# US 12,179,611 B2 · Electrical energy storage system for an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,179,611 B2 - Document ID: US12179611B2 - Status: Granted - Kind: B2 - Application number: 18/134,624 - Filed: 2023-04-14 - Published: 2023-11-02 - Granted: 2024-12-31 - Earliest claimed: 2022-04-29 - Assignees: Airbus Urban Mobility GmbH - Applicants: Airbus Urban Mobility GmbH - Inventors: Michael Geiss - Web page: https://patentgrep.com/patent/US12179611B2 ## CPC - H02J 7/667: {disconnection of loads if battery is not under charge, e.g. in vehicle if engine is not running} - B60L 3/0046: {relating to electric energy storage systems, e.g. batteries or capacitors} - B60L 50/60: using power supplied by batteries (in combination with fuel cells B60L50/75) - B60L 58/10: for monitoring or controlling batteries - B64D 27/34: All-electric aircraft - B64D 27/35: Arrangements for on-board electric energy production, distribution, recovery or storage - B64D 27/357: using batteries - H02J 1/086: {for providing alternative feeding paths between load or loads and source or sources when the main path fails} - H02J 7/60: including safety or protection arrangements - H02J 7/855: {with circuits adapted for supplying loads from the battery} - B60L 2200/10: Air crafts - H02J 2105/32: {for aircrafts} - H02J: ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY - B60L: PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES (arrangements or mounting of electrical propulsion units or of plural diverse prime-movers for mutual or common propulsion in vehicles B60K1/00, B60K6/20; arrangements or mounting of electrical gearing in vehicles B60K17/12, B60K17/14; preventing wheel slip by reducing power in rail vehicles B61C15/08; dynamo-electric machines H02K; control or regulation of electric motors H02P); SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES (electric coupling devices combined with mechanical couplings of vehicles B60D1/64; electric heating for vehicles B60H1/00); ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL (control or regulation of electric motors H02P); MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT ## Abstract An electrical energy storage system for an aircraft, comprising at least one electrical energy storage unit with power supply lines and an energy source that is configured to store electrical energy and to supply electrical power at a predetermined voltage range via the power supply lines, wherein the at least one electrical energy storage unit comprises a power switching unit that is adapted to operate in an associated supply mode for supplying electrical power from the energy source via the power supply lines, and to operate in an associated disconnect mode for disconnecting the energy source from the power supply lines. ## Claims ### Claim 1 An electrical energy storage system for an aircraft, comprising at least one electrical energy storage unit with power supply lines and an energy source that is configured to store electrical energy and to supply electrical power at a predetermined voltage range via the power supply lines, wherein the at least one electrical energy storage unit comprises: a power switching unit that is adapted to operate in an associated supply mode for supplying electrical power from the energy source via the power supply lines, and to operate in an associated disconnect mode for disconnecting the energy source from the power supply lines; a driver enable stage that comprises at least a first enable channel and a second enable channel, wherein each one of the first enable channel and the second enable channel is adapted to operate in one of an enable mode and a disable mode; and a switch driver unit that is adapted to operate in one of an enable mode and a disable mode; wherein the power switching unit is configured to operate in the supply mode if the switch driver unit and at least one of the first enable channel and the second enable channel are operated in enable mode, and wherein the power switching unit is configured to operate in the disconnect mode if the switch driver unit is operated in disable mode, or if both the first enable channel and the second enable channel are operated in disable mode. ### Claim 2 (depends on 1) The electrical energy storage system of claim 1, further comprising: a first trigger source that is connected to the first enable channel; and a second trigger source that is connected to the second enable channel; wherein the first trigger source is configured to switch the first enable channel between enable mode and disable mode; and wherein the second trigger source is configured to switch the second enable channel between enable mode and disable mode. ### Claim 3 (depends on 2) The electrical energy storage system of claim 2, wherein the first enable channel comprises a first diode, and the first trigger source comprises a first safety switch; and wherein the second enable channel comprises a second diode, and the second trigger source comprises a second safety switch. ### Claim 4 (depends on 3) The electrical energy storage system of claim 3, wherein the first enable channel is enabled if the first safety switch is in closed state, and disabled if the first safety switch is in opened state; and wherein the second enable channel is enabled if the second safety switch is in closed state, and disabled if the second safety switch is in opened state. ### Claim 5 (depends on 4) The electrical energy storage system of claim 4, wherein the second trigger source further comprises a discrete command unit; and wherein the second safety switch is a safety relay. ### Claim 6 (depends on 5) The electrical energy storage system of claim 5, wherein the discrete command unit is embodied by means of a flight management system or protection logic of an aircraft to which the electrical energy storage system is mounted. ### Claim 7 (depends on 5) The electrical energy storage system of claim 5, wherein the discrete command unit is configured to switch the safety relay between closed state and opened state on the basis of current operating conditions of an aircraft to which the electrical energy storage system is