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: Disclosed are an apparatus for controlling a battery of air mobility and a method thereof. The apparatus maximizes the efficiency of a plurality of batteries provided in the air mobility by classifying the plurality of battery modules into a first battery group with high power characteristics and a second battery group with high energy characteristics, using power from the first battery group as a power source during takeoff and landing of the air mobility, and using power from the second battery group as the power source during cruising of the air mobility.

Abstract: An apparatus and method for controlling battery thermal management of a vehicle include at least one sensor that detects a temperature and a voltage of a plurality of battery cells in a battery module, a heating device that generates heat, and a processor that controls an operation of the heating device based on a location in which thermal runaway occurs in the battery module when determining that the thermal runaway occurs in the battery cell of the plurality of battery cells located within the battery module based on the temperature and the voltage of the battery cell.

Abstract: Provided is a method in which a management server provides wireless LAN security policy by participating in multiple APs. The method includes a step of receiving terminal information of a terminal, which is acquired in a process of scanning broadcasting information of multiple APs, from each of the multiple APs, a step of issuing and storing a token for opening a wireless LAN data channel to each of the multiple APs on the basis of reception time points of the terminal information, a step of receiving a token request for opening a wireless LAN data channel to an AP to be accessed, selected by a terminal among the multiple APs, and a step of distributing, to the terminal, a token of the AP to be accessed corresponding to the token request.

Abstract: An integrated cleaning module of a vehicle sensor includes a washing liquid supply module configured to supply cleaning liquid; and an air supply module connected to the washing liquid supply module and configured to supply air. The air supply module includes a compressor configured to generate compressed air; an air tank in which the compressed air generated by the compressor is stored; and an integrated dispenser configured to be in fluid connection with the washing liquid supply module and the air tank. The integrated dispenser is configured to distribute the cleaning liquid and the compressed air.

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: 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: 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 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: 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: 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.

Abstract: An emergency power management system of a mobility, may include a fuse device connected to a battery and including a first circuit and a second circuit in which a first fuse and a second fuse are respectively provided and are connected in parallel, a pyro switch provided between the first circuit and the second circuit, and configured to establish electric connection with the first circuit in ordinary times and to release electric connection with the first circuit and to establish electric connection with the second circuit in a case of emergency, a determiner configured to determine abnormality of the first fuse based on current applied from the high-voltage battery or voltages at opposite end portions of the first fuse, and a controller configured to operate the pyro switch when abnormality occurs in the first fuse.

Abstract: A battery module having a plurality of stacked battery module units is provided. The battery module unit includes a cooling fin in which an interval between two cooling plates facing each other is expandable and contractible. A battery cell is in contact with each of the two cooling plates and having lead tabs at each end. Protruding steps extend from both ends of the cooling plates to maximize a contact area with the lead tabs of the battery cell. Lead tab fasteners are coupled to the protruding steps to fix the lead tabs of the battery cell to the protruding steps. The lead tap fasteners include connecting grooves and connecting protrusions relative to each other to be coupled by a linear relative movement with lead tap fasteners of an adjacent battery module unit.

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: An emergency power management system of a mobility, may include a fuse device connected to a battery and including a first circuit and a second circuit in which a first fuse and a second fuse are respectively provided and are connected in parallel, a pyro switch provided between the first circuit and the second circuit, and configured to establish electric connection with the first circuit in ordinary times and to release electric connection with the first circuit and to establish electric connection with the second circuit in a case of emergency, a determiner configured to determine abnormality of the first fuse based on current applied from the high-voltage battery or voltages at opposite end portions of the first fuse, and a controller configured to operate the pyro switch when abnormality occurs in the first fuse.