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公开(公告)号：US20210016880A1
公开(公告)日：2021-01-21
申请号：US16651173
申请日：2018-09-27
摘要： An autonomous flying device achieving a large payload and a long continuous flight tune and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.
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公开(公告)号：US20240336379A1
公开(公告)日：2024-10-10
申请号：US18681620
申请日：2022-10-06
发明人： Mitsuru Ishikawa
摘要： A flight device in which a mechanism for transmitting power is simplified is provided. The flight device 10 includes an airframe 19, main rotors 14, an engine 30, and power transmission shafts 25. The main rotors 14 are rotated to generate drive force that causes the airframe 19 to lift. The engine 30 includes crankshafts. The power transmission shafts 25 are connected to the crankshafts. Moreover, the engine 30 rotates the main rotors 14 via the power transmission shafts 25. The power transmission shafts 25 are tilted with respect to a second direction D2.
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公开(公告)号：US11975821B2
公开(公告)日：2024-05-07
申请号：US17755898
申请日：2020-10-27
发明人： Mitsuru Ishikawa , Taro Fukuda , Takuma Takezawa , Nobuyuki Tada
CPC分类号： B64C25/12 , B64C25/20 , B64C39/024
摘要： Provided is a flight device that can surely perform transformation operations of legs supporting a fuselage base in landing. A flight device 10 includes: a fuselage base 14; a first leg 26 provided on the fuselage base 14 and transformable between a flight state and a landing state; a second leg 27 provided on the fuselage base 14 as a separate body from the first leg 26 and transformable between the flight state and the landing state; a first drive unit 281 and a second drive unit 282 configured to drive transformation operations of the first leg 26 and the second leg 27; and an operation interconnecting mechanism 16 configured to interconnect the first leg 26 and the second leg 27 in terms of operation.
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公开(公告)号：US20230221166A1
公开(公告)日：2023-07-13
申请号：US17928380
申请日：2022-03-29
发明人： Yasutoshi Ono , Mitsuru Ishikawa
CPC分类号： G01G19/08 , B64U50/30 , B64U50/19 , G05D1/0816 , B64C39/024 , B64U2101/40
摘要： The present invention provides a flying apparatus that can accurately measure a weight of a transported objected in a simple configuration. The flying apparatus 10 includes rotors 11, motors 12, a flight sensor 13, an electric power conversion unit 14, and a computation control unit 15. The flight sensor 13 measures physical quantities acting on a fuselage base portion 16. The computation control unit 15 generates instruction signals based on the physical quantities to cause the fuselage base portion 16 to be at a predetermined position in a predetermined attitude. The electric power conversion unit 14 adjusts amounts of electric power supplied to the motors 121 and the like based on the received instruction signals. Moreover, the computation control unit 15 calculates an estimated weight that is an estimation value of a weight of the transported object, based on magnitudes of the instruction signals.
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公开(公告)号：US20240343423A1
公开(公告)日：2024-10-17
申请号：US18683158
申请日：2022-10-06
发明人： Mitsuru Ishikawa , Takahito Sekita
IPC分类号： B64U50/10 , B64U10/16 , B64U101/00
CPC分类号： B64U50/10 , B64U10/16 , B64U2101/00
摘要： A flight device that can accurately perform attitude control with a sub-rotor is provided. The flight device 10 includes an airframe 19, an engine 30, motors 21, main rotors 14, and sub-rotors 15. The engine 30 rotates the main rotors 14. The motors 21 rotate the sub-rotors 15. The main rotors 14 are arranged below the sub-rotors 15. In the flight device 10, arranging the main rotors 14 below the sub-rotors 15 prevents the sub-rotors 15 from being affected by an air flow generated by rotation of the main rotors 14. Accordingly, the sub-rotors 15 can provide thrusts as designed by being rotated, and the position and the attitude of the airframe 19 can be accurately adjusted.
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公开(公告)号：US20240343421A1
公开(公告)日：2024-10-17
申请号：US18294290
申请日：2022-08-02
发明人： Mitsuru Ishikawa
IPC分类号： B64U10/16 , B64D27/357 , B64U50/19
CPC分类号： B64U10/16 , B64D27/357 , B64U50/19
摘要： Provided is a flight device that includes multiple drive sources and that can continuously fly even when one of the drive sources stops in flight, by using the other drive source. The flight device 10 includes a first drive system 11 and a second drive system 12. The first drive system 11 includes a battery 27, rotor 151 and the like configured to be rotated by energy supplied from the battery 27, and a first control unit 20 configured to control the numbers of revolutions of the rotor 151 and the like depending on a flight condition. The second drive system includes the battery 27, rotor 181 and the like configured to be rotated by energy supplied from the battery 27, and a second control unit 21 configured to control the numbers of revolutions of the rotor 181 and the like depending on the flight condition. In the emergency flight state, when the first drive system 11 stops, the flight device 10 lands by rotating the rotor 151 and the like, and when the second drive system 12 stops, the flight device 10 lands by rotating the rotor 181 and the like.
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公开(公告)号：US20240343425A1
公开(公告)日：2024-10-17
申请号：US18294249
申请日：2022-08-02
摘要： An engine-carrying flight device capable of stably hovering is provided. The engine-carrying flight device 10 can fly in a hovering state in which an altitude is maintained and in an ascending/descending state in which the altitude is changed. The engine-carrying flight device 10 includes main rotors 14, sub-rotors 15, an engine 26; motors 21; and an arithmetic control unit 25. The main rotors 14 are rotated by drive force received from the engine 26, the sub-rotors 15 are rotated by drive force received from the motors 21, and the arithmetic control unit 25 causes a thrust generated by rotation of the main rotors 14 to be smaller than a thrust necessary for keeping the altitude constant, in the hovering state.
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公开(公告)号：US20230042223A1
公开(公告)日：2023-02-09
申请号：US17971831
申请日：2022-10-24
摘要： An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.
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公开(公告)号：US20220388635A1
公开(公告)日：2022-12-08
申请号：US17755898
申请日：2020-10-27
发明人： Mitsuru ISHIKAWA , Taro FUKUDA , Takuma TAKEZAWA , Nobuyuki TADA
摘要： Provided is a flight device that can surely perform transformation operations of legs supporting a fuselage base in landing. A flight device 10 includes: a fuselage base 14; a first leg 26 provided on the fuselage base 14 and transformable between a flight state and a landing state; a second leg 27 provided on the fuselage base 14 as a separate body from the first leg 26 and transformable between the flight state and the landing state; a first drive unit 281 and a second drive unit 282 configured to drive transformation operations of the first leg 26 and the second leg 27; and an operation interconnecting mechanism 16 configured to interconnect the first leg 26 and the second leg 27 in terms of operation.
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公开(公告)号：US20190338679A1
公开(公告)日：2019-11-07
申请号：US16480162
申请日：2017-07-05
发明人： Toru Kano
摘要： Provided is an opposed-piston engine which attains high output, ensures combustion toughness, and includes a simplified configuration of a crankshaft counter-rotation synchronization mechanism which rotates crankshafts in engine units in opposite directions. An opposed-piston engine 10 of the present invention includes a first engine unit 11 and a second engine unit 21. The first engine unit 11 and the second engine unit 21 respectively include a first cylinder 12 and a second cylinder 22 independent of each other. In addition, a first valve driving mechanism 19 and a second valve driving mechanism 20 which control valves also function as a crankshaft counter-rotation synchronization mechanism 29 which rotates a first crankshaft 14 of the first engine unit 11 and a second crankshaft 24 of the second engine unit 21 in the opposite directions.
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