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1. 发明授权

US06312358B1 Constant speed drive apparatus for aircraft generator and traction speed change apparatus 有权
标题翻译：用于飞机发电机和牵引变速装置的恒速驱动装置
公开(公告)号：US06312358B1
公开(公告)日：2001-11-06
申请号：US09583167
申请日：2000-05-30
申请人： Tatsuhiko Goi , Kouji Kawakami , Eiichi Yamakawa
发明人： Tatsuhiko Goi , Kouji Kawakami , Eiichi Yamakawa
IPC分类号： B60K4114
CPC分类号： F16H15/38 , F16H61/664 , Y10T477/619
摘要： A constant speed drive apparatus for an aircraft generator comprises an input shaft for receiving drive torque from an aircraft engine, a traction speed change mechanism of continuously-variable speed change ratio which is coupled to the input shaft, an output shaft for supplying the aircraft generator with drive torque which is changed in speed by the traction speed change mechanism, and a control computer for controlling the speed change ratio of the traction speed change mechanism to maintain the output shaft at a predetermined rotational frequency. With such constitution it is possible to achieve a small and lightweight constant speed drive apparatus having a high transmission efficiency.
摘要翻译：一种用于飞机发电机的恒速驱动装置，包括用于接收来自飞机发动机的驱动扭矩的输入轴，耦合到输入轴的连续变速变速比的牵引变速机构，用于供应飞机发电机的输出轴具有通过牵引变速机构而改变速度的驱动转矩，以及用于控制牵引变速机构的变速比以将输出轴保持在预定转速的控制计算机。利用这种结构，可以实现具有高传动效率的小而轻的恒速驱动装置。

2. 发明授权

US06273681B1 Rotor blade flap driving apparatus 有权
标题翻译：转子叶片挡板驱动装置
公开(公告)号：US06273681B1
公开(公告)日：2001-08-14
申请号：US09517722
申请日：2000-03-02
申请人： Eiichi Yamakawa , Tatsuro Hongu
发明人： Eiichi Yamakawa , Tatsuro Hongu
IPC分类号： B64C27615
CPC分类号： B64C27/001 , B64C27/615 , B64C2027/7283 , B64C2027/7294 , Y02T50/34 , Y10T74/18992
摘要： An actuator and first to fourth links constitute a first displacement magnifying mechanism. An input shaft which is fixed in a basal end of the first and second links, a support shaft which is fixed in a basal end of the third and fourth links, and a displacement magnifying lever constitute a second displacement magnifying mechanism. In the displacement magnifying lever, an intermediate portion is angularly displaceably coupled to a tip end of the support shaft, a tip end of the input shaft is angularly displaceably coupled to one end, and an output rod is angularly displaceably coupled to another end. The expansion and contraction of the actuator are magnified by the first and second displacement magnifying mechanisms so as to drive a flap angularly via output rod. According to this configuration, the displacement of the actuator can be largely magnified so that the flap can be sufficiently angularly displaced in the vertical direction and in a reciprocal manner.
摘要翻译：致动器和第一至第四连杆构成第一位移放大机构。固定在第一和第二连杆的基端的输入轴，固定在第三和第四连杆的基端的支撑轴和位移放大杆构成第二位移放大机构。在位移放大杆中，中间部分以可角度方式可移动地联接到支撑轴的末端，输入轴的顶端可角度地可移动地联接到一端，并且输出杆成角度地可移动地联接到另一端。致动器的膨胀和收缩由第一和第二位移放大机构放大，以通过输出杆角度地驱动翼片。根据该结构，致动器的位移可以大幅度地放大，使得翼片能够在垂直方向和倒数方向上被充分地角度位移。

