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公开(公告)号：US20230294837A1
公开(公告)日：2023-09-21
申请号：US18105261
申请日：2023-02-03
发明人： Takeshi Matsumoto
CPC分类号： B64D35/04 , H02J7/1415 , H02J2310/44 , B64D2221/00
摘要： A power supply device includes a power generator, a drive source, a plurality of power supply lines, a plurality of batteries, a difference calculating unit 11, a difference summing unit 12, and an electric power summing unit 13. The difference calculating unit 11 is configured to calculate differences D1, D2, D3, and D4 between a target charge state set for each battery and an estimated charge state. The difference summing unit 12 is configured to sum the differences D1, D2, D3, and D4 calculated by the difference calculating unit 11. The electric power summing unit 13 is configured to sum the charge state calculated by the difference summing unit 12 and electric power used for the electric loads. A control unit 9 controls the drive source such that electric power calculated by the electric power summing unit 13 is generated by the power generator.
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公开(公告)号：US20220306307A1
公开(公告)日：2022-09-29
申请号：US17694748
申请日：2022-03-15
发明人： Daiko Tsutsumi , Akinori Kita , Takeshi Matsumoto , Yuya Ishihara
IPC分类号： B64D31/00 , B64D27/24 , B60L50/61 , B60L53/60 , B60L58/12 , B64D27/10 , B64D27/02 , B64C29/00
摘要： A hybrid aircraft that flies by using a plurality of rotors (takeoff and landing rotors and cruise rotors) includes a generator, a battery charged with power generated by the generator, a plurality of electric motors that rotate the respective rotors by the power generated by the generator and power supplied from the battery, and a controller that sets a target remaining capacity of the battery according to a flight state of the aircraft and controls charging and discharging of the battery so that the remaining capacity of the battery approaches the target remaining capacity.
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公开(公告)号：US20220194577A1
公开(公告)日：2022-06-23
申请号：US17537546
申请日：2021-11-30
发明人： Akinori Kita , Takeshi Matsumoto , Daiko Tsutsumi
摘要： An aircraft propulsion system capable of reducing a rotational load of an engine shaft is provided. An aircraft propulsion system includes a plurality of engines (60-1 and 60-2) and a controller (100). When a flight state is a first state, the controller (100) causes some of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine. At least one engine (60-1) of the plurality of engines (60-1 and 60-2) includes a bleed air hole (71-1), a bleed air pipe (72-1), and a bleed air valve (73-1). When causing the engine (60-2) which has stopped to start up again, the controller (100) opens a bleed air valve (73-1) in the engine (60-1) which is in operation and supplies compressed air of the compressor (62-1) to the compression chamber (64-2) of the engine (60-2) which has stopped.
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公开(公告)号：US11799315B2
公开(公告)日：2023-10-24
申请号：US17697010
申请日：2022-03-17
发明人： Yuya Ishihara , Daiko Tsutsumi , Takeshi Matsumoto
CPC分类号： H02J7/345 , B60L50/40 , B60L50/60 , B60L58/22 , G01R31/3835 , H02J7/0013 , H02J7/0063 , B60L2240/547
摘要： Before power is supplied to a load from a capacitor and a plurality of batteries, a battery for initially supplying power for charging to the capacitor is determined from among the plurality of batteries, based on a result of acquiring the voltage of each battery, and voltage equalization of the plurality of batteries is performed in response to power for charging being supplied to the capacitor from the determined battery.
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公开(公告)号：US20220311269A1
公开(公告)日：2022-09-29
申请号：US17697010
申请日：2022-03-17
发明人： Yuya Ishihara , Daiko Tsutsumi , Takeshi Matsumoto
摘要： Before power is supplied to a load from a capacitor and a plurality of batteries, a battery for initially supplying power for charging to the capacitor is determined from among the plurality of batteries, based on a result of acquiring the voltage of each battery, and voltage equalization of the plurality of batteries is performed in response to power for charging being supplied to the capacitor from the determined battery.
