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1. 发明授权

US06198991B1 Low-noise level landing apparatus and system for helicopters 失效
标题翻译：用于直升机的低噪声平台着陆装置和系统
公开(公告)号：US06198991B1
公开(公告)日：2001-03-06
申请号：US09250276
申请日：1999-02-16
申请人： Eiichi Yamakawa , Natsuki Kondo , Hiroki Nishimura
发明人： Eiichi Yamakawa , Natsuki Kondo , Hiroki Nishimura
IPC分类号： D05D100
CPC分类号： G08G5/025 , G05D1/0676 , G05D1/0858
摘要： A low-noise level landing apparatus for helicopters comprises a helicopter position calculator for calculating the position of the helicopter, a data input device, an air data sensor for measuring an airspeed and a descending angle, a rotor tachometer for detecting a rotor rotational speed, a memory and a fuel gauge for calculating the weight of the helicopter, a rotor rotational speed controller for controlling the rotor rotational speed, a BVI noise generating area database device for storing noise levels in accordance with parameters of descending speed, airspeed, descending angle, rotor rotational speed and weight of the helicopter. A computer selects a flight route, an airspeed, a descending angle and a rotor rotational speed wherein noise is reduced, by setting a plurality of flight routes on the basis of the helicopter position and landing point and by referring to the noise generating area database device. Low-noise level landing is then carried out by pilot manual control or automatic flight control. By modifying the selected flight route on the basis of ground noise data received by a data receiver, the optimal flight route is reselected. As a result, a flight route wherein noise reduction can be attained during landing can be selected more properly.
摘要翻译：用于直升机的低噪声级着陆装置包括用于计算直升机位置的直升机位置计算器，数据输入装置，用于测量空速和下降角的空气数据传感器，用于检测转子转速的转子转速计，用于计算直升机重量的存储器和燃料计，用于控制转子转速的转子转速控制器，用于根据下降速度，空速，下降角等参数存储噪声水平的BVI噪声产生区域数据库装置，转子转速和直升机的重量。计算机通过基于直升机位置和着陆点设置多个飞行路线并通过参考噪声产生区域数据库设备来选择飞行路线，空速，下降角度和转子旋转速度，其中噪声降低。然后通过飞行员手动控制或自动飞行控制进行低噪声级别着陆。通过根据数据接收机接收到的地面噪声数据修改所选择的飞行路线，重新选择最佳飞行路线。结果，可以更适当地选择在着陆期间可以获得降噪的飞行路线。