3. 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， -

4. 发明授权

US5782433A Engine deceleration device and power transmission device for helicopters 失效
标题翻译：直升机发动机减速装置和动力传动装置
公开(公告)号：US5782433A
公开(公告)日：1998-07-21
申请号：US615786
申请日：1996-03-12
申请人： Tatsuhiko Goi , Nobuyoshi Yamauchi , Eiichi Yamakawa
发明人： Tatsuhiko Goi , Nobuyoshi Yamauchi , Eiichi Yamakawa
IPC分类号： B64C27/12 , B64C27/14 , F16H15/38 , F16H37/02 , F16H37/08 , B64C27/58
CPC分类号： B64C27/14 , F16H37/086 , B64C2027/125 , F16H2015/383 , Y10T74/1913
摘要： Each engine is directly coupled to an engine deceleration device composed of a traction speed change mechanisms and a planetary speed change mechanism, and is decelerated at a desired speed change ratio, and rotate and drive a collector gear and a main rotor shaft. The collector gear rotates and drives accessories and a tail rotor through a second traction speed change mechanism changing speed in inverse number of the speed change ratio of the traction speed change mechanisms. Thus, the rotating speed of the engines can be continuously decelerated at an arbitrary speed change ratio, and an engine deceleration device of small size, light weight, and low loss is realized. At the same time, a power transmission device for helicopters capable of changing the rotating speed of the main rotor at a constant engine rotating speed is realized.
摘要翻译：每个发动机直接联接到由牵引变速机构和行星变速机构构成的发动机减速装置，并且以期望的变速比减速，并且旋转并驱动集电齿轮和主转子轴。收集器齿轮通过第二牵引变速机构转动和驱动附件和尾转子，转速与牵引变速机构的变速比成反比。因此，发动机的转速可以以任意的变速比连续减速，实现体积小，重量轻，损耗低的发动机减速装置。同时，实现了能够以恒定的发动机转速改变主转子的转速的直升机用动力传递装置。

5. 发明授权

US06454207B1 Flap support mechanism and a flap-equipped rotor blade 有权
标题翻译：翼片支撑机构和带翼片的转子叶片
公开(公告)号：US06454207B1
公开(公告)日：2002-09-24
申请号：US09702809
申请日：2000-11-01
申请人： Eiichi Yamakawa , Noriaki Katayama , Tetsuya Hori
发明人： Eiichi Yamakawa , Noriaki Katayama , Tetsuya Hori
IPC分类号： B64C902
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： A flap support mechanism for attachment of a flap to a rotor blade so as to permit angular displacement with respect thereto has a tension-torsion member disposed coaxial with a hinge axis of the flap. One end at the blade root side of the tension-torsion member is secured to the rotor blade. The other end at the blade tip side of the tension-torsion member is secured to the flap. The tension-torsion member is placed such that it passes through a narrow cavity formed at the interior of the rotor blade. Such construction permits smooth flap motion in spite of a large centrifugal force.
摘要翻译：用于将翼片附接到转子叶片以允许相对于其的角位移的翼片支撑机构具有与翼片的铰链轴线同轴设置的张力扭转构件。张力扭转构件的叶片根侧的一端固定到转子叶片。张力扭转构件的叶片末端侧的另一端固定在翼片上。张力扭转构件被放置成使得其穿过形成在转子叶片内部的窄空腔。这样的结构允许平滑的翼片运动，尽管离心力很大。