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公开(公告)号：US11795834B2
公开(公告)日：2023-10-24
申请号：US17683388
申请日：2022-03-01
发明人： Takeshi Matsumoto , Akinori Kita
CPC分类号： F01D15/10 , F02C9/48 , H02P9/04 , H02P9/107 , B64D2027/026 , F02C6/20 , F02C7/36 , F04D27/02 , F05D2220/323 , F05D2220/76 , F05D2270/021 , F05D2270/022 , F05D2270/042 , F05D2270/052 , F05D2270/304 , F05D2270/309 , F05D2270/335 , H02P9/102 , H02P9/105
摘要： An aircraft propulsion system includes a gas turbine engine; a generator; a storage battery; a motor which drives a rotor, using at least one of the electric power which is output from the generator and the electric power which is output from the storage battery; a detection unit which detects the number of revolutions of the engine shaft; an engine control unit which controls at least a fuel flow rate of the gas turbine engine; and a generator control unit which controls the operation of the generator. When the number of revolutions satisfies a predetermined condition, at least the generator control unit executes a control for reducing a sudden change in the number of revolutions.
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公开(公告)号：US20230299605A1
公开(公告)日：2023-09-21
申请号：US18115010
申请日：2023-02-28
发明人： Masashi Eto , Takeshi Matsumoto , Daiko Tsutsumi
CPC分类号： H02J7/007182 , H02J7/0063 , H02J7/0014 , B64D27/24 , B60L50/60 , B60L2200/10
摘要： A power supply device includes a power generator, a drive source, a plurality of power supply lines, a plurality of batteries, a diode, a difference calculating unit 11, 12, 13, or 14, and a difference summing unit 16. The difference calculating unit 11, 12, 13, or 14 is configured to calculate a difference between demanded electric power P1, P2, P3, or P4 in the corresponding power supply line and a charge state of the corresponding battery. The difference summing unit 16 is configured to sum the differences in electric power in the power supply lines calculated by the difference calculating units 11, 12, 13, and 14. In the power supply device, the drive source is controlled such that electric power equal to or higher than the electric power calculated by the difference summing unit 16 is generated by the power generator.
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公开(公告)号：US20230272748A1
公开(公告)日：2023-08-31
申请号：US18173992
申请日：2023-02-24
发明人： Takeshi Matsumoto
CPC分类号： F02C7/22 , F01D15/10 , F02C6/14 , F05D2220/76
摘要： When the output power of a gas turbine is going to be reduced and when the relationship between the target output power and the rotational frequency of the gas turbine satisfies predetermined conditions, a control device of a power unit system reduces the output power of the gas turbine to the target output power and thereafter reduces the rotational frequency of the gas turbine to the target rotational frequency, whereas when the relationship between the target output power and the rotational frequency of the gas turbine does not satisfy the predetermined conditions, the control device reduces the rotational frequency of the gas turbine to the target rotational frequency and thereafter reduces the output power of the gas turbine to the target output power.
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公开(公告)号：US20230099869A1
公开(公告)日：2023-03-30
申请号：US17946070
申请日：2022-09-16
发明人： Akinori Kita , Takeshi Matsumoto
IPC分类号： B64D27/24 , B64D27/10 , B64D31/00 , B64D35/08 , B64D45/00 , B60L50/61 , F02K3/00 , H01M10/42
摘要： The propulsion system have a load change detecting unit detecting a load change and an operating point control unit controlling power operating points defined using a torque T and a rotation number Ne. The operating point control unit calculates target power operating points 44 and 54 corresponding to the load after change for first power operating points 41 and 51 that are current power operating points in a case in which a change in the load is detected by the load change detecting unit. By changing the fuel flow in a range not exceeding a predetermined fuel line, the operating point control unit moves the power operating points from first power operating points 41 and 51 to second power operating points 42 and 52, third power operating points 43 and 53, and target power operating points 44 and 54 in order.
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公开(公告)号：US20230076465A1
公开(公告)日：2023-03-09
申请号：US17898501
申请日：2022-08-30
发明人： Akinori Kita , Takeshi Matsumoto
摘要： A load fluctuation detection unit that detects a load fluctuation of an aircraft, and an operating point control unit that controls a power operating point defined by a torque and rotation speed based on a flight state. The operating point control unit sets a target power operating point (62) for coping with a load with respect to an initial power operating point (61) in an operating point map (40) when the load has fluctuated. The operating point control unit moves the power operating point from the initial power operating point (61) on a first operating line (41) to the target power operating point (62) on a second operating line (42), to a return power operating point (63) on the first operating line (41) while keeping a torque T constant, and then to the initial power operating point (61) along the first operating line (41).
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