2. 发明授权

US5957662A helicopter blade aerofoil 失效
标题翻译：直升机叶片机翼
公开(公告)号：US5957662A
公开(公告)日：1999-09-28
申请号：US945300
申请日：1997-10-17
申请人： Makoto Aoki , Hiroki Nishimura , Eiichi Yamakawa
发明人： Makoto Aoki , Hiroki Nishimura , Eiichi Yamakawa
IPC分类号： B64C27/46 , B64C3/14 , B64C27/467
CPC分类号： B64C27/467 , B64C3/14 , Y10S416/02 , Y10S416/05
摘要： In a helicopter blade aerofoil, upper and lower surfaces thereof are defined by the following coordinates, and the leading edge profile of the aerofoil is defined by the following leading edge radius and center of circle. Thus drag divergence Mach number Mdd and maximum lift coefficient Clmax can be increased and the level of noise can be reduced.______________________________________X/C Yup/C Ylow/C______________________________________0.00000 0.00000 0.000000.00250 0.00781 -0.005580.00500 0.01131 -0.007650.00750 0.01423 -0.008740.01000 0.01660 -0.009640.01750 0.02224 -0.011560.02500 0.02658 -0.012760.50000 0.03585 -0.015680.07500 0.04128 -0.017580.10000 0.04480 -0.019010.15000 0.04893 -0.021130.20000 0.05095 -0.023060.25000 0.05181 -0.024920.30000 0.05200 -0.026470.35000 0.05179 -0.027600.40000 0.05129 -0.028210.45000 0.05038 -0.028270.50000 0.04888 -0.027750.55000 0.04673 -0.026620.60000 0.04393 -0.024910.65000 0.04037 -0.022680.70000 0.03592 -0.019960.75000 0.03052 -0.016820.80000 0.02430 -0.013370.85000 0.01751 -0.009740.90000 0.01046 -0.005970.95000 0.00407 -0.002361.00000 0.00207 -0.00079______________________________________ Leading edge radius r/C = 0.00844, Center of circle X/C = 0.00842, Y/C = 0.00064,
摘要翻译： PCT No.PCT / JP97 / 00674 Sec。 371日期1997年10月17日第 102（e）1997年10月17日PCT 1997年3月5日PCT公布。公开号WO97 / 32780 PCT 日期1997年9月12日在直升机叶片机翼中，其上表面和下表面由以下坐标限定，机翼的前缘轮廓由以下前缘半径和圆心定义。因此，可以增加拖曳发散马赫数Mdd和最大提升系数Clmax，并且可以降低噪声水平。 - X / C Yup / C Ylow / C - 0.00000 0.00000 0.00000 - 0.00250 0.00781 -0.00558 - 0.00500 0.01131 -0.00765 - 0.00750 0.01423 -0.00874 - 0.01000 0.01660 -0.00964 - 0.01750 0.02224 -0.01156 - 0.02500 0.02658 -0.01276 - 0.50000 0.03585 -0.01568 - 0.07500 0.04128 -0.01758 -0.10000 0.04480 -0.01901-0.15000 0.04893 -0.02113 -0.20000 0.05095 -0.02306 -0.25000 0.05181 -0.02492-0.30000 0.05200 -0.02647 -0.35000 0.05179 -0.02760-0.40000 0.05129 -0.02821-0.45000 0.05038 -0.02827-0.50000 0.04888 -0.02775 - 0.55000 0.04673 -0.02662 - 0.60000 0.04393 -0.02491 - 0.65000 0.04037 -0.02268 - 0.70000 0.03592 -0.01996 - 0.75000 0.03052 -0.01682 - 0.80000 0.02430 -0.01337 - 0.85000 0.01751 -0.00974 - 0.90000 0.01046 -0.00597 - 0.95000 0.00407 -0.00236 - 1.00000 0.00207 -0.00079 - 前缘半径r / C = 0.00844， - 圆心X / C = 0.00842，Y / C = 0.00064， -

