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1. 发明授权

US09868515B2 Aircraft electric actuator drive apparatus 有权
公开(公告)号：US09868515B2
公开(公告)日：2018-01-16
申请号：US14470194
申请日：2014-08-27
申请人： NABTESCO CORPORATION , IHI AEROSPACE CO., LTD.
发明人： Shingo Nakagawa , Yoichi Yamamoto , Hitoshi Oyori
IPC分类号： B64C13/50 , B64D41/00
CPC分类号： B64C13/50 , B64D41/00 , Y02T50/44
摘要： An aircraft electric actuator drive apparatus has an electric actuator and a secondary power supply device. The electric actuator is driven using electric power from a main power unit provided in an aircraft. The secondary power supply device can temporarily supply electric power to the electric actuator while electric power from the main power unit is applied to the electric actuator.

2. 发明授权

US09819179B2 Aircraft electric power system 有权
公开(公告)号：US09819179B2
公开(公告)日：2017-11-14
申请号：US14470219
申请日：2014-08-27
申请人： NABTESCO CORPORATION , IHI AEROSPACE CO., LTD.
发明人： Shingo Nakagawa , Yoichi Yamamoto , Hitoshi Oyori
IPC分类号： B60L1/00 , H02J1/08 , H02J1/10 , H02J1/12 , H02J4/00 , H02J7/34 , H02J1/00
CPC分类号： H02J1/08 , H02J1/102 , H02J1/12 , H02J4/00 , H02J7/34 , H02J2001/004 , H02J2001/008
摘要： An aircraft electric power system provided in an aircraft includes a predetermined DC power supply bus for supplying electric power to a load. The DC power supply bus is configured to always be connected to two or more types of power supply devices having different forms.

3. 发明授权

US09318983B2 Motor controller 有权
标题翻译：电机控制器
公开(公告)号：US09318983B2
公开(公告)日：2016-04-19
申请号：US14560406
申请日：2014-12-04
申请人： SINFONIA TECHNOLOGY CO., LTD. , IHI AEROSPACE CO., LTD.
发明人： Yoshito Ohta , Keisuke Onishi , Hitoshi Oyori
IPC分类号： H02P6/00 , H02P29/02 , H02P21/00
CPC分类号： H02P6/002 , H02P6/28 , H02P21/22 , H02P29/0243
摘要： A 0-axis current calculator 7 configured to calculate a target value of the 0-axis current by setting the current of the open phase to be zero when one of the phases becomes open, or determines that the target value of the 0-axis current is zero when there is no open phase is provided. Based on the target values of the d-axis current and the q-axis current, the target value of the 0-axis current calculated by the 0-axis current calculator 7, and the d-axis current, the q-axis current, and the 0-axis current transformed by the d-q-0 transformer 8, the current supplied to each phase of the motor are controlled.
摘要翻译： 0轴电流计算器7，被配置为当其中一个相位变为断开时，通过将开路相位的电流设置为零来计算0轴电流的目标值，或者确定0轴电流的目标值当没有提供开放相位时为零。基于d轴电流和q轴电流的目标值，由0轴电流计算器7计算的0轴电流的目标值和d轴电流，q轴电流，和由dq-0变压器8变换的0轴电流，控制提供给电动机各相的电流。

4. 发明申请

US20140139152A1 ELECTRIC ACTUATOR DRIVE DEVICE AND ACTUATOR USING SAME 审中-公开
标题翻译：电动执行器驱动装置和执行器使用相同
公开(公告)号：US20140139152A1
公开(公告)日：2014-05-22
申请号：US14122127
申请日：2012-04-05
申请人： IHI AEROSPACE CO. LTD.
发明人： Hitoshi Oyori , Masaya Wakita , Yukio Shimomura
IPC分类号： H02P3/14
CPC分类号： H02P3/14 , B64G1/40 , B64G1/66 , H02P3/18 , H02P27/06 , H02P29/0241
摘要： To bring an actuator driving motor having a malfunction such as failure to a stop in a shorter time without employing a mechanical braking system. The present invention is an electric actuator driver, including: a power supply; an actuator driving motor (11A, 11B) to be supplied with power from the power supply to drive an actuator (B1); a motor braking circuit (C) to apply a regenerative brake on the actuator driving motor (11A, 11B); a malfunction occurrence determining means (D1) to determine whether there is a malfunction in a necessary component; and a regenerative braking means (D3) to apply the regenerative brake on the actuator driving motor (11A, 11B) by means of the motor braking circuit (C).
摘要翻译：在不使用机械制动系统的情况下，使具有故障的致动器驱动电动机在较短时间内发生故障。本发明是一种电动执行器驱动器，包括：电源; 致动器驱动电动机（11A，11B），从电源供给动力以驱动致动器（B1）; 在所述致动器驱动电动机（11A，11B）上施加再生制动的电动机制动回路（C）; 故障发生确定装置（D1），用于确定是否存在必要部件中的故障; 以及通过马达制动电路（C）将再生制动施加在致动器驱动马达（11A，11B）上的再生制动装置（D3）。

