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1. 发明专利

JP2013099175A Electric actuator, electric actuator motive power cut-off method, and electric actuator motive power cut-off device 有权
标题翻译：电动执行器，电动执行器动力切断方法和电动执行器动力切断装置
公开(公告)号：JP2013099175A
公开(公告)日：2013-05-20
申请号：JP2011241648
申请日：2011-11-02
申请人： Nabtesco Corp , ナブテスコ株式会社
发明人： SHIGETOMO RYOTA , SHIRAI YASUYUKI
IPC分类号： H02K7/06 , F16D3/06 , F16H25/20 , F16H25/22
CPC分类号： H02K7/06 , F16D7/10 , F16D28/00 , F16D43/208 , F16D2023/123 , H02K7/003 , H02K7/108 , H02K7/112 , H02K2213/06
摘要： PROBLEM TO BE SOLVED: To provide an electric actuator capable of transferring an operation of a drive target apparatus to an allowable state at an occurrence of a fixed state, and further simplifying the mechanism and downsizing the structure.SOLUTION: A motive power cut-off mechanism 24 is provided to include a case part 37, an inner shaft part 38, a supporting part 39, and a coupling member 40. The case part 37 is fixed to an electric motor 21. The inner shaft part 38 inside the case part 37 is fixed to a screw part 30. The supporting part 39 is installed to support a load parallel in an axial direction between the case part 37 and the inner shaft part 38, engaged with the inner shaft part 38, and slidable to the case part 37 at an axial direction groove and a circumferential direction groove. When a torque equal to or more than a predetermined level acts, the coupling member 40 disconnects the coupling between the case part 37 and the inner shaft part 38 to cut off transmission of motive power.
摘要翻译：要解决的问题：提供一种能够在固定状态发生时将驱动目标装置的操作传送到允许状态的电动致动器，并且进一步简化机构并且缩小结构。解决方案：动力切断机构24设置为包括壳体部分37，内轴部分38，支撑部分39和联接部件40.壳体部分37固定到电动机21 壳体部37内的内轴部38被固定在螺纹部30上。支撑部39被安装成支撑在壳体部37与内轴部38之间沿轴向平行的负载，轴部38，并且在轴向槽和圆周方向槽处可滑动到壳体部37。当等于或大于预定水平的扭矩作用时，联接构件40断开壳体部分37和内轴部分38之间的联接，以切断动力传递。版权所有（C）2013，JPO＆INPIT

2. 发明专利

JP2015028387A 航空機アクチュエータの油圧システム有权
标题翻译：飞机执行器液压系统
公开(公告)号：JP2015028387A
公开(公告)日：2015-02-12
申请号：JP2014203580
申请日：2014-10-02
申请人：ナブテスコ株式会社 , Nabtesco Corp
发明人： FUKUI ATSUSHI , SHIRAI YASUYUKI
IPC分类号： F15B20/00 , B64C13/42 , F15B11/00
摘要：【課題】機体側油圧源の機能の喪失時又は低下時であってもアクチュエータを駆動可能であるとともに、システム全体の温度上昇と使用される油の温度上昇とを抑制することができる、航空機アクチュエータの油圧システムを提供する。【解決手段】電動モータ19は、機体側油圧源104の機能の喪失又は低下時にアクチュエータ14に圧油を供給可能な可変容量式のバックアップ用油圧ポンプ18を駆動する。電源ユニット20は、可変周波数電源から供給される電力を整流する。ドライバ21は、電源ユニット20からの電力を供給し、上記ポンプ18を所定の一定回転速度で回転させるように電動モータ19を駆動する。上記ポンプ18、電動モータ19、及びドライバ21における上記ポンプ18の回転速度に対するそれぞれの効率の変化に基づいて、それらの効率の積としての総合効率が最大値となるように、一定回転速度が設定される。【選択図】図2
摘要翻译：要解决的问题：提供一种即使当机体侧液压源的功能丧失或降低时也能驱动执行器的飞行器致动器的液压系统，并且可以抑制整个系统的温度上升和上升使用中的油的温度。解决方案：当机体侧液压源104的功能丧失或降低时，电动机19驱动能够向致动器14供应加压油的可变容量型备用液压泵18。动力单元20对从变频电源供给的电力进行整流。向驱动器21提供来自动力单元20的电力以驱动电动机19，使得泵18以预定的恒定转速旋转。基于泵18，电动机19和驱动器21的效率随着泵18的转速的变化而变化，恒定的转速被设定为其效率的乘积的总效率达到最大值。

