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公开(公告)号：US20240343403A1
公开(公告)日：2024-10-17
申请号：US18386074
申请日：2023-11-01
发明人： Hyun Ki Cho , Jin Soo Jang , Yoon Cheol Jeon , Jong Pil Kim
IPC分类号： B64D31/00
CPC分类号： B64D31/00 , B64D2221/00
摘要： 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.
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公开(公告)号：US20240343118A1
公开(公告)日：2024-10-17
申请号：US18386059
申请日：2023-11-01
发明人： Hyun Ki Cho , Jin Soo Jang , Yoon Cheol Jeon , Jong Pil Kim
CPC分类号： B60L3/0046 , B60L58/18 , G01R31/1263 , G01R31/14
摘要： 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.
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3.发明公开公开(公告)号：US20240198854A1
公开(公告)日：2024-06-20
申请号：US18200209
申请日：2023-05-22
发明人： Yoon Cheol Jeon , Hyun Ki Cho , Jin Soo Jang
CPC分类号： B60L58/22 , B60L53/20 , B60L58/12 , B64D27/24 , B64U50/34 , H02J7/0048 , B60L2200/10 , B64D2221/00 , H02J2207/20
摘要： 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.
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公开(公告)号：US20220204178A1
公开(公告)日：2022-06-30
申请号：US17381741
申请日：2021-07-21
发明人： Woo Suk Jung , Gwi Taek Kim , Yoon Cheol Jeon , Hyun Ki Cho
摘要： 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.
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公开(公告)号：US20240177615A1
公开(公告)日：2024-05-30
申请号：US18133682
申请日：2023-04-12
发明人： Hyun Ki Cho , Jin Soo Jang , Yoon Cheol Jeon , Jong Pil Kim
CPC分类号： G08G5/003 , B64U10/20 , B64U50/32 , G08G5/0013 , B64U2101/60
摘要： 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.
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6.发明公开公开(公告)号：US20240157799A1
公开(公告)日：2024-05-16
申请号：US18133659
申请日：2023-04-12
发明人： Hyun Ki Cho , Yoon Cheol Jeon , Jin Soo Jang
CPC分类号： B60L3/04 , B60L3/0046 , B60L58/16 , B60W10/08 , B60L2200/10 , B60L2240/549
摘要： 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.
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公开(公告)号：US20240359805A1
公开(公告)日：2024-10-31
申请号：US18380850
申请日：2023-10-17
发明人： Yoon Cheol Jeon , Jin Soo Jang , Jong Pil Kim , Hyun Ki Cho
CPC分类号： B64D31/00 , B60L50/60 , B60L53/00 , B60L58/10 , H01M10/4264 , H01M10/441 , B60L2200/10 , B60L2210/10 , B64D2221/00 , H01M2220/20
摘要： 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.
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公开(公告)号：US11993392B2
公开(公告)日：2024-05-28
申请号：US17381741
申请日：2021-07-21
发明人： Woo Suk Jung , Gwi Taek Kim , Yoon Cheol Jeon , Hyun Ki Cho
摘要： 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.
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公开(公告)号：US11664652B2
公开(公告)日：2023-05-30
申请号：US17389585
申请日：2021-07-30
发明人： Yoon Cheol Jeon , Hyun Woo Jun , Hee Kwang Lee , Hyun Ki Cho , Gwi Taek Kim , Hyun Seok Hong , Woo Suk Jung
CPC分类号： H02H3/20 , B60L3/0046 , B60L50/60 , B64D27/24 , H01H39/00 , H01H85/04 , H02H1/0007 , B60L2200/10
摘要： 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.
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公开(公告)号：US20240336150A1
公开(公告)日：2024-10-10
申请号：US18532539
申请日：2023-12-07
发明人： Jong Pil Kim , Hyun Ki Cho , Yoon Cheol Jeon , Ji Han Lee
IPC分类号： B60L50/75 , B60L3/00 , B60L58/40 , B64D27/355 , B64D27/357 , H01M16/00 , H02J4/00 , H02J7/00 , H02P5/74
CPC分类号： B60L50/75 , B60L3/0046 , B60L58/40 , B64D27/355 , B64D27/357 , H01M16/006 , H02J4/00 , H02J7/0063 , H02P5/74 , B60L2200/10 , B64D2041/005 , B64D2221/00 , H01M2220/20 , H01M2250/20 , H01M2250/402 , H02J2207/20 , H02J2300/30
摘要： 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.
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