Abstract: A battery pack includes at least one battery module including a plurality of battery cells, and a module housing to receive the plurality of battery cells, at least one thermoelectric module disposed outside or inside of the module housing of the battery module and configured to generate voltage when a temperature of the battery module rises to a predetermined temperature or above, and an energy drain unit configured to discharge the battery module when a predetermined magnitude of voltage or above is applied from the thermoelectric module.

Abstract: Provided is a method in an electricity-driven apparatus to be driven by receiving power through a plurality of battery packs in a parallel type. The method includes detecting a state of charge (SOC) of each of the plurality of battery packs, calculating a voltage difference between the plurality of battery packs based on the detected SOC, and performing battery pack balancing based on the calculated voltage difference exceeding a threshold value. The battery pack balancing is performed by a pre-charging circuit including a balancing relay.

Abstract: A system for detecting a defective battery using wireless communications. The system includes first sensors and a first master device. The first sensors are matched on a 1:1 basis with first battery modules to monitor the first battery modules. The first master device communicates with the first sensors. The respective first sensors each include a first monitoring circuit which collects a primary data on a 1:1-matched first battery module in a monitoring mode, and a first communicating circuit which outputs the primary data to the first master device in a communicating mode. The first monitoring circuit is turned off in the communicating mode. The first communicating circuit is turned off in the monitoring mode.

Abstract: The present invention relates to a battery management system and a battery pack and the battery management system according to an embodiment of the present invention includes: a pack voltage sampling unit configured to periodically sample a pack voltage of a battery pack; a pack current sampling unit configured to sample a pack current of the battery pack; and a control unit configured to, after starting to sample the pack voltage of the battery pack, when the pack voltage sampling of the battery pack is completed, record a time from a sampling start time of the pack voltage to a sampling completion time of the pack voltage as a first time, and transmit a voltage sampling synchronization signal for measuring a cell voltage of a battery cell to a plurality of lower-level battery management systems, wherein the control unit performs sampling synchronization on the sampled measurement signal between each lower-level battery management system based on a second time, which is a sampling time at which a cell voltag

Abstract: An auxiliary propulsion apparatus of an air vehicle may include an engine mounted in a fuselage of the air vehicle, a generator configured to be driven using power from the engine, a compressor configured to be driven by the engine or the generator, a battery configured to store electricity generated by the generator, an electricity distributor connected to the generator, the battery and the main propulsion apparatus and configured to distribute electricity generated by the generator to the battery and to a main propulsion apparatus, and at least one nozzle device configured to jet high-pressure gas, supplied from the compressor, to an outside of the fuselage.

Abstract: The present disclosure provides a battery system and a controlling method of the same. The battery system includes a plurality of rechargeable battery packs, and includes a first battery pack that is rechargeable, a second battery pack that is rechargeable independently of the first battery pack, a first switching element that switches the first battery pack between at least a charging node and a discharging node, a second switching element that switches the second battery pack between at least the charging node and the discharging node, and a controller that controls switching states of the first switching element and the second switching element based on usage states and states of charge of the first battery pack and the second battery pack, and thus it is possible to effectively charge a high capacity and high output battery pack.

Abstract: Disclosed is a battery management system and a battery pack and the battery management system includes: a pack voltage sampling unit for periodically sampling a pack voltage of a battery pack; a pack current sampling unit for sampling a pack current of the battery pack; and a control unit for, when the pack voltage sampling of the battery pack is completed, recording a time from a sampling start time of the pack voltage to a sampling completion time of the pack voltage as a first time, and transmitting a voltage sampling synchronization signal for measuring a cell voltage of a battery cell to a plurality of lower-level battery management systems.

Abstract: A power control device is provided for an aircraft. The power control device may include at least one first battery, a second battery having a lower power density and higher energy density than the at least one first battery, at least one lift motor connected, via a first electrical path, to the at least one first battery, a cruise motor connected, via a second electrical path, to the second battery, and a power control circuit configured to control the at least one first battery, the second battery, the at least one lift motor, and the cruise motor.

Abstract: The present disclosure relates to a flight system and a failure responding method therefor. A flight system includes: a plurality of fuse boxes configured to control application of a voltage to at least one propulsion device; and an interlock control apparatus configured to control interlock lines between fuse boxes connected using the interlock lines among the fuse boxes to synchronize and control opening of the fuse boxes connected using the interlock lines.

Abstract: A system for a vehicle may include a first battery pack diagnosis apparatus connected to a first battery pack, a second battery pack diagnosis apparatus connected to a second battery pack, a third battery pack diagnosis apparatus connected to a third battery pack, and a fourth battery pack diagnosis apparatus connected to a fourth battery pack. The first battery pack diagnosis apparatus may be configured to determine, based on a measured value of an integrated insulation resistance of an inverter terminal associated with the vehicle, whether a battery, of the first battery pack, the second battery pack, the third battery pack, or the fourth battery pack, is in a failure state, and based on a determination that the battery is in the failure state and based on individually measured insulation resistance of the first-fourth battery packs, determine a failure position of the battery.