5. 发明申请

US20130287594A1 FLUID SUPPLY DEVICE 审中-公开
标题翻译：流体供应装置
公开(公告)号：US20130287594A1
公开(公告)日：2013-10-31
申请号：US13870898
申请日：2013-04-25
申请人： IHI AEROSPACE CO., LTD.
发明人： Hitoshi Oyori , Noriko Morioka
IPC分类号： F04B49/06
CPC分类号： F02D41/3082 , F02D41/3845 , F02M37/00 , F02M37/18 , F04B49/06 , F04B49/20 , F04B2205/09 , F04B2207/041 , F04C14/02 , F04C14/08
摘要： A fuel supply device according to the present invention comprises a first fuel pump for forcing fuel from a fuel tank to a fuel passage, a first electric motor for driving the first fuel pump, a second fuel pump for forcing fuel from the fuel tank to the fuel passage, a second electric motor for driving the second fuel pump, a supply flow rate sensor for detecting flow rate in the supply passage, and a control device for controlling the flow rate in the supply passage to follow a desired value thereof, by regulating rotational speeds of the first and second electric motors depending on a difference between the desired value and a detected value of flow rate in the supply passage.
摘要翻译：根据本发明的燃料供应装置包括用于将燃料从燃料箱施加到燃料通道的第一燃料泵，用于驱动第一燃料泵的第一电动机，用于将来自燃料箱的燃料迫使到第二燃料泵的第二燃料泵燃料通道，用于驱动第二燃料泵的第二电动机，用于检测供给通道中的流量的供给流量传感器，以及用于通过调节来控制供给通道中的流量以追随其期望值的控制装置第一和第二电动机的转速取决于期望值与供给通道中的流量的检测值之间的差异。

6. 发明授权

US10280866B2 Fluid supply device 有权
公开(公告)号：US10280866B2
公开(公告)日：2019-05-07
申请号：US15487321
申请日：2017-04-13
申请人： IHI AEROSPACE CO., LTD.
发明人： Hitoshi Oyori , Noriko Morioka
IPC分类号： F04C14/02 , F04C14/08 , F04B49/20 , F04B49/06 , F02M37/18 , F02D41/38 , F02D41/30 , F02M37/00
摘要： A fuel supply device according to the present invention comprises a first fuel pump for forcing fuel from a fuel tank to a fuel passage, a first electric motor for driving the first fuel pump, a second fuel pump for forcing fuel from the fuel tank to the fuel passage, a second electric motor for driving the second fuel pump, a supply flow rate sensor for detecting flow rate in the supply passage, and a control device for controlling the flow rate in the supply passage to follow a desired value thereof, by regulating rotational speeds of the first and second electric motors depending on a difference between the desired value and a detected value of flow rate in the supply passage.

7. 发明申请

US20170218875A1 FLUID SUPPLY DEVICE 审中-公开
公开(公告)号：US20170218875A1
公开(公告)日：2017-08-03
申请号：US15487321
申请日：2017-04-13
申请人： IHI AEROSPACE CO., LTD.
发明人： Hitoshi Oyori , Noriko Morioka
IPC分类号： F02D41/30 , F02M37/18
CPC分类号： F02D41/3082 , F02D41/3845 , F02M37/00 , F02M37/18 , F04B49/06
摘要： A fuel supply device according to the present invention comprises a first fuel pump for forcing fuel from a fuel tank to a fuel passage, a first electric motor for driving the first fuel pump, a second fuel pump for forcing fuel from the fuel tank to the fuel passage, a second electric motor for driving the second fuel pump, a supply flow rate sensor for detecting flow rate in the supply passage, and a control device for controlling the flow rate in the supply passage to follow a desired value thereof, by regulating rotational speeds of the first and second electric motors depending on a difference between the desired value and a detected value of flow rate in the supply passage.

