# US 11,095,129 B2 · Capacitor based power system and unmanned vehicle with the capacitor based power system thereof > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,095,129 B2 - Document ID: US11095129B2 - Status: Granted - Kind: B2 - Application number: 15/849,411 - Filed: 2017-12-20 - Published: 2018-07-19 - Granted: 2021-08-17 - Earliest claimed: 2016-02-12 - Assignees: Capacitor Sciences Incorporated - Applicants: Capacitor Sciences Incorporated - Inventors: Ian Kelly-Morgan; Pavel Ivan Lazarev - Web page: https://patentgrep.com/patent/US11095129B2 ## CPC - B64U 10/13: Flying platforms - B64U 30/20: Rotors; Rotor supports - B64U 50/19: using electrically powered motors - H01G 4/005: Electrodes - H01G 4/14: Organic dielectrics - H01G 4/18: of synthetic material, e.g. derivatives of cellulose (H01G4/16 takes precedence) - H01G 4/228: Terminals - H01G 11/56: Solid electrolytes, e.g. gels; Additives therein - H02J 7/52: for charge balancing, e.g. equalisation of charge between batteries - H02J 7/82: Control of state of charge [SOC] - H02M 3/156: with automatic control of output voltage or current, e.g. switching regulators - H02M 3/1582: {Buck-boost converters (H02M3/1584 takes precedence)} - B64D 2221/00: Electric power distribution systems onboard aircraft - B64U 2101/60: for transporting passengers; for transporting goods other than weapons - H02J 7/345: {using capacitors as storage or buffering devices} - H02K 11/0094: {Structural association with other electrical or electronic devices} - Y02T 50/40: Weight reduction - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR - H01G: CAPACITORS; CAPACITORS, RECTIFIERS, DETECTORS, SWITCHING DEVICES, LIGHT-SENSITIVE OR TEMPERATURE-SENSITIVE DEVICES OF THE ELECTROLYTIC TYPE (selection of specified materials as dielectric H01B3/00; capacitors having potential barriers H10D1/62, H10K10/10) - H02J: ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY - H02M: APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF (transformers H01F; dynamo-electric converters H02K47/00; controlling transformers, reactors or choke coils, control or regulation of electric motors, generators or dynamo-electric converters H02P) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - H02K: DYNAMO-ELECTRIC MACHINES (dynamo-electric relays H01H53/00; conversion of DC or AC input power into surge output power {H03K3/53}) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The present disclosure provides an unmanned vehicle comprising a device to be powered; a capacitor energy storage system (CESS) and controller board for at least temporarily powering and operating the device to powered. Further, the CESS includes one or more metacapacitors as an energy storage medium. Additionally, the disclosure provides a capacitor energy storage cell composed of the at least one metacapacitor and a DC-voltage conversion device, where the output voltage of the metacapacitor is the input voltage of the DC-voltage conversion device. Still further, the CESS may be comprised of a module of said capacitor energy storage cells, or a system of modules of said capacitor energy storage cells. ## Claims ### Claim 1 An unmanned aerial vehicle (UAV), comprising: one or more propulsion mechanisms; a capacitor energy storage system configured to at least temporarily discharge power to the one or more propulsion mechanisms; a controller board configured to control the one or more propulsion mechanisms and to power on and off the capacitor energy storage system; wherein the capacitor energy storage system includes one or more metacapacitors, wherein each of the one or more metacapacitors includes a first electrode and a second electrode separated by a layer of metadielectric material with a relative permittivity greater than or equal to 1000 Coulombs2/(Newton-meter2) and a resistivity between 1015 SI cm and 1024 Ω cm; and wherein the layer of metadielectric material includes supramolecular structures of polarizable compounds, and said supramolecular structures of polarizable compounds are comprised of composite organic molecules with at least one enhanced polarizable fragment, and electrically resistive substituents that reduce the electrical interaction of the enhanced polarizable fragments from other supramolecular structures of polarizable compounds in said metadielectric material and said metadielectric material has a resistivity between 1015 Ω·cm and 1024 Ω·cm. ### Claim 2 (depends on 1) The UAV according to claim 1, wherein the capacitor energy storage system includes one or more metacapacitors. ### Claim 3 (depends on 1) The UAV of claim 1, wherein the capacitor energy storage system includes: at least one capacitor energy storage module (CESM), wherein each one of the at least one CESM includes one or more individual capacitor energy storage cells having anodes and cathodes and an interconnection system, wherein each of the one or more individual capacitor energy storage cells includes at least one capacitor energy storage device and a DC-voltage conversion device, wherein the capacitor energy storage device comprises one or more metacapacitors, wherein the output voltage of the capacitor energy storage device is an input voltage of the DC-voltage conversion device during discharging the capacitor energy storage device, wherein the input voltage of the capacitor energy storage device is an output voltage of the DC-voltage conversion device while charging the capacitor energy storage device; an interconnection system coupled to the one or more capacitor energy storage modules, wherein the interconnection system connects the anodes and cathodes of the individual energy storage cells to create a common anode and common cathode of the capacitor energy storage module, wherein each individual capacitor energy storage cell