公开(公告)号：US6135713A

公开(公告)日：2000-10-24

申请号：US233986

申请日：1999-01-19

Applicant: David B. Domzalski ,  Friedrich K. Straub ,  Dennis K. Kennedy

Inventor： David B. Domzalski ,  Friedrich K. Straub ,  Dennis K. Kennedy

IPC: B64C27/00 ,  B64C27/615 ,  B64C9/00

CPC classification number: B64C27/615 ,  B64C27/001 ,  B64C2027/7277 ,  B64C2027/7283 ,  B64C2027/7288 ,  Y02T50/34

Abstract: An actively controlled helicopter rotor blade includes a trailing edge flap actuated by a fast-acting actuator. A lightweight, rugged, fast-acting actuator suitable for use as the flap actuator comprises a pair of column actuators composed of a smart material such as piezoelectric, magnetostrictive, shape memory alloy or other material that exhibits a shape change when subjected to an external stimulus. Each of the column actuators is composed of multiple piezoelectric ceramic actuator elements bonded together to form the individual columns. Each of the column actuators engages the base of an actuator tube that, in turn, is urged against the column actuators by a tension member. Differential voltage applied to the columns causes a differential elongation of the column actuators, which causes the actuator tube to pivot about an axis proximal the tips of the column actuators. The movement of the actuator tube is coupled by a linkage to the rotor blade flap. Spherical joints are disposed between the column actuators and the actuator tube to prevent transmission of substantial bending loads to the column actuators and a mid-point support is also provided for each of the column actuators to limit the magnitude of acceleration induced bending loads, which would otherwise lead to tensile failure of the ceramic actuator elements.

Abstract translation: 主动控制的直升机转子叶片包括由快速作用的致动器驱动的后缘翼片。 一种轻巧，坚固，快速作用的致动器，适合用作翼片致动器，包括一对柱形致动器，其由诸如压电，磁致伸缩，形状记忆合金或其它材料的智能材料组成，当受到外部刺激时，其表现出形状变化 。 每个柱致动器由多个压电陶瓷致动器元件组成，结合在一起以形成各个柱。 每个柱致动器接合致动器管的基部，而致动器管的基部又被张力构件推靠在柱致动器上。 施加到柱的差分电压导致柱致动器的差异伸长，这导致致动器管围绕靠近柱致动器的尖端的轴线枢转。 致动器管的运动通过连接件与转子叶片翼片联接。 球形接头设置在柱致动器和致动器管之间，以防止将实质的弯曲载荷传递到柱致动器，并且还为每个柱致动器提供中点支撑件，以限制加速度引起的弯曲载荷的大小， 否则导致陶瓷致动器元件的拉伸失效。

公开(公告)号：US6131849A

公开(公告)日：2000-10-17

申请号：US203769

申请日：1998-12-02

Applicant: Daniel A. Nyhus

Inventor： Daniel A. Nyhus

IPC: B64C27/18 ,  B64C27/24

CPC classification number: B64C27/18 ,  B64C27/24

Abstract: An articulating and telescoping duct is provided for use in a helicopter reaction drive flow path for ducting the exhaust and/or bypass gases from the aircraft engine into the flow ducts of the rotor blades. In a preferred embodiment the telescoping duct comprises a tubular member having a bead formed at each end. Each of the beads has an outside surface formed into a spherically curved sector that is centered radially about the axis of the tubular member. The receiving duct at one end comprises a complementary spherical bore that seals against and retains the spherical outside surface of the tubular member while permitting the tubular member to articulate relative to the receiving duct. The receiving duct at the other end comprises a complementary cylindrical bore that seals against the spherical outside surface of the tubular member while permitting the tubular member both to articulate relative to and telescope in and out of the cylindrical bore.By incorporating an articulating and telescoping duct into the flow path of the reaction drive it is possible to route the exhaust gases from the engine to the rotor blades with less total duct length and with fewer bends than was heretofore possible, thereby reducing the total losses associated with the ducting with a concomitant increase in aircraft efficiency.

Abstract translation: 提供了一种用于直升机反应驱动流路的铰接和伸缩管道，用于将来自飞行器发动机的排气和/或旁路气体引导到转子叶片的流动管道中。 在优选实施例中，伸缩管道包括管状构件，其具有在每个端部处形成的胎圈。 每个珠具有形成为球形弯曲的扇形部分的外表面，其围绕管状构件的轴线径向放置。 在一端的接收管道包括互补的球形孔，其密封并保持管状构件的球形外表面，同时允许管状构件相对于接收管道铰接。 在另一端的接收管道包括互补的圆柱形孔，其在管状构件的球形外表面上密封，同时允许管状构件两者相对于圆柱形孔相对于凸出并且伸出圆柱孔。 通过将铰接和伸缩管道结合到反应驱动器的流动路径中，可以将排气从发动机引导到转子叶片，具有较少的总管道长度并且具有比迄今为止更少的弯曲，从而减少相关的总损失 随着管道的增加，飞机效率也随之增加。

公开(公告)号：US5951252A

公开(公告)日：1999-09-14

申请号：US928905

申请日：1997-09-12

Applicant: Neal W. Muylaert

Inventor： Neal W. Muylaert

IPC: B64C27/39 ,  B64C27/38

CPC classification number: B64C27/39

Abstract: A flap lock device for restraining the flapping movement of a main rotor blade assembly on a helicopter. The flap lock device includes an first elongate frame member which extends between a first end and a second end and second elongate frame member which also extends between a first end and a second end. A pivot connection pivotally connects the first end of the first frame member with the first end of the second frame member. An outwardly facing contact pad is coupled to each of the frame members and adapted for contact with various positions on the helicopter. An actuating device interconnects the first and second frame members and is used to forcibly move the contact pads outwardly and into contact with the helicopter. The flap lock device is installed between the main rotor blade assembly and the main rotor assembly to forcibly maintain the main rotor blade assembly against the droop stop mechanism.

