Control systems for unmanned aerial vehicles
Unmanned aerial systems including an unmanned aerial vehicle and a command device. The unmanned aerial vehicle includes a propulsion system, a vehicle power source, a vehicle electronic controller, and a vehicle coupling mechanism. The command device includes a command power source, a command electronic controller, and a command coupling mechanism. The vehicle electronic controller is without power from the vehicle power source when the vehicle coupling mechanism is connected to the command coupling mechanism. The command electronic controller is without power from the command power source when the vehicle coupling mechanism is connected to the command coupling mechanism. The vehicle electronic controller receives power from the vehicle power source when the vehicle coupling mechanism is separate from the command coupling mechanism. The command electronic controller receives power from the command power source when the vehicle coupling mechanism is separate from the command coupling mechanism.
1. An unmanned aerial system comprising:
an unmanned aerial vehicle including
a propulsion system configured to provide sustained flight of the unmanned aerial vehicle,
a vehicle power source,
a vehicle electronic controller, and
a vehicle coupling mechanism; and
a command device including
a command power source,
a command electronic controller, and
a command coupling mechanism configured to connect with the vehicle coupling mechanism,
wherein when the vehicle coupling mechanism is connected to the command coupling mechanism,
the vehicle electronic controller is without power from the vehicle power source, and
the command electronic controller is without power from the command power source, and
wherein when the vehicle coupling mechanism is separate from the command coupling mechanism,
the vehicle electronic controller receives power from the vehicle power source, and
the command electronic controller receives power from the command power source.
2. The unmanned aerial system of claim 1 ,
wherein the vehicle coupling mechanism including a first switch that selectively electrically connects the vehicle power source to the vehicle electronic controller, and
wherein the command coupling mechanism including a second switch that selectively electrically connects the command power source to the command electronic controller.
3. The unmanned aerial system of claim 2 ,
wherein when the vehicle coupling mechanism is connected to the command coupling mechanism,
the vehicle power source is electrically disconnected from the vehicle electronic controller, and
the command power source is electrically disconnected from the command electronic controller, and
wherein when the vehicle coupling mechanism is separate from the command coupling mechanism,
the vehicle power source is electrically connected to the vehicle electronic controller, and
the command power source is electrically connected to the command electronic controller.
4. The unmanned aerial system of claim 3 , wherein the first switch including a first normally-closed switch, and wherein the second switch including a second normally-closed switch.
5. The unmanned aerial system of claim 3 , wherein the first switch including a first push-to-break biased switch, and wherein the second switch including a second push-to-break biased switch.
6. The unmanned aerial system of claim 5 ,
wherein the vehicle coupling mechanism further including a first protrusion,
wherein the command coupling mechanism further including a second protrusion, and
wherein when the vehicle coupling mechanism is connected to the command coupling mechanism,
the first protrusion presses the second push-to-break biased switch, and
the second protrusion presses the first push-to-break biased switch.
7. The unmanned aerial system of claim 3 ,
wherein the first switch including a first normally-closed biased reed switch and a first magnet,
wherein the second switch including a second normally-closed biased reed switch and a second magnet, and
wherein when the vehicle coupling mechanism is connected to the command coupling mechanism,
the first magnet is positioned in close proximity to the second normally-closed biased reed switch, and
the second magnet is positioned in close proximity to the first normally-closed biased reed switch.
8. The unmanned aerial system of claim 3 , wherein the first switch including a first normally-closed biased optocoupler, and wherein the second switch including a second normally-closed biased optocoupler.
9. The unmanned aerial system of claim 8 ,
wherein the vehicle coupling mechanism further including a first protrusion,
wherein the command coupling mechanism further including a second protrusion, and
wherein when the vehicle coupling mechanism is connected to the command coupling mechanism,
the second protrusion is positioned to block a first optical path of the first normally-closed biased optocoupler, and
the first protrusion is positioned to block a second optical path of the second normally-closed biased optocoupler.
10. The unmanned aerial system of claim 1 , wherein responsive to the vehicle coupling mechanism being separated from the command coupling mechanism, the vehicle electronic controller is configured to activate the propulsion system of the unmanned aerial vehicle.
11. The unmanned aerial system of claim 10 , wherein responsive to the vehicle coupling mechanism being separated from the command coupling mechanism, the command electronic controller is configured to transmit a location signal via a command transceiver of the command device.
12. The unmanned aerial system of claim 11 , wherein responsive to receiving the location signal via a vehicle transceiver of the unmanned aerial vehicle, the vehicle electronic controller is configured to
determine a location of the command device, and
operate the propulsion system based on the location of the command device such that the unmanned aerial vehicle is positioned within a predetermined distance from the location of the command device.
13. The unmanned aerial system of claim 12 , wherein the command device is incorporated in a wearable device.
14. The unmanned aerial system of claim 1 , wherein the propulsion system includes two or more rotors that are positionable in a collapsed configuration and in a deployed configuration, and wherein responsive to the vehicle coupling mechanism being separated from the command coupling mechanism, the two or more rotors are moved from the collapsed configuration to the deployed configured.
15. An unmanned aerial system comprising:
an unmanned aerial vehicle comprising
an airframe
a vehicle power source disposed within the airframe,
a propulsion system operatively mounted to the airframe and configured to provide sustained flight of the unmanned aerial vehicle,
one or more vehicle sensors configured to detect motion of the airframe,
a vehicle electronic controller disposed within the airframe and configured to
track the motion of the airframe based on data received from the one or more vehicle sensors,
determine when the airframe is moving along a parabolic trajectory based on the data received from the one or more vehicle sensors, and
responsive to determining when the airframe is positioned at a vertex of the parabolic trajectory, activate the propulsion system, and
a command device that is coupleable to the airframe of the unmanned aerial vehicle,
wherein the vehicle electronic controller is without power from the vehicle power source when the unmanned aerial vehicle is connected to the command device, and
wherein the vehicle electronic controller receives power from the vehicle power source when the unmanned aerial vehicle is separate from the command device.
16. The unmanned aerial system of claim 15 , wherein the propulsion system including
two or more rotors, and
one or more motors operatively coupled to the two or more rotors,
wherein the vehicle electronic controller activates the propulsion system by sending control signals to the propulsion system which cause the two or more rotors to rotate.
17. The unmanned aerial system of claim 15 , wherein upon the vehicle electronic controller receiving power from the vehicle power source, the propulsion system is inactive until the vehicle electronic controller determines that the airframe is positioned at the vertex of the parabolic trajectory.
18. The unmanned aerial system of claim 17 , wherein upon receiving power from the vehicle power source, the vehicle electronic controller tracks the motion of the airframe to determine when the airframe is moving along the parabolic trajectory.
19. The unmanned aerial system of claim 15 , wherein the one or more vehicle sensors are further configured to detect an orientation of the airframe, and wherein the vehicle electronic controller is further configured to
determine when the airframe is in a predetermined orientation based on the data received from the one or more vehicle sensors, and
activate the propulsion system when the airframe is positioned at the vertex of the parabolic trajectory and the airframe is in the predetermined orientation.