8. 发明申请

US20150274285A1 WHEEL DRIVE SYSTEM FOR AIRCRAFT 有权
标题翻译：用于飞机的车轮驱动系统
公开(公告)号：US20150274285A1
公开(公告)日：2015-10-01
申请号：US14673315
申请日：2015-03-30
申请人： SINFONIA TECHNOLOGY CO., LTD. , IHI AEROSPACE CO., LTD. , SUMITOMO PRECISION PRODUCTS CO., LTD.
发明人： Hiroshi Saito , Nobuyuki Nakanishi , Hitoshi Oyori , Masayuki Takada
IPC分类号： B64C25/40 , B64C25/34
CPC分类号： B64C25/405 , B64C25/34 , B64C25/40 , Y02T50/823
摘要： Provided is a wheel drive system for aircraft RS including a motor 2 that is connected to a wheel 12, and provided with two voltage supply lines L1 and L2 for supplying the voltages Vta and Vpr with varying the length of a winding 21 to be energized; a voltage supply unit for supplying the voltage Vta and Vpr to the two voltage supply lines L1 and L2; and a control unit 8 for controlling the voltage supply unit, wherein the control unit 8 is configured to select one of the two voltage supply lines L1 and L2, and supply the voltage Vta or Vpr, by controlling the voltage supply unit.
摘要翻译：提供一种用于航空器RS的轮驱动系统，其包括连接到车轮12的马达2，并且设置有用于提供电压Vta和Vpr的两个电压供应线L1和L2，以改变要被激励的绕组21的长度; 用于将电压Vta和Vpr提供给两个电压供应线L1和L2的电压供应单元; 以及用于控制电压供应单元的控制单元8，其中控制单元8被配置为通过控制电压供应单元来选择两个电压供应线L1和L2中的一个，并且提供电压Vta或Vpr。

9. 发明授权

US09369068B2 Control device for drive device 有权
标题翻译：驱动装置控制装置
公开(公告)号：US09369068B2
公开(公告)日：2016-06-14
申请号：US14550433
申请日：2014-11-21
申请人： IHI AEROSPACE CO., LTD. , SINFONIA TECHNOLOGY CO., LTD.
发明人： Hitoshi Oyori , Yoshito Ohta , Keisuke Onishi
IPC分类号： H02P5/00 , G05B11/38 , G05B11/36
CPC分类号： H02P5/00 , G05B11/32 , G05B11/36 , G05B11/38 , G05B2219/40208 , G05B2219/42317
摘要： Multipliers 21a and 21b output values, which are obtained by multiplying a total drive command value Es by first and second gains G1 and G2, respectively, as first and second drive command values E1 and E2. Controllers 23a and 23b control first and second actuators (motors) 5 and 7, respectively, on the basis of the first and second drive command values. The detection values of the drive amounts of the actuators are denoted by Ef1 and Ef2, respectively, and the detection value of the drive amount of a driven body is denoted by Ef. A gain calculator 27 calculates the gains G1 and G2 on the basis of Ef1, Ef and Ef2. An upper limit value of Ef, which denotes the drive amount of the driven body, is denoted by Lmax. When Ef1, Ef2 or Ef approaches zero, the first gain G1 is brought close to (Ef1−Lmax/2)/(Ef−Lmax).
摘要翻译：乘法器21a和21b的输出值分别通过将总驱动指令值Es乘以第一和第二增益G1和G2作为第一和第二驱动指令值E1和E2获得。控制器23a和23b分别基于第一和第二驱动指令值来控制第一和第二致动器（马达）5和7。致动器的驱动量的检测值分别由Ef1和Ef2表示，驱动体的驱动量的检测值用Ef表示。增益计算器27基于Ef1，Ef和Ef2来计算增益G1和G2。表示被驱动体的驱动量的Ef的上限值由Lmax表示。当Ef1，Ef2或Ef接近零时，第一增益G1接近（Ef1-Lmax / 2）/（Ef-Lmax）。

10. 发明申请

US20150100180A1 ELECTRICITY GENERATION SYSTEM 有权
标题翻译：电力发电系统
公开(公告)号：US20150100180A1
公开(公告)日：2015-04-09
申请号：US13870935
申请日：2013-04-25
申请人： IHI AEROSPACE CO., LTD.
发明人： Hitoshi Oyori , Noriko Morioka
IPC分类号： B64D41/00 , B60R16/03
CPC分类号： B64D41/00 , B60R16/03 , F01D15/10 , F02C3/113 , F02C7/36 , F05D2220/76 , F05D2270/101
摘要： An electricity generation system according to the present invention comprises a first electric generator designed to generate electricity by rotation of a high-pressure shaft of a compressor constituting a jet engine, a second electric generator designed to generate electricity by rotation of a low-pressure shaft of the compressor, a power distributor for distributing power generated by the first and second electric generators among a multiple loads, a first power regulation device for regulating power output of the first electric generator, a second power regulation device for regulating power output of the second electric generator, and a power control device which manipulates the first and second power regulation devices to ensure a specified amount or greater of jet engine surge margin.
摘要翻译：根据本发明的发电系统包括设计成通过构成喷气发动机的压缩机的高压轴的旋转而发电的第一发电机，设计成通过低压轴的旋转发电的第二发电机的分配器，用于在多个负载中分配由第一和第二发电机产生的电力的功率分配器，用于调节第一发电机的功率输出的第一功率调节装置，用于调节第二发电机的功率输出的第二功率调节装置发电机和操作第一和第二功率调节装置的功率控制装置，以确保喷射发动机喘振裕度的规定量以上。

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