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公开(公告)号：US09180976B2
公开(公告)日：2015-11-10
申请号：US14193161
申请日：2014-02-28
Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
Inventor： Hiroshi Kobayashi , Akira Nishizawa
Abstract: The present invention provides an electric propulsion system control apparatus that uses electric means alone so that effects pertaining to weight and cost are suppressed, is capable of accurate detection even when an airspeed has a binary relationship with a torque and a rotation speed of a propeller, and thereby exhibits improved detection precision and responsiveness. The electric propulsion system control apparatus drives a propulsion propeller to rotate, and is configured to estimate the airspeed from a data set stored in advance in relation to the airspeed and a propeller characteristic, and a plurality of torque and rotation speed estimation values detected under different driving conditions.
Abstract translation: 本发明提供了一种电动推进系统控制装置，其单独使用电气装置，以便抑制与重量和成本有关的影响，即使当空速与螺旋桨的转矩和转速具有二元关系时，也能够进行精确检测， 从而表现出提高的检测精度和响应性。 电动推进系统控制装置驱动推进螺旋桨旋转，并且被配置为从相对于空速和螺旋桨特性预先存储的数据集估计空速，以及在不同的速度下检测的多个转矩和转速估计值 驾驶条件。
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公开(公告)号：US20140257599A1
公开(公告)日：2014-09-11
申请号：US14193161
申请日：2014-02-28
Applicant: Japan Aerospace Exploration Agency
Inventor： Hiroshi Kobayashi , Akira Nishizawa
IPC: B64D31/06
Abstract: The present invention provides an electric propulsion system control apparatus that uses electric means alone so that effects pertaining to weight and cost are suppressed, is capable of accurate detection even when an airspeed has a binary relationship with a torque and a rotation speed of a propeller, and thereby exhibits improved detection precision and responsiveness. The electric propulsion system control apparatus drives a propulsion propeller to rotate, and is configured to estimate the airspeed from a data set stored in advance in relation to the airspeed and a propeller characteristic, and a plurality of torque and rotation speed estimation values detected under different driving conditions.
Abstract translation: 本发明提供了一种电动推进系统控制装置，其单独使用电气装置，以便抑制与重量和成本有关的影响，即使当空速与螺旋桨的转矩和转速具有二元关系时，也能够进行精确检测， 从而表现出提高的检测精度和响应性。 电动推进系统控制装置驱动推进螺旋桨旋转，并且被配置为从相对于空速和螺旋桨特性预先存储的数据集估计空速，以及在不同的速度下检测的多个转矩和转速估计值 驾驶条件。
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公开(公告)号：US12015361B2
公开(公告)日：2024-06-18
申请号：US17796682
申请日：2020-03-04
Inventor： Kenji Fujiwara , Hisatoshi Fukumoto , Tomoki Takegami , Tetsuya Kojima , Akihiko Iwata , Masahiro Sugahara , Hiroshi Kobayashi , Mari Nishiyama , Akira Nishizawa
Abstract: 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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Patent Agency Ranking
公开(公告)号：US10023318B2
公开(公告)日：2018-07-17
申请号：US15314848
申请日：2015-06-30
Applicant: Japan Aerospace Exploration Agency
Inventor： Hiroshi Kobayashi , Akira Nishizawa
Abstract: A motorized aircraft is controlled by a drive control means that rotationally drives a propulsion system propeller. The propulsion system propeller is driven by a plurality of electric motors. A comparison detection unit compares estimated propeller torque and estimated motor torque with each other and detects an abnormal state of an electric motor on the basis of the fact that a difference between the propeller torque and a multiple of the motor torque is above a predetermined value.
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公开(公告)号：US20170190435A1
公开(公告)日：2017-07-06
申请号：US15314848
申请日：2015-06-30
Applicant: Japan Aerospace Exploration Agency
Inventor： Hiroshi Kobayashi , Akira Nishizawa
CPC classification number: B64D27/24 , B60L2200/10 , B60L2220/42 , B64D35/08 , H02K7/116 , H02K16/00 , H02K2213/06 , H02P5/46 , H02P29/10 , Y02T50/44 , Y02T50/62
Abstract: A motorized aircraft is controlled by a drive control means (120) that rotationally drives a propulsion system propeller. The propulsion system propeller is driven by a plurality of electric motors (130). Total output of the plurality of electric motors (130) and required output satisfy the following relationship: Pmax(n−1)/n>Preq (where Pmax is the total output (kW) of the electric motors, n is the number of electric motors, and Preq is the required output (kW)).
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6.发明授权公开(公告)号：US10377500B2
公开(公告)日：2019-08-13
申请号：US15129298
申请日：2015-03-12
Applicant: Japan Aerospace Exploration Agency
Inventor： Hiroshi Kobayashi , Akira Nishizawa , Tomoko Iijima , Takeshi Tagashira
IPC: B64D27/24
Abstract: To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.
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7.发明申请公开(公告)号：US20180127104A1
公开(公告)日：2018-05-10
申请号：US15129298
申请日：2015-03-12
Applicant: Japan Aerospace Exploration Agency
Inventor： Hiroshi Kobayashi , Akira Nishizawa , Tomoko Iijima , Takeshi Tagashira
IPC: B64D27/24
CPC classification number: B64D27/24 , B64C2201/021 , Y02T10/7258 , Y02T50/64
Abstract: To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.
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公开(公告)号：US12170496B2
公开(公告)日：2024-12-17
申请号：US17798563
申请日：2020-03-04
Inventor： Kenji Fujiwara , Hisatoshi Fukumoto , Tomoki Takegami , Tetsuya Kojima , Akihiko Iwata , Masahiro Sugahara , Hiroshi Kobayashi , Mari Nishiyama , Akira Nishizawa
Abstract: 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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