mounted. ### Claim 8 (depends on 2) The electrical energy storage system of claim 2, wherein the first trigger source further comprises an impact switch that is configured to switch the first enable channel to disable mode in response to detection of an impact on the first trigger source. ### Claim 9 (depends on 2) The electrical energy storage system of claim 2, wherein the second trigger source further comprises an impact switch that is configured to switch the second enable channel to disable mode in response to detection of an impact on the second trigger source. ### Claim 10 (depends on 1) The electrical energy storage system of claim 1, further comprising a discharge control function unit that is connected to the switch driver unit and adapted to command the switch driver unit to operate either in enable mode or disable mode. ### Claim 11 (depends on 10) The electrical energy storage system of claim 10, wherein the discharge control function unit is configured to command the switch driver unit on the basis of predetermined operating conditions of an aircraft to which the electrical energy storage system is mounted. ### Claim 12 (depends on 10) The electrical energy storage system of claim 10, wherein the discharge control function unit is embodied by means of a battery management system associated with the energy source. ### Claim 13 (depends on 1) The electrical energy storage system of claim 1, wherein the power switching unit comprises at least one power switching device with a magnetic switch and an associated switch control coil; wherein the magnetic switch is arranged in one of the power supply lines; and wherein the associated switch control coil is connected to the switch driver unit, the first enable channel, and the second enable channel. ### Claim 14 (depends on 13) The electrical energy storage system of claim 13, wherein the magnetic switch is closed in supply mode of the power switching unit by means of the associated switch control coil. ### Claim 15 (depends on 1) An aircraft with an electrical energy storage system according to claim 1. ### Claim 16 (depends on 2) The electrical energy storage system of claim 2, wherein the first enable channel comprises a first circuitry, and the first trigger source comprises a first safety switch; and wherein the second enable channel comprises a second circuitry, and the second trigger source comprises a second safety switch. ### Claim 17 An electrical energy storage system for an aircraft, the electrical energy storage system comprising: an electrical energy storage unit with power supply lines and an energy source configured to store electrical energy and to supply electrical power at a predetermined voltage range via the power supply lines, wherein the electrical energy storage unit comprises: a power switching unit adapted to operate in an associated supply mode for supplying electrical power from the energy source via the power supply, and to operate in an associated disconnect mode for disconnecting the energy source from the power supply; a driver enable stage comprising a first enable channel and a second enable channel, with one of the first enable channel and the second enable channel adapted to operate in one of an enable mode and a disable mode; and a switch driver unit adapted to operate in one of an enable mode and a disable mode; wherein the power switching unit is configured to operate in the supply mode if the switch driver unit and at least one of the first enable channel and the second enable channel are operated in enable mode, and wherein the power switching unit is configured to operate in the disconnect mode if the switch driver unit is operated in disable mode, or if both the first enable channel and the second enable channel are operated in disable mode. ### Claim 18 (depends on 17) The electrical energy storage system of claim 17, further comprising: a first trigger source connected to the first enable channel; and a second trigger source connected to the second enable channel; wherein the first trigger source is configured to switch the first enable channel between enable mode and disable mode; and wherein the second trigger source is configured to switch the second enable channel between enable mode and disable mode. ### Claim 19 (depends on 18) The electrical energy storage system of claim 18, wherein the first enable channel comprises a first diode, and the first trigger source comprises a first safety switch; and wherein the second enable channel comprises a second diode, and the second trigger source comprises a second safety switch, wherein the first enable channel is enabled if the first safety switch is in closed state, and disabled if the first safety switch is in opened state; and wherein the second enable channel is enabled if the second safety switch is in closed state, and disabled if the second safety switch is in opened state. ### Claim 20 An electrical energy storage system for an aircraft, the electrical energy storage system comprising: an electrical energy store with power supply lines and an energy source configured to store electrical energy and to supply electrical power at a predetermined voltage range via the power supply lines, wherein the electrical energy store comprises: a power switch adapted to operate in an associated supply mode for supplying electrical power from the energy source via the power supply, and to operate in an associated disconnect mode for disconnecting the energy source from the power supply; a driver enable stage comprising a first enable channel and a second enable channel, with one of the first enable channel and the second enable channel adapted to operate in one of an enable mode and a disable mode; and a switch driver operable in one of an enable mode and a disable mode; wherein the power switch is operable in the supply mode if the switch driver and at least one of the first enable channel and the second enable channel are operated in enable mode, and wherein the power switch is operable in the disconnect mode if the switch driver is operated in disable mode, or if both the first enable channel and the second enable channel are operated in disable mode.