3. 发明授权

US06164918A Helicopter blade aerofoil 有权
标题翻译：直升机叶片机翼
公开(公告)号：US06164918A
公开(公告)日：2000-12-26
申请号：US176954
申请日：1998-10-22
申请人： Makoto Aoki , Hiroki Nishimura , Eiichi Yamakawa
发明人： Makoto Aoki , Hiroki Nishimura , Eiichi Yamakawa
IPC分类号： B64C27/46 , B64C27/467 , B63H1/26
CPC分类号： B64C27/467 , Y10S416/02
摘要： Upper and lower surfaces of an aerofoil are defined by the following coordinates given in the table below, and the configuration of a leading edge of the aerofoil is defined by the following leading edge radius and the center of circle. Thus drag divergence Mach number Mdd and maximum lift coefficient Clmax can be increased and the noise level can be reduced.______________________________________ X/C Yup/C Ylow/C ______________________________________ 0.00000 -0.00323 -0.00323 0.00100 0.00155 -0.00758 0.00250 0.00418 -0.00925 0.00500 0.00782 -0.01062 0.00750 0.01060 -0.01155 0.01000 0.01312 -0.01213 0.01750 0.01912 -0.01316 0.02500 0.02381 -0.01388 0.05000 0.03437 -0.01561 0.75000 0.04070 -0.01707 0.10000 0.04466 -0.01852 0.15000 0.04893 -0.02100 0.20000 0.05083 -0.02312 0.25000 0.05150 -0.02506 0.30000 0.05149 -0.02663 0.35000 0.05105 -0.02775 0.40000 0.05016 -0.02835 0.45000 0.04875 -0.02839 0.50000 0.04663 -0.02767 0.55000 0.04359 -0.02618 0.60000 0.03974 -0.02407 0.65000 0.03515 -0.02146 0.70000 0.03000 -0.01847 0.75000 0.02451 -0.01523 0.80000 0.01892 -0.01187 0.85000 0.01347 -0.00851 0.90000 0.00836 -0.00529 0.95000 0.00381 -0.00233 1.00000 0.00207 -0.00079 ______________________________________ Leading edge radius r/C=0.01073 Center of circle X/C=0.01072, Y/C=-0.00373
摘要翻译：机翼的上表面和下表面由下表中给出的以下坐标定义，机翼前缘的结构由以下前缘半径和圆心定义。因此，可以增加拖曳发散马赫数Mdd和最大提升系数Clmax，并且可以降低噪声水平。 - X / C Yup / C Ylow / C - 0.00000 -0.00323 -0.00323 - 0.00100 0.00155 -0.00758 - 0.00250 0.00418 -0.00925 - 0.00500 0.00782 -0.01062 - 0.00750 0.01060 -0.01155 - 0.01000 0.01312 -0.01213 - 0.01750 0.01912 -0.01316 - 0.02500 0.02381 - 0.01388 -0.05000 0.03437 -0.01561-0.75000 0.04070 -0.01707 -0.10000 0.04466 -0.01852-0.15000 0.04893 -0.02100 -0.20000 0.05083 -0.02312 -0.25000 0.05150 -0.02506-0.30000 0.05149 -0.02663-0.35000 0.05105 -0.02775-0.40000 0.05016 -0.02835-0.45000 0.04875 - 0.02839-0.50000 0.04663 -0.02767-0.55000 0.04359 -0.02618-0.60000 0.03974 -0.02407-0.65000 0.03515 -0.02146-0.70000 0.03000 -0.01847-0.75000 0.02451 -0.01523-0.80000 0.01892 -0.01187-0.85000 0.01347 -0.00851-0.90000 0.00836 -0.00529-0.95000 0.00381 - 0.00233 - 1.00000 0.00207 -0.00079 - 前缘半径r / C = 0.01073圆心X / C = 0.01072，Y / C = -0.00373

4. 发明授权

US5961290A Helicopter blade aerofoil 失效
标题翻译：直升机叶片机翼
公开(公告)号：US5961290A
公开(公告)日：1999-10-05
申请号：US23699
申请日：1998-02-13
申请人： Makoto Aoki , Hiroki Nishimura , Eiichi Yamakawa
发明人： Makoto Aoki , Hiroki Nishimura , Eiichi Yamakawa
IPC分类号： B64C27/46 , B64C27/467 , B63H1/26
CPC分类号： B64C27/467 , Y10S416/02 , Y10S416/05
摘要： The coordinates defining the upper surface, lower surface, leading edge configuration and center of circle for a helicopter blade airfoil are given to increase maximum lift coefficient and lift-to-drag ratio, and to reduce noise level.
摘要翻译：给出了确定直升机叶片翼面的上表面，下表面，前缘结构和圆心的坐标，以增加最大升力系数和提升阻力比，并降低噪声水平。