Abstract translation: 一种用于限制主转子叶片组件在直升机上的拍动运动的翼片锁定装置。 翼片锁定装置包括在第一端和第二端之间延伸的第一细长框架构件和在第一端和第二端之间延伸的第二细长框架构件。 枢转连接将第一框架构件的第一端与第二框架构件的第一端枢转地连接。 面向外的接触垫联接到每个框架构件并且适于与直升机上的各种位置接触。 致动装置将第一和第二框架构件互连，并用于将接触垫向外强制地移动并与直升机接触。 翼片锁定装置安装在主转子叶片组件和主转子组件之间，以强制地将主转子叶片组件抵靠下垂停止机构保持。

公开(公告)号：US5731056A

公开(公告)日：1998-03-24

申请号：US661825

申请日：1996-06-11

Applicant: George H. Butler, III

Inventor： George H. Butler, III

IPC: A44B18/00 ,  B32B3/06

CPC classification number: A44B18/00 ,  Y10T24/27 ,  Y10T24/2708 ,  Y10T24/2725 ,  Y10T428/14 ,  Y10T428/24008 ,  Y10T428/24017 ,  Y10T428/24273

Abstract: A securing system includes a primary structure and a first strip of hook and loop fasteners adapted to be secured thereon. A secondary structure includes a plurality of apertures disposed therein. The plurality of apertures fit over the first strip of hook and loop fasteners when the secondary structure is placed onto the primary structure. A second strip of hook and loop fasteners is adapted for fitting over the plurality of apertures of the secondary structure and for contacting portions of the first strip of hook and loop fasteners through the plurality of apertures. The contacting of the first and second strips of hook and loop fasteners secures the primary structure to the secondary structure. The second strip of hook and loop fasteners is flexible, and is removable from the plurality of apertures with only a relatively small removal force, compared to the removal force required to remove a second rigid strip of hook and loop fasteners from the first strip of hook and loop fasteners on the primary structure.

Abstract translation: 固定系统包括主结构和适于固定在其上的钩和环紧固件的第一条。 二次结构包括设置在其中的多个孔。 当二次结构被放置在主结构上时，多个孔适合在第一条钩和紧固件上。 钩和环紧固件的第二条适于装配在二级结构的多个孔上，并且用于使第一条钩和环紧固件的部分通过多个孔接触。 第一和第二条钩和紧固件的接触将主结构固定到二级结构。 第二条钩和紧固件是柔性的，并且与从第一条带钩移除第二刚性带钩环紧固件所需的去除力相比，具有仅相对较小的移除力的可移除的多个孔 并在一级结构上设置环形紧固件。

公开(公告)号：US5583312A

公开(公告)日：1996-12-10

申请号：US397656

申请日：1995-03-01

Applicant: Thaddeus Jakubowski, Jr.

Inventor： Thaddeus Jakubowski, Jr.

IPC: B64D1/06 ,  B64D1/04

CPC classification number: B64D1/06

Abstract: There is provided a renewable energy source ejector rack for retaining and releasing stores (bombs or the like) on an aircraft, which has on-board pressurization capability, employs a single pressurization system for two or more release mechanisms, and uses air or other clean non-pyrotechnic pressurized gases both as the energy source and energy transfer medium. The aircraft contains a miniature compressor and purification system. Ambient air is filtered, dried and stored as an energy medium. Since the compressor system is onboard, the pressure can be constantly maintained regardless of temperature change. Using purified air eliminates the excessive cleaning burden imposed when using state-of-the-art pyrotechnics, and eliminates the sealing problems associated with hydraulics.

Abstract translation: 提供了一种用于在飞机上保存和释放存储（炸弹等）的可再生能源喷射器架，其具有板载加压能力，采用单个加压系统用于两个或更多个释放机构，并且使用空气或其它清洁 非烟火加压气体作为能源和能量转移介质。 该飞机包含一个微型压缩机和净化系统。 环境空气被过滤，干燥并作为能量介质储存。 由于压缩机系统在船上，所以无论温度变化如何，压力都可以持续保持。 使用净化空气消除了使用最先进的烟火技术时施加的过度清洁负担，并消除了与液压相关的密封问题。

公开(公告)号：US5454530A

公开(公告)日：1995-10-03

申请号：US68907

申请日：1993-05-28

Applicant: John W. Rutherford ,  Matthew O'Rourke ,  William R. McDonnell ,  Brian T. Smith

Inventor： John W. Rutherford ,  Matthew O'Rourke ,  William R. McDonnell ,  Brian T. Smith

IPC: B64C27/24 ,  B64C27/22 ,  B64C39/12

CPC classification number: B64C27/24

Abstract: A dual-mode high speed rotorcraft is disclosed which combines the efficiency of a helicopter with