6. 发明授权

US06272404B1 Flight path indicated apparatus 失效
标题翻译：飞行路线指示装置
公开(公告)号：US06272404B1
公开(公告)日：2001-08-07
申请号：US09250281
申请日：1999-02-16
申请人： Takaki Amano , Eiichi Yamakawa
发明人： Takaki Amano , Eiichi Yamakawa
IPC分类号： G01C2300
CPC分类号： G01C23/005 , G02B27/01
摘要： A flight path display apparatus provided in a cockpit of an aircraft has a head-up display unit. An image combining panel of the head-up display unit displays a flight path image projected from projecting system which is superimposed on the outside view. Computing system for calculating the image to be projected to the image combining panel calculates a display position of the target flight path based on data from storage system in which predetermined flight paths are stored and from aircraft flight data measuring system for measuring the position and attitude of the aircraft. When the display position of the target flight path is outside a display area of the image combining panel, a target mark indicative of a direction toward the flight path from the center of the display area blinks on the image combining panel. With the above construction, a flight path display apparatus which allows a pilot to keep sight on a target flight path is realized.
摘要翻译：设置在飞行器的驾驶舱中的飞行路径显示装置具有平视显示单元。平视显示单元的图像组合面板显示从投影系统投影的飞行路径图像，其叠加在外部视野上。用于计算要投影到图像组合面板的图像的计算系统基于存储有预定飞行路径的存储系统的数据和用于测量位置和姿态的飞行器飞行数据测量系统来计算目标飞行路径的显示位置飞机。当目标飞行路径的显示位置在图像合成面板的显示区域之外时，表示从显示区域的中心向飞行路径的方向的目标标记在图像合成面板上闪烁。通过上述结构，可以实现使飞行员能够保持瞄准目标飞行路径的飞行路径显示装置。

7. 发明授权

US06499690B1 Rotor blade flap drive apparatus 有权
标题翻译：转子叶片挡板驱动装置
公开(公告)号：US06499690B1
公开(公告)日：2002-12-31
申请号：US09673980
申请日：2000-12-06
申请人： Noriaki Katayama , Tatsuro Hongu , Eiichi Yamakawa
发明人： Noriaki Katayama , Tatsuro Hongu , Eiichi Yamakawa
IPC分类号： B64C2700
CPC分类号： B64C27/615 , B64C2027/7266 , B64C2027/7272 , Y02T50/34
摘要： Displacements of output portions 35, 36 of a pair of piezoelectric actuators 25, 26 arranged spanwise in a flap drive apparatus are magnified by a displacement magnification mechanism 27 so that a swing arm 28 is driven in swinging fashion with large amplitude. A flap 22 attached to the trailing edge of a blade 21 by way of a connecting rod 30 connected to a tip of the swing arm 28 is driven in vertical angular displacement fashion. The displacement magnification mechanism 27 possesses an eccentric shaft 40 has a first shaft 41 and second shaft 42 with offset axes. An output portion 35 is coupled to the first shaft 41, and an output portion 36 is coupled to the second shaft 42. The swing arm 28 is fixed to the eccentric shaft 40. Displacement of the output portions 35, 36 of the actuators 25, 26 in opposite phase results in a stable swing of the swing arm 28.
摘要翻译：在翼片驱动装置中翼展地布置的一对压电致动器25,26的输出部分35,36的位移由位移放大机构27放大，使得摆动臂28以大幅度的摆动方式被驱动。通过连接到摆臂28的尖端的连杆30连接到叶片21的后缘的翼片22以垂直角位移方式被驱动。位移放大机构27具有偏心轴40，具有第一轴41和具有偏移轴的第二轴42。输出部分35联接到第一轴41，并且输出部分36联接到第二轴42.摆臂28固定到偏心轴40.致动器25的输出部分35,36的位移， 26相反地导致摆臂28的稳定摆动。