Abstract: A power supply system of an aircraft includes a fuel cell that generates electrical energy, a converter device including a mode switch device that supplies power to a first motor device through a first output terminal and switches a connection between an output node of the fuel cell and the first output terminal, a first battery device that supplies a voltage from a first battery to a second motor device through a second output terminal and connects the second output terminal with the first output terminal under control of the mode switch device, and a processor that controls the mode switch device to enter an emergency mode when detecting an error in the converter device or the first battery device and connects the first output terminal with the second output terminal.

Abstract: A wing frame includes a front wing beam extending in a left-right direction; a rear wing beam extending in the left-right direction and spaced rearward from the front wing beam, and a plurality of rib parts, each of which includes a middle rib coupled to a rear side of the front wing beam and a front side of the rear wing beam.

Abstract: A battery support body may include a bracket extending in a front-rear direction and a shock absorber, which may extend in the front-rear direction and may be coupled to the bracket in a direction crossing the front-rear direction. At least a portion of the shock absorber may be provided in the form of foam.

Abstract: A battery management apparatus can include a measuring unit connected to a battery and configured to operate in a measurement mode during a predetermined measurement time at each preset measurement cycle and measure battery information including at least one of voltage and temperature of the battery while operating in the measurement mode, and a control unit configured to operate in a communication mode during a preset operation time at each preset communication cycle, receive the battery information from the measuring unit while operating in the communication mode, set a next operation time point at which the measuring unit is to operate in the measurement mode based on at least one of the communication cycle and a measurement time, and change an operation time to operate in the communication mode at each subsequent communication cycle to correspond to the measurement time.

Abstract: An auxiliary propulsion apparatus of an air vehicle may include an engine mounted in a fuselage of the air vehicle, a generator configured to be driven using power from the engine, a compressor configured to be driven by the engine or the generator, a battery configured to store electricity generated by the generator, an electricity distributor connected to the generator, the battery and the main propulsion apparatus and configured to distribute electricity generated by the generator to the battery and to a main propulsion apparatus, and at least one nozzle device configured to jet high-pressure gas, supplied from the compressor, to an outside of the fuselage.

Abstract: A battery management apparatus is discussed, and includes: a measuring unit connected to a battery and configured to operate in a measurement mode during a predetermined measurement time at each preset measurement cycle and measure battery information including at least one of voltage and temperature of the battery while operating in the measurement mode; and a control unit configured to operate in a communication mode during a preset operation time at each preset communication cycle, receive the battery information from the measuring unit while operating in the communication mode, set a next operation time point at which the measuring unit is to operate in the measurement mode based on at least one of the communication cycle and a measurement time, and change an operation time to operate in the communication mode at each subsequent communication cycle based on the measurement time.

Abstract: Provided is a method in an electricity-driven apparatus to be driven by receiving power through a plurality of battery packs in a parallel type. The method includes detecting a state of charge (SOC) of each of the plurality of battery packs, calculating a voltage difference between the plurality of battery packs based on the detected SOC, and performing battery pack balancing based on the calculated voltage difference exceeding a threshold value. The battery pack balancing is performed by a pre-charging circuit including a balancing relay.

Abstract: The present disclosure relates to a flight control apparatus, a system including the same, and a method thereof. An example embodiment of the present disclosure provides a flight control apparatus, including: at least one processor, and memory storing instructions that, when executed by the at least one processor, cause the flight control apparatus to determine, based on environmental information and based on variations of a parameter for each operation mode of an aerial vehicle, a flight path among at least one candidate path associated with a destination for the aerial vehicle.

Abstract: An auxiliary propulsion apparatus of an air vehicle may include an engine mounted in a fuselage of the air vehicle, a generator configured to be driven using power from the engine, a compressor configured to be driven by the engine or the generator, a battery configured to store electricity generated by the generator, an electricity distributor connected to the generator, the battery and the main propulsion apparatus and configured to distribute electricity generated by the generator to the battery and to a main propulsion apparatus, and at least one nozzle device configured to jet high-pressure gas, supplied from the compressor, to an outside of the fuselage.

Abstract: The present disclosure relates to a battery pack diagnosis control apparatus, a battery system including the same, and a method thereof. An exemplary embodiment of the present disclosure provides a battery system including: at least one battery pack; a flight control apparatus configured to transmit at least one of a battery discharge mode command or a motor discharge command; a battery control apparatus configured to transmit a relay control command for a relay based on receiving the battery discharge mode command, and transmit a diagnosis command based on receiving the motor discharge command; and at least one battery pack control apparatus configured to control the relay based on receiving the relay control command, and diagnose a failure of the at least one battery pack by measuring a current of the at least one battery pack based on receiving the diagnosis command.