3. 发明专利

JP2011247334A Hydraulic system for aircraft actuator 审中-公开
标题翻译：用于航空器执行器的液压系统
公开(公告)号：JP2011247334A
公开(公告)日：2011-12-08
申请号：JP2010120328
申请日：2010-05-26
申请人： Nabtesco Corp , ナブテスコ株式会社
发明人： FUKUI ATSUSHI , SHIRAI YASUYUKI
IPC分类号： F15B20/00 , B64C13/42 , F15B11/00
CPC分类号： F04B49/06 , B64C13/40 , F15B18/00 , F15B20/004 , F15B2211/20515 , F15B2211/20546 , F15B2211/7054 , F15B2211/8633 , F15B2211/8636 , F15B2211/864 , F15B2211/8757 , Y02T50/44 , Y10T137/85986
摘要： PROBLEM TO BE SOLVED: To provide a hydraulic system for an aircraft actuator which drives an actuator even when a loss or reduction in the function of an aircraft hydraulic power source occurs, and which suppresses an increase in the overall temperature of the system and in the temperature of an oil used.SOLUTION: The hydraulic system includes: an electric motor 19, which drives a variable capacity backup hydraulic pump 18 that can supply pressure oil to an actuator 14 when a loss or reduction occurs in the function of an aircraft central hydraulic power source 104; a power source unit 20 which rectifies electric power supplied from a variable frequency supply 108; and a driver 21 which supplies the electric power from the power source unit 20 and drives the electric motor 19 so as to rotate the pump 18 at a predetermined constant rotational speed. The constant rotational speed is set, based on the change in the efficiency of each of the pump 18, the electric motor 19, and the driver 21 with respect to the rotational speed of the pump so as to maximize the overall efficiency obtained as a product of these efficiencies.
摘要翻译：要解决的问题：提供一种用于飞机致动器的液压系统，其即使在发生飞行器液压动力源的功能的损失或降低时也驱动致动器，并且抑制了系统的总体温度的升高并在所用的油温度下。解决方案：液压系统包括：电动机19，其驱动可变容量备用液压泵18，当在飞行器中央液压动力源104的功能中发生损失或减少时，该可变容量备用液压泵18可向致动器14供应压力油 ; 电源单元20，其对从可变频率电源108提供的电力进行整流; 以及驱动器21，其从电源单元20提供电力并驱动电动机19，以使泵18以预定的恒定转速旋转。基于泵18，电动马达19和驱动器21的效率相对于泵的转速的变化来设定恒定转速，以便最大化作为产品获得的整体效率的这些效率。版权所有（C）2012，JPO＆INPIT

4. 发明专利

JP2012247125A Electric actuator for mounting in missile 有权
标题翻译：电动执行器安装在MISSILE
公开(公告)号：JP2012247125A
公开(公告)日：2012-12-13
申请号：JP2011119001
申请日：2011-05-27
申请人： Nabtesco Corp , ナブテスコ株式会社
发明人： SHIRAI YASUYUKI
IPC分类号： F42B10/64 , H02K33/16
摘要： PROBLEM TO BE SOLVED: To provide an electric actuator for mounting in a missile, able to reduce the number of components thereof, simplify the structure thereof, secure high output thereof and reduce the size thereof.SOLUTION: A plate-shaped magnet 11 is provided as an oscillation member and is supported in a cantilever manner oscillatably relative to a body side of the missile 100. A stator 12 includes: an iron core 25 installed around the magnet 11; and a coil 26 wound around the iron core 25. The plate-shaped magnet 11 has a pair of flat end faces (11a, 11b) extending parallel to each other. One end face 11a forms a north pole, and the another end face 11b forms a south pole. The coil 26 is installed to face at least either one or the another end face (11a, 11b) of the magnet 11.
摘要翻译：要解决的问题：为了提供一种用于安装在导弹中的电致动器，能够减少其部件数量，简化其结构，确保其高输出并减小其尺寸。解决方案：板状磁体11设置为振动件，并以相对于导弹100的主体侧摆动的悬臂方式支撑。定子12包括：安装在磁体11周围的铁芯25; 以及卷绕在铁芯25周围的线圈26.板状磁体11具有彼此平行延伸的一对平坦端面11a，11b。一个端面11a形成北极，另一端面11b形成南极。线圈26被安装成面对磁体11的至少一个或另一个端面（11a，11b）。版权所有（C）2013，JPO＆INPIT

