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公开(公告)号：US20230057522A1
公开(公告)日：2023-02-23
申请号：US17796682
申请日：2020-03-04
发明人： Kenji FUJIWARA , Hisatoshi FUKUMOTO , Tomoki TAKEGAMI , Tetsuya KOJIMA , Akihiko IWATA , Masahiro SUGAHARA , Hiroshi KOBAYASHI , Mari NISHIYAMA , Akira NISHIZAWA
摘要： A motor control device includes: a step-down device including a DC-output power conversion device having a first mode for outputting first voltage and a second mode for outputting second voltage lower than the first voltage; a power supply device; and a control device, and controls a motor. When a flying object takes off, the control device controls the power conversion device in the first mode. When the control device judges that flight information which is one or both of information of a motor parameter obtained along with control for the motor and information of an environmental factor relevant to the flight altitude of satisfies a predetermined condition, or when the control device has received an mode signal for which the second mode is selected on the basis of the flight information during control for the motor, the control device controls the power conversion device in the second mode.
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公开(公告)号：US20230084424A1
公开(公告)日：2023-03-16
申请号：US17798563
申请日：2020-03-04
发明人： Kenji FUJIWARA , Hisatoshi FUKUMOTO , Tomoki TAKEGAMI , Tetsuya KOJIMA , Akihiko IWATA , Masahiro SUGAHARA , Hiroshi KOBAYASHI , Mari NISHIYAMA , Akira NISHIZAWA
摘要： A motor control device includes: a power source device including a DC-output power conversion device having a first mode for outputting first voltage and a second mode for outputting second voltage higher than the first voltage; a power supply device; and a control device, and controls a motor. When a flying object takes off, the control device controls the power conversion device in the second mode. When the control device judges that flight information which is one or both of information of a motor parameter obtained along with control for the motor and information of an environmental factor relevant to the flight altitude satisfies a predetermined condition, or when the control device has received an operation mode signal for which the first mode is selected on the basis of the flight information during control for the motor, the control device controls the power conversion device in the first mode.
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公开(公告)号：US20240109665A1
公开(公告)日：2024-04-04
申请号：US17754507
申请日：2020-07-29
摘要： To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.
To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.
[Solving Means] An electric aircraft 1 includes: one or two or more electric propulsion systems 20 each including a propeller or fan 21 for propulsion disposed to contribute to a lift of a main wing 11, 12, and an electric motor 22 that drives the propeller or fan 21; and a controller that adjusts the electric propulsion system 20 on the basis of a relationship between a variable relating to an operating state of the electric propulsion system 20 and an aerodynamic force generated on the main wing 11, 12 such that a total thrust by the electric propulsion systems 20 or the aerodynamic force on the main wing 11, 12 has a predetermined value or falls within a predetermined range.
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