Unmanned aerial vehicle powered using electric propulsion
An unmanned aerial vehicle (UAV) powered using electric propulsion is provided. The unmanned aerial vehicle (UAV) includes a main frame and a plurality of thrust rings. The plurality of thrust rings is arranged in a first spatial configuration around the main frame and is rotatably coupled to at least one actuator in the main frame along a pivot axis. The unmanned aerial vehicle (UAV) further includes a plurality of plasma actuators disposed on at least one of the plurality of thrust rings. Further, in an actuated state, the plurality of plasma actuators actuates to generate a plasma thrust that causes the unmanned aerial vehicle (UAV) to orient along a particular axis or move in a specific direction.
1. An unmanned aerial vehicle (UAV), comprising:
a main frame;
a plurality of thrust rings that is arranged in a first spatial configuration around the main frame and rotatably coupled to at least one actuator in the main frame along a pivot axis; and
a plurality of plasma actuators disposed on at least one of the plurality of thrust rings,
wherein, in an actuated state, the plurality of plasma actuators is actuated to generate a plasma thrust that causes the UAV to orient along a particular axis or move in a specific direction.
2. The UAV according to claim 1 , wherein the main frame comprises:
a front section,
a first side section that includes a first shaft of the at least one actuator,
a second side section that includes a second shaft of the at least one actuator,
wherein each thrust ring of the plurality of thrust rings is rotatably coupled to the first shaft at a first position of the plurality of thrust rings and the second shaft at a second position of the plurality of thrust rings, and
wherein the second position is diametrically opposite to the first position.
3. The UAV according to claim 1 , wherein the first spatial configuration corresponds to one of a stowed state or the actuated state.
4. The UAV according to claim 3 , wherein, in the stowed state, the first spatial configuration is a default configuration in which each thrust ring of the plurality of thrust rings is concentrically aligned along the pivot axis substantially parallel to a base section of the main frame.
5. The UAV according to claim 1 , wherein, in the actuated state, the first spatial configuration includes each thrust ring of the plurality of thrust rings positioned substantially at an acute angle with each other.
6. The UAV according to claim 1 , wherein each thrust ring of the plurality of thrust rings circumscribes the main frame and rotates independent to each other along the pivot axis.
7. The UAV according to claim 1 , wherein each plasma actuator of the plurality of plasma actuators is having a substantially cylindrical structure comprising a plurality of openings in a Dot Matrix Pattern, spread across a surface of the substantially cylindrical structure.
8. The UAV according to claim 7 , wherein the actuation of the plurality of plasma actuators controls a pattern of at least one of a release of corona discharge via a first portion of the plurality of openings or a collection of the released corona discharge via a second portion of the plurality of openings.
9. The UAV according to claim 8 , wherein an orientation of the UAV is controlled based on a second spatial configuration of each thrust ring of the plurality of thrust rings and the controlled pattern of at least one of the release or the collection of the corona discharge, and
the second spatial configuration is same as or different from the first spatial configuration.
10. The UAV according to claim 1 , wherein the plurality of plasma actuators comprises:
a first plasma actuator disposed across a section of a dominant thrust ring of the plurality of thrust rings, and
a group of plasma actuators disposed across different sections of minor thrust rings of the plurality of thrust rings.
11. A control system for an unmanned aerial vehicle (UAV), comprising:
a first electronic controller communicatively coupled to a plurality of plasma actuators disposed on at least one of a plurality of thrust rings, which is arranged in a first spatial configuration around a main frame of the UAV;
a second electronic controller communicatively coupled to at least one actuator disposed in the main frame and rotatably coupled to the plurality of thrust rings; and
a processor that:
receives an input; and
controls, based on the input, an actuation of the plurality of plasma actuators generate a plasma thrust that causes the UAV to orient along a particular axis or move in a specific direction.
12. The control system according to claim 11 , wherein each plasma actuator of the plurality of plasma actuators is having a substantially cylindrical structure comprising a plurality of openings in a Dot Matrix Pattern, spread across a surface of the substantially cylindrical structure.
13. The control system according to claim 12 , wherein the actuation of the plurality of plasma actuators controls a pattern of at least one of a release of corona discharge via a first portion of the plurality of openings or a collection of the released corona discharge via a second portion of the plurality of openings.
14. The control system according to claim 13 , wherein an orientation of the UAV is controlled based on a second spatial configuration of each thrust ring of the plurality of thrust rings and the controlled pattern of at least one of the release or the collection of the corona discharge, and
the second spatial configuration is same as or different from the first spatial configuration.
15. The control system according to claim 11 , wherein the first spatial configuration corresponds to one of a stowed state or an actuated state.
16. A method of assembling an unmanned aerial vehicle (UAV), comprising:
disposing a main frame that comprises at least one actuator;
arranging a plurality of thrust rings in a first spatial configuration around the main frame such that the plurality of thrust rings is rotatably coupled to the at least one actuator in the main frame along a pivot axis; and
disposing a plurality of plasma actuators on at least one of the plurality of thrust rings.
17. The method according to claim 16 , wherein the first spatial configuration corresponds to one of a stowed state or an actuated state.
18. The method according to claim 16 , wherein each plasma actuator of the plurality of plasma actuators is having a substantially cylindrical structure comprising a plurality of openings in a Dot Matrix Pattern, spread across a surface of the substantially cylindrical structure.
19. The method according to claim 18 , wherein the actuation of the plurality of plasma actuators controls a pattern of at least one of a release of corona discharge via a first portion of the plurality of openings or a collection of the released corona discharge via a second portion of the plurality of openings.
20. The method according to claim 19 , wherein an orientation of the UAV is controlled based on a second spatial configuration of each thrust ring of the plurality of thrust rings and the controlled pattern of at least one of the release or the collection of the corona discharge, and
the second spatial configuration is same as or different from the first spatial configuration.