Drone systems and methods
An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.
1. An aircraft comprising:
a body defining an interior compartment configured to hold at least one of a passenger or a payload;
a battery system;
a plurality of arms coupled to and extending from the body; and
a plurality of non-wing-mounted propulsion devices configured to provide thrust to fly the aircraft, each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms;
wherein the plurality of propulsion devices are powered by the battery system;
wherein the plurality of propulsion devices include at least two propulsion devices that are selectively pivotable about at least two axes;
wherein the plurality of propulsion devices include at least one of (i) electric counter rotating ducted fans or (ii) electric ducted ionizing electrode engines; and
wherein the plurality of propulsion devices include the electric ducted ionizing electrode engines, and wherein each of the electric ducted ionizing electrode engines includes:
a housing;
a plurality of electrodes positioned in the housing, the plurality of electrodes comprising:
a first pair of electrodes including a first set of one or more ionizing electrodes paired with a first set of one or more attractive electrodes; and
a second pair of electrodes including a second set of one or more ionizing electrodes paired with a second set of one or more attractive electrodes; and
a control system configured to control the plurality of electrodes to provide a desired amount of thrust, wherein to provide the desired amount of thrust, the control system is configured to:
selectively apply a first voltage differential across the first pair of electrodes and approximately zero voltage differential across the second pair of electrodes to provide a first amount of thrust;
selectively apply a second voltage differential across the second pair of electrodes and approximately zero voltage differential across the first pair of electrodes to provide a second amount of thrust; and
selectively apply the first voltage differential across the first pair of electrodes and the second voltage differential across the second pair of electrodes to provide a third amount of thrust.
2. The aircraft of claim 1 , wherein the battery system includes a charging receiver configured to charge the battery system based on a remote signal received from a remote, wireless beaming system.
3. The aircraft of claim 1 , wherein the battery system includes a solar panel configured to charge the battery system.
4. The aircraft of claim 1 , wherein the plurality of propulsion devices include more than two propulsion devices, and wherein each of the plurality of propulsion devices is pivotable about at least two axes.
5. The aircraft of claim 1 , wherein the plurality of arms are at least one of (i) retractable such that the plurality of propulsion devices are selectively storable within or under the body or (ii) slidable along the body to facilitate selectively repositioning the propulsion devices.
6. The aircraft of claim 1 , further comprising a pair of wings, one of the pair of wings extending from each lateral side of the body.
7. The aircraft of claim 6 , wherein the pair of wings are retractable such that the pair of wings are selectively storable within, along, or under the body.
8. The aircraft of claim 6 , wherein the pair of wings are selectively pivotable such that an angle at which the pair of wings are oriented is controllable and independent of an angle of attack of the body.
9. The aircraft of claim 1 , further comprising a rear engine coupled to a rear end of the body.
10. The aircraft of claim 9 , wherein the rear engine is selectively repositionable relative to a nominal, rearward facing position.
11. The aircraft of claim 1 , further comprising wheel assemblies including wheels and wheel actuators, wherein the wheel actuators are configured to selectively extend the wheels from the body.
12. The aircraft of claim 11 , wherein the wheel assemblies include motors configured to drive the wheels.
13. The aircraft of claim 1 , wherein the interior compartment includes a payload bay configured to receive the payload.
14. The aircraft of claim 1 , wherein the interior compartment includes a passenger cabin, the passenger cabin including a transparent cabin panel that is selectively repositionable to facilitate entering the passenger cabin.
15. A propulsion device for an aircraft, the propulsion device comprising:
a housing;
a plurality of electrodes positioned in the housing, the plurality of electrodes comprising:
a first pair of electrodes including a first set of one or more ionizing electrodes paired with a first set of one or more attractive electrodes; and
a second pair of electrodes including a second set of one or more ionizing electrodes paired with a second set of one or more attractive electrodes; and
a control system configured to control the plurality of electrodes to provide a desired amount of thrust, wherein to provide the desired amount of thrust, the control system is configured to:
selectively apply a first voltage differential across the first pair of electrodes and approximately zero voltage differential across the second pair of electrodes to provide a first amount of thrust;
selectively apply a second voltage differential across the second pair of electrodes and approximately zero voltage differential across the first pair of electrodes to provide a second amount of thrust; and
selectively apply the first voltage differential across the first pair of electrodes and the second voltage differential across the second pair of electrodes to provide a third amount of thrust.
16. The propulsion device of claim 15 , wherein applying the first voltage differential across the first pair of electrodes generates an electric field configured to ionize molecules proximate the first set of one or more ionizing electrodes and force the ionized molecules towards the first set of one or more attractive electrodes.
17. The propulsion device of claim 15 , wherein the housing has an inlet and an outlet, and wherein an inlet area of the inlet is greater than an outlet area of the outlet.
18. The propulsion device of claim 15 , wherein the housing includes a first channel and a second channel, wherein the first pair of electrodes is positioned in the first channel, wherein the second pair of electrodes is positioned in the second channel, and wherein the housing includes an electrically-insulating wall positioned to separate the first channel and the second channel.