mechanism;
a sixth maneuverability propulsion mechanism; and
wherein:
at least one of the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, the fifth maneuverability propulsion mechanism, and the sixth maneuverability propulsion mechanism is horizontally aligned; and
at least one of the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, the fifth maneuverability propulsion mechanism, and the sixth maneuverability propulsion mechanism is vertically aligned.
8. The aerial vehicle apparatus of claim 7 , wherein:
each of the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, the fifth maneuverability propulsion mechanism, and the sixth maneuverability propulsion mechanism are within a plane and extend radially around a central portion of the aerial vehicle apparatus.
9. The aerial vehicle apparatus of claim 7 , further comprising:
a first arm extending from a central portion of the aerial vehicle apparatus;
a second arm extending from the central portion of the aerial vehicle apparatus;
a third arm extending from the central portion of the aerial vehicle apparatus;
a fourth arm extending from the central portion of the aerial vehicle apparatus;
a fifth arm extending from the central portion of the aerial vehicle apparatus; and
a sixth arm extending from the central portion of the aerial vehicle apparatus.
10. The aerial vehicle apparatus of claim 9 , wherein:
the first maneuverability propulsion mechanism is coupled to an end of the first arm;
the second maneuverability propulsion mechanism is coupled to an end of the second arm;
the third maneuverability propulsion mechanism is coupled to an end of the third arm;
the fourth maneuverability propulsion mechanism is coupled to an end of the fourth arm;
the fifth maneuverability propulsion mechanism is coupled to an end of the fifth arm; and
the sixth maneuverability propulsion mechanism is coupled to an end of the sixth arm.
11. The aerial vehicle apparatus of claim 10 , wherein:
each of the first arm, the second arm, the third arm, the fourth arm, the fifth arm, and the sixth arm extend radially from a center portion of the aerial vehicle apparatus.
12. The aerial vehicle apparatus of claim 11 , wherein:
each of the first arm, the second arm, the third arm, the fourth arm, the fifth arm, and the sixth arm are in a same plane.
13. The aerial vehicle apparatus of claim 10 , wherein:
the first arm and the second arm are in different planes.
14. The aerial vehicle apparatus of claim 10 , wherein:
each of the first arm, the second arm, the third arm, the fourth arm, the fifth arm, and the sixth arm extend in different directions from the central portion of the aerial vehicle apparatus.
15. An aerial vehicle apparatus, comprising:
a lifting propulsion mechanism configured to generate a lift sufficient to maintain the aerial vehicle apparatus at an altitude;
a first maneuverability propulsion mechanism;
a second maneuverability propulsion mechanism;
a third maneuverability propulsion mechanism;
a fourth maneuverability propulsion mechanism;
a fifth maneuverability propulsion mechanism; and
wherein:
the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, and the third maneuverability propulsion mechanism are oriented in a first direction; and
at least one of the fourth maneuverability propulsion mechanism and the fifth maneuverability propulsion mechanism are oriented in a second direction that is different than the first direction.
16. The aerial vehicle apparatus of claim 15 , wherein at least one of the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, or the fifth maneuverability propulsion mechanism includes at least one of a fan, a jet, a turbojet, a turbo fan, or a jet engine.
17. The aerial vehicle apparatus of claim 15 , further comprising:
a sixth propulsion mechanism.
18. The aerial vehicle apparatus of claim 15 , further comprising:
at least one propulsion mechanism controller operable to control each of the first maneuverability propulsion mechanism, the second maneuverability propulsion mechanism, the third maneuverability propulsion mechanism, the fourth maneuverability propulsion mechanism, or the fifth maneuverability propulsion mechanism during an aerial flight of the aerial vehicle apparatus.