Patent ID: 11932396
Assignee: BLUEHALO, LLC
Field: Measurement (Instruments)
Classification: CPC B  G  H | IPC B  G  H

Claim 0:
1. An unmanned aerial vehicle comprising:
a. a central body comprising:
i. a first enclosure comprising:
1. a first top wall;
2. a first bottom wall;
3. at least one first side wall connecting the first top wall and the first bottom wall such that the first top wall, the first bottom wall, and the at least one first side wall define a first chamber;
wherein the first top wall, the first bottom wall, and the at least one first side wall comprise a first continuous covering of a first conductive material on a first outer surface thereof to inhibit electromagnetic fields;

4. a plurality of low voltage components positioned in the first chamber, and wherein the plurality of low voltage components comprises:
1. a first signal processing system comprising:
 a. a first antenna interface operatively connected to a first antenna outside the central body and configured to receive a first plurality of input radio frequency signals;
 b. at least one first bandpass filter, wherein the at least one first bandpass filter is operatively connected to the first antenna interface, and wherein the at least one first bandpass filter is configured to:
 i. obtain, from the first antenna via the first antenna interface, the first plurality of input radio frequency signals; and
 ii. filter the first plurality of input radio frequency signals to provide a second plurality of input radio frequency signals;
 c. at least one first notch filter, wherein the at least one first notch filter is operatively connected to the at least one first bandpass filter, and wherein the at least one first notch filters is configured to:
 i. obtain, from the at least one first bandpass filter, the second plurality of input radio frequency signals; and
 ii. filter the second plurality of radio frequency signals to attenuate a first desired range of frequencies and provide a third plurality of input radio frequency signals;
 d. a first varistor operatively connected to the at least one first notch filter and configured to:
 i. obtain, from the at least one first notch filter, the third plurality of input radio frequency signals; and
 ii. clamp a first voltage of the third plurality of input radio frequency signals based on a first selected clamping voltage;
 e. a first radio transceiver interface operatively connected to the first varistor configured to receive the clamped third plurality of input radio frequency signals;
2. a first radio transceiver operatively connected to the radio transceiver interface and configured to receive the clamped third plurality of input radio frequency signals including control information included therein,
3. a flight controller operatively connected to the first radio transceiver and configured to receive the third plurality of input radio frequency signals and the control information and provide a plurality of control signals to direct movement of the unmanned aerial vehicle based on the third plurality of input radio frequency signals;
4. a second signal processing system comprising:
 a. a second antenna interface operatively connected to a second antenna outside the central body and configured to receive a fourth plurality of input radio frequency signals;
 b. at least one second bandpass filter, wherein the at least one second bandpass filter is operatively connected to the second antenna interface, and wherein the at least one second bandpass filter is configured to:
 i. obtain, from the second antenna interface, the fourth plurality of input radio frequency signals; and
 ii. filter the fourth plurality of radio frequency signals to provide a fifth plurality of radio frequency signals;
 c. at least one second notch filter, wherein the at least one second notch filter is operatively connected to the at least one second bandpass filter, and wherein the at least one second notch filter is configured to:
 i. obtain, from the at least one second bandpass filter, the fifth plurality of input radio frequency signals; and
 ii. filter the fifth plurality of radio frequency signals to attenuate a second desired range of frequencies and provide a sixth plurality of radio frequency signals;
 d. a second varistor operatively connected to the at least one second notch filter and configured to:
 i. obtain, from the at least one second notch filter, the sixth plurality of input radio frequency signals; and
 ii. clamp a second voltage of the sixth plurality of input radio frequency signals based on a second selected clamping voltage;
 e. a second radio transceiver interface operatively connected to the second varistor and configured to receive the clamped sixth plurality of input radio frequency signals from the second varistor;
5. a second radio transceiver operatively connected to the second radio transceiver interface and configured to receive the clamped sixth plurality of input radio frequency signals including navigation information included therein;
6. a navigation system operatively connected to the second radio transceiver and configured to receive the clamped sixth plurality of input radio frequency signals, and generate three-dimensional position information associated with the unmanned aerial vehicle in three-dimensional space based on the sixth plurality of input radio frequency signals and the navigation information;

ii. a voltage feedthrough connector operatively connected to the flight controller and the navigation system in the first enclosure, and configured to provide power from a power distribution module in a second enclosure;
iii. the second enclosure operatively connected to the first enclosure comprising:
1. a second top wall;
2. a second bottom wall;
3. at least one second side wall connecting the second top wall and the second bottom wall such that the second top wall, the second bottom wall, and the at least one second side wall define a second chamber;
wherein the second top wall, the second bottom wall, and the at least one second side wall comprise a second continuous covering of a second conductive material on a second outer surface thereof to inhibit electromagnetic fields;

4. a plurality of high voltage components positioned in the second chamber, and wherein the plurality of high voltage components comprises:
a. a plurality of electronic speed controllers operatively connected to the flight controller via the voltage feedthrough connector, and configured to:
 i. obtain the plurality of control signals provided by the flight controller; and
 ii. generate a first plurality of motor speed signals based on the plurality of control signals provided by the flight controller;
b. the power distribution module operatively connected to the flight controller via the voltage feedthrough connector and operatively connected to each electronic speed controller of the plurality of electronic speed controllers,
 wherein the power distribution module is configured to distribute a low voltage power input to the flight controller via the voltage feedthrough connector,
 and wherein the power distribution module is configured to distribute a high voltage input to the plurality of electronic speed controllers;
c. an input power interface operatively connected to a voltage source outside the central body via an input power filter, wherein the voltage source is configured to provide power to the power distribution module; and
d. a plurality of high power filters, wherein each respective high power filter is operatively connected to a respective electronic speed controller of the plurality of electronic speed controllers, and wherein each high power filter is configured to:
 i. obtain respective motor speed signals generated by the respective electronic speed controller; and
 ii. filter the respective motor speed signals to generate respective filtered motor speed signals;

b. at least one electric motor operatively connected to the central body and electrically connected to at least one high power filter of the plurality of high power filters, the at least one electric motor operatively connected to at least one propeller such that the at least one propeller is rotatable by the at least one electric motor, and wherein each respective at least one electric motor is configured to:
i. obtain the respective filtered motor speed signals from the at least one high power filter; and
ii. rotate the at least one propeller based on the respective filtered motor speed signals;

c. a barometric pressure feedthrough having a first length and a first diameter and configured to pass air through the central body of the unmanned aerial vehicle.