8. 发明授权

US06315522B1 Helicopter blade aerofoil and helicopter blade 有权
标题翻译：直升机叶片翼型和直升机叶片
公开(公告)号：US06315522B1
公开(公告)日：2001-11-13
申请号：US09511802
申请日：2000-02-23
申请人： Eiichi Yamakawa , Akihiko Tsuchihashi , Kenjiro Inagaki
发明人： Eiichi Yamakawa , Akihiko Tsuchihashi , Kenjiro Inagaki
IPC分类号： B63H126
CPC分类号： B64C27/467 , Y10S416/05
摘要： Upper and lower faces of a helicopter blade aerofoil are defined by the following coordinates. TABLE 1 X/C Yup/C Ylow/C 0.00000 0.00000 0.00000 0.00100 0.00511 −0.00584 0.00250 0.00843 −0.00813 0.00500 0.01218 −0.01014 0.00750 0.01505 −0.01136 0.01000 0.01747 −0.01218 0.01250 0.01959 −0.01277 0.01500 0.02150 −0.01328 0.01750 0.02325 −0.01375 0.02000 0.02487 −0.01415 0.02500 0.02780 −0.01483 0.05000 0.03891 −0.01714 0.07500 0.04682 −0.01862 0.10000 0.05291 −0.01979 0.15000 0.06152 −0.02206 0.20000 0.06666 −0.02470 0.25000 0.06892 −0.02729 0.30000 0.06895 −0.02949 0.35000 0.06841 −0.03109 0.40000 0.06744 −0.03211 0.45000 0.06568 −0.03270 0.50000 0.06301 −0.03272 0.55000 0.05943 −0.03211 0.60000 0.05498 −0.03084 0.65000 0.04968 −0.02883 0.70000 0.04349 −0.02600 0.75000 0.03649 −0.02237 0.80000 0.02886 −0.01794 0.85000 0.02087 −0.01315 0.90000 0.01279 −0.00777 0.95000 0.00538 −0.00304 1.00000 0.00236 −0.00095 leading edge radius r/C=0.0096 center of circle X/C=0.0097, Y/C=−0.0018 Accordingly, the maximum lift coefficient Clmax is large in a wide velocity range from lower velocity to higher velocity, and reduction of noise level and pitching moment can be achieved.
摘要翻译：直升机叶片机翼的上下面由以下坐标定义：前缘半径r / C = 0.0096圆心X / C = 0.0097，Y / C = -0.0018因此，最大升力系数Clmax大可以实现从较低速度到较高速度的宽速度范围，以及噪声水平和俯仰力矩的降低。

9. 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。

10. 发明授权

US06190132B1 Rotor blade for rotorcraft 有权
标题翻译：旋翼飞轮转子叶片
公开(公告)号：US06190132B1
公开(公告)日：2001-02-20
申请号：US09404824
申请日：1999-09-24
申请人： Eiichi Yamakawa , Atsushi Murashige , Tomoka Tsujiuchi
发明人： Eiichi Yamakawa , Atsushi Murashige , Tomoka Tsujiuchi
IPC分类号： B64C2746
CPC分类号： B64C27/46 , B64C27/463 , B64C27/467 , Y10S416/02
摘要： A blade root portion of a rotor blade is attached to a rotor head for rotating. A center portion linearly elongates from the blade root portion. A blade tip portion outward elongates from the center portion and has a shape which is defined by a leading edge, a side edge and a trailing edge, and has a predetermined aerofoil. In the leading edge of the blade tip portion, a swept-back angle &lgr;(r) at a distance r from the rotation center of a rotor satisfies relational expression (1) of a rotor blade length R of a rotorcraft, a maximum flight Mach number M∞ which is a flight limit speed of the rotorcraft, a blade tip Mach number MTIP which is a tip speed during hovering, and a drag divergence Mach number Mdd which is determined from the aerofoil of the blade tip portion. According to this configuration, it is possible to provide a rotor blade for a rotorcraft in which the performance in high-speed flying is improved, the high-speed impulsive noise can be reduced, and a high control performance is attained.
摘要翻译：转子叶片的叶片根部附接到转子头部用于旋转。中心部分从叶片根部线性延伸。叶片尖端部分从中心部分向外延伸并且具有由前缘，侧边缘和后缘限定的形状，并且具有预定的机翼。在叶片尖端部分的前缘中，与转子旋转中心距离r的扫掠角lambd（r）满足旋翼飞机转子叶片长度R的关系式（1），最大飞行马赫数数字Minfin是旋翼航空器的飞行极限速度，作为悬停期间的尖端速度的叶片尖端马赫数MTIP，以及从叶片尖端部分的翼面确定的牵引发散马赫数Mdd。根据该结构，能够提供用于旋转飞行器的转子叶片，其中提高了高速飞行的性能，可以降低高速冲击噪声，并且实现了高的控制性能。

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