5. 发明申请

US20120037336A1 VEHICLE HEAT MANAGEMENT DEVICE 有权
标题翻译：车辆热管理装置
公开(公告)号：US20120037336A1
公开(公告)日：2012-02-16
申请号：US13258252
申请日：2009-05-07
申请人： Masahide Ishikawa , Kaname Uzuki , Atsushi Morita , Keiko Tanaka , Yuki Miyamoto , Satoru Shiga , Masaki Morita , Miyuki Matsuda , Manabu Orihashi , Yoshihiro Saeki , Keiichi Uno , Hiroki Nishimura , Takayuki Kumamoto
发明人： Masahide Ishikawa , Kaname Uzuki , Atsushi Morita , Keiko Tanaka , Yuki Miyamoto , Satoru Shiga , Masaki Morita , Miyuki Matsuda , Manabu Orihashi , Yoshihiro Saeki , Keiichi Uno , Hiroki Nishimura , Takayuki Kumamoto
IPC分类号： F01P9/00
CPC分类号： B60H1/08 , B60H1/00314 , F01P2060/16 , F02B29/0493 , F02M26/33 , F02N19/04 , F16H57/0413 , Y02T10/146 , Y02T10/16 , Y10T477/653
摘要： When there is an extremely low ambient temperature, an electronic control unit controls operation of a circulation path for coolant water in such a manner that, after starting of an engine, the coolant water is supplied from the engine first to a throttle valve and an EGR valve and then to an oil warmer for a transmission. This solves a failure problem in the throttle valve and the EGR valve caused by frost formation at an early stage. As a result, desired operating performance of the vehicle is quickly ensured and heat management in the vehicle is carried out in a desired manner when there is an extremely low ambient temperature.
摘要翻译：当环境温度非常低时，电子控制单元控制冷却水循环路径的操作，使得在发动机启动之后，冷却水从发动机首先供应到节流阀和EGR 阀门，然后到油加热器进行传动。这解决了在早期阶段由于霜冻形成引起的节流阀和EGR阀的故障问题。结果，当环境温度极低时，能够快速确保车辆的期望的操作性能，并且以期望的方式进行车辆的热管理。

6. 发明授权

US08475337B2 Vehicle heat management device 有权
标题翻译：车辆热管理装置
公开(公告)号：US08475337B2
公开(公告)日：2013-07-02
申请号：US13258252
申请日：2009-05-07
申请人： Masahide Ishikawa , Kaname Uzuki , Atsushi Morita , Keiko Tanaka , Yuki Miyamoto , Satoru Shiga , Masaki Morita , Miyuki Matsuda , Manabu Orihashi , Yoshihiro Saeki , Keiichi Uno , Hiroki Nishimura , Takayuki Kumamoto
发明人： Masahide Ishikawa , Kaname Uzuki , Atsushi Morita , Keiko Tanaka , Yuki Miyamoto , Satoru Shiga , Masaki Morita , Miyuki Matsuda , Manabu Orihashi , Yoshihiro Saeki , Keiichi Uno , Hiroki Nishimura , Takayuki Kumamoto
IPC分类号： F16H59/00
CPC分类号： B60H1/08 , B60H1/00314 , F01P2060/16 , F02B29/0493 , F02M26/33 , F02N19/04 , F16H57/0413 , Y02T10/146 , Y02T10/16 , Y10T477/653
摘要： When there is an extremely low ambient temperature, an electronic control unit controls operation of a circulation path for coolant water in such a manner that, after starting of an engine, the coolant water is supplied from the engine first to a throttle valve and an EGR valve and then to an oil warmer for a transmission. This solves a failure problem in the throttle valve and the EGR valve caused by frost formation at an early stage. As a result, desired operating performance of the vehicle is quickly ensured and heat management in the vehicle is carried out in a desired manner when there is an extremely low ambient temperature.
摘要翻译：当环境温度非常低时，电子控制单元控制冷却水循环路径的操作，使得在发动机启动之后，冷却水从发动机首先供应到节流阀和EGR 阀门，然后到油加热器进行传动。这解决了在早期阶段由于霜冻形成引起的节流阀和EGR阀的故障问题。结果，当环境温度极低时，能够快速确保车辆的期望的操作性能，并且以期望的方式进行车辆的热管理。