includes one or more metacapacitors coupled to a DC-voltage conversion device; and a power interconnection system and a system controller coupled to the one or more capacitive energy storage modules, through which the capacitor energy storage system discharges to power the device. ### Claim 4 (depends on 3) The UAV of claim 3, wherein the interconnection system of the capacitor energy storage module includes a parameter bus connected to the one or more individual capacitor energy storage cells by power switches; and wherein the capacitor energy storage module of further comprising a power meter coupled to the one or more individual capacitor energy storage cells. ### Claim 5 (depends on 3) The UAV of claim 3 further comprising a networked control node coupled to the one or more individual capacitor energy storage cells. ### Claim 6 (depends on 3) The UAV of claim 3, wherein the system controller includes a deterministic controller, an asynchronous controller, or a controller having distributed clock, an electronic switch and an input device configured to receive a user input, the electronic switch being electrically connected to the at least one CESM for controlling discharge of power from the capacitor energy storage system to the one or more mocw propulsion mechanisms, the input device electrically connected to the electronic switch for controlling a switch-on or a switch-off state of the electronic switch. ### Claim 7 (depends on 3) The UAV of claim 3, wherein the capacitive energy storage cells (CESCs) are configured to be replaceable and charged by power from a DC power generation system or an AC power source and to be discharged to supply power to said unmanned aerial vehicle and its systems, wherein each individual CESC includes at least one capacitive energy storage device (CESD) coupled to a DC-voltage conversion device, wherein each individual CESC includes a control board to stabilize output voltage of the DC-conversion device and to control the charging and discharging of the CESD, wherein the CESD comprises one or more metacapacitors. ### Claim 8 (depends on 3) The UAV of claim 3, wherein the capacitor energy storage system includes two different configurations of CESM, wherein a first configuration of CESM includes a CESC adapted for constant speed operation of the UAV, and a second configuration of CESM includes a CESC adapted for acceleration operation of the UAV. ### Claim 9 (depends on 1) The UAV of claim 1, wherein the metadielectric material has a breakdown field (Ebd) strength between 0.01 V/nm and 2.0 V/nm. ### Claim 10 (depends on 1) The UAV of claim 1, wherein the electrically resistive substituents are alkyl and perhaloalkyl C3-50 chains or fused polycyclic alkyl or partially halogenated alkyl or perhalo alkyl groups, wherein the resistive substituents are longer than 3 nm in one direction. ### Claim 11 (depends on 1) The UAV of claim 1, wherein polarization may include non-linear polarization, hyperpolarization, ionic polarization, electronic polarization, any combination thereof; and wherein hyperpolarizablity and non-linear polarization effects are enhanced due to non-symmetrical positioning of at least 1 electrophilic group, at least 1 nucleophilic group, at least one conjugated rings system fragment, at least one ionic substituent, any combination thereof. ### Claim 12 (depends on 11) The UAV of claim 11, wherein the enhanced polarizable fragments include rylene fragments, naphthalene fragments, anthracene fragments, chromophores, tictoids, zwitterion substituents, ionic liquid substituents, Sharp polymers, Furuta co-polymers, para-Furuta polymers, or any combination thereof. ### Claim 13 (depends on 1) A UAV of claim 1, wherein the supramolecular structures of polarizable compounds include liquid crystal derived structures. ### Claim 14 (depends on 13) The UAV of claim 13, wherein the liquid crystal derived structures include nematic type structures, chematic type structures, chiral nematic type structures, lyotropic type structures or any combination thereof. ### Claim 15 (depends on 14) The UAV of claim 14, wherein the liquid crystal derived structures include lyotropic type structures, wherein the lyotropic type structures are lamellar and micelle structures. ### Claim 16 (depends on 1) The UAV of claim 1, wherein charge is measured by voltage of the capacitor energy storage device. ### Claim 17 (depends on 1) The UAV of claim 1, wherein a device to be powered includes a propulsion unit of the unmanned aerial vehicle. ### Claim 18 (depends on 17) The UAV of claim 17, wherein the propulsion unit includes at least one rotor with rotatable blades, an equivalent number of motor drivers and motors; and wherein the capacitor energy storage system energizes the motor to cause rotation of the rotor including the blades, thereby generating a lift for the unmanned vehicle; and wherein the at least one motor driver and motor are controlled by said controller board; and wherein the capacitor energy storage system is configured to store sufficient energy for the UAV to fly for at least about 10 minutes without recharging. ### Claim 19 (depends on 17) The UAV of claim 17, wherein the unmanned vehicle is configured to bear and deploy a payload weighing at least 0.25 kg; and wherein the said payload is configured to be electrically connected to the capacitor energy storage system; and wherein the capacitor energy storage system is configured to store sufficient energy for the UAV to fly for a minimum of 10 minutes or more of flight time on a full charge. ### Claim 20 (depends on 17) The UAV of claim 17 further comprising a power generation system electrically connected to the capacitor energy storage system and capable of charging said capacitor energy storage system or directly powering said unmanned vehicle.