5. 发明专利

JP2010172075A Electric actuator 有权
标题翻译：电动执行器
公开(公告)号：JP2010172075A
公开(公告)日：2010-08-05
申请号：JP2009010552
申请日：2009-01-21
申请人： Nabtesco Corp , ナブテスコ株式会社
发明人： HIRAI MIKIAKI , SHIRAI YASUYUKI , NOMURA TSUNETOSHI , ITO KOJI
IPC分类号： H02K7/06 , B64C25/24 , F16H25/20 , F16H25/24
CPC分类号： H02K7/06 , B64C25/24 , F16H25/2015 , F16H25/2454 , F16H2025/2075 , H02K7/10 , Y10T74/18168 , Y10T74/18656
摘要： PROBLEM TO BE SOLVED: To provide an electric actuator with a piston rod to be driven by an electric motor through a screw shaft, wherein its structure reduces an external force or impact acting on the screw shaft when the piston rod is at a stretched position. SOLUTION: The electric actuator 1 includes a cylinder body 2, the screw shaft 3 placed in the cylinder body 2 and rotatably driven by an electric motor 23, a nut 5 screwed onto the screw shaft 3, the piston rod 4 that is caused to make linear motion through the nut 5 by the rotation of the screw shaft 3; recesses 6 formed on the outer circumferential surface of the nut 5, keys 7 each provided to a recess 6, holes 8 formed on the outer circumference of the piston portion 4a of the piston rod 4, into which the keys 7 are fit, and a tapered portion 9 formed on an inner wall of the cylinder body 2, into which the keys 7 are fit. When the piston rod 4 is caused to advance, the keys 7 are moved outward and fit into the tapered portion 9 and the backward movement of the piston rod 4 is arrested by the keys 7. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：为了提供具有由电动机通过螺杆轴驱动的活塞杆的电致动器，其中当活塞杆处于一个位置时，其结构减小了作用在螺杆轴上的外力或冲击力拉伸位置解决方案：电动执行器1包括缸体2，螺杆轴3放置在缸体2中并由电动机23旋转驱动，螺母5螺纹连接到螺杆轴3上，活塞杆4是通过螺杆轴3的旋转使螺母5线性运动; 形成在螺母5的外周面上的凹部6，各自设置在凹部6上的键7，形成在活塞杆4的活塞部4a的外周上形成有孔7，孔7配合在其中，孔8 形成在缸体2的内壁上的锥形部分9，键7配合到其中。当活塞杆4前进时，钥匙7向外移动并配合到锥形部分9中，并且活塞杆4的向后运动被钥匙7锁定。（C）2010，JPO＆INPIT

6. 发明专利

JP2012152062A Three-phase dc motor 有权
标题翻译：三相直流电动机
公开(公告)号：JP2012152062A
公开(公告)日：2012-08-09
申请号：JP2011010036
申请日：2011-01-20
申请人： Nabtesco Corp , ナブテスコ株式会社
发明人： SHIRAI YASUYUKI
IPC分类号： H02K21/14 , H02K1/16
CPC分类号： H02K1/165 , H02K7/06 , H02K21/14
摘要： PROBLEM TO BE SOLVED: To provide a three-phase DC motor that eliminates the need for combination of torque and contributes to a reduction in wing thickness.SOLUTION: A three-phase DC motor includes: a rotor 30 that has magnetic poles 30a; a stator 28 that is arranged on an outer side of the rotor 30 and includes a plurality of cores 32b with inner circumferential surfaces thereof facing an outer circumferential surface of the rotor 30; and three or more coils that are wound around the cores 32b. On outer sides thereof, the magnetic poles 30a have respective N-poles and S-poles arranged alternatingly in a circumferential direction of the rotor 30. With reference to a first imaginary plane P1 that passes through a shaft center O of the rotor 30, coils 35a, 35b, 35c, and 35d are arranged only in a range from the first imaginary plane P1 to second imaginary planes P2 that are rotated at predetermined angles, in a rotor rotational direction and in the opposite direction, from the first imaginary plane P1. The inner circumferential surfaces of 3N (N=1, 2, 3, ...) cores 32b that are adjacent to one another out of the plurality of cores 32b are arranged so as to fit into width of one pole on the outer sides of the magnetic poles 30a.
摘要翻译：要解决的问题：提供一种三相直流电动机，其不需要组合扭矩并且有助于减小机翼厚度。解决方案：三相直流电动机包括：具有磁极30a的转子30; 定子28，其设置在转子30的外侧，并且具有多个芯32b，其内周面面对转子30的外周面; 以及缠绕在芯32b周围的三个或更多个线圈。在其外侧，磁极30a具有在转子30的圆周方向上交替布置的各自的N极和S极。参考通过转子30的轴心O的第一假想平面P1，线圈 35a，35b，35c和35d仅在从第一假想平面P1到第二假想平面P2的范围内，其从第一假想平面P1以转子旋转方向和相反方向以预定角度旋转。在多个芯32b中彼此相邻的3N（N = 1,2,3，...）芯32b的内圆周表面被布置成适合于在多个芯32b的外侧的一个极的宽度磁极30a。版权所有（C）2012，JPO＆INPIT

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