7. 发明授权

US6101431A Flight system and system for forming virtual images for aircraft 有权
标题翻译：用于形成飞机虚拟图像的飞行系统和系统
公开(公告)号：US6101431A
公开(公告)日：2000-08-08
申请号：US137748
申请日：1998-08-21
申请人： Yoshiyuki Niwa , Shunichi Bandoh , Ryutaro Yabe , Hiroki Nishimura , Mikio Terashima , Sumio Sako
发明人： Yoshiyuki Niwa , Shunichi Bandoh , Ryutaro Yabe , Hiroki Nishimura , Mikio Terashima , Sumio Sako
IPC分类号： G01C21/20 , B64D45/00 , G01C11/00 , G01C23/00 , G01S5/00 , G01S5/14 , G01S7/51 , G01S17/89 , G01S17/93 , G08G5/02 , G01C21/00
CPC分类号： G08G5/0086 , G01C11/00 , G01S17/89 , G01S17/933 , G01S5/0072 , G01S7/51 , G08G5/0021 , G01S19/51
摘要： A three-dimensional digital map prepared by an satellite or the like is stored in a first memory as a wide-area information. Narrow-area information obtained by a laser radar is stored in a second memory. Obstacle information on obstacles, such as high-voltage power lines, high buildings and cranes, is stored in a third memory. These three information are read out to generate virtual images on a see-through type display mounted on a helmet of a pilot so that the virtual images is superimposed on the actual field of vision.
摘要翻译：由卫星等制作的三维数字地图作为广域信息存储在第一存储器中。通过激光雷达获得的窄区域信息被存储在第二存储器中。诸如高压电力线，高层建筑物和起重机等障碍物的障碍物信息被存储在第三存储器中。这三个信息被读出以在安装在飞行员头盔上的透视型显示器上产生虚拟图像，使得虚拟图像叠加在实际的视野上。

8. 发明授权

US5940280A Converter circuit of battery charger for electric vehicle 失效
标题翻译：电动汽车充电器转换电路
公开(公告)号：US5940280A
公开(公告)日：1999-08-17
申请号：US56726
申请日：1998-04-08
申请人： Yasumasa Murai , Hiroki Nishimura , Katsunori Sugimori
发明人： Yasumasa Murai , Hiroki Nishimura , Katsunori Sugimori
IPC分类号： H02J7/00 , H02J7/02 , H02M1/42 , H02M3/335 , H02M3/337 , H02M5/00 , H02M7/12 , H02M7/21
CPC分类号： H02M1/4208 , H02J7/022 , H02M3/337 , Y02B40/90 , Y02B70/126 , Y02T90/127
摘要： A battery charger converter circuit is disclosed in which a half-bridge rectifier circuit formed from two diodes, a half-bridge circuit formed from two switching elements, and a series circuit formed from two capacitors are connected at either end, respectively, thereof in parallel to each other, a boosting reactor being provided at the AC side of the half-bridge rectifier circuit; a primary circuit of the converter, including a primary coil of a high-frequency transformer, connected between a common point of connection between the switching elements and a common point of connection between the two capacitors, and a control circuit for the two switching elements; and a secondary circuit of the converter, including the secondary coil of the high-frequency transformer, a full-bridge rectifier circuit connected in parallel to the secondary coil and a smoothing capacitor; a high-frequency power generated by the primary circuit of the converter being rectified by the secondary circuit and charged into cells.
摘要翻译：公开了一种电池充电器转换器电路，其中由两个二极管形成的半桥整流电路，由两个开关元件形成的半桥电路和由两个电容器形成的串联电路分别在其两端分别连接在半桥式整流电路的AC侧设置有升压电抗器，所述转换器的初级电路包括连接在所述开关元件之间的公共连接点与所述两个电容器之间的公共连接点之间的高频变压器的初级线圈，以及用于所述两个开关元件的控制电路; 以及包括高频变压器的次级线圈的转换器的次级电路，与次级线圈并联连接的全桥整流电路和平滑电容器; 由转换器的主电路产生的高频功率由次级电路整流并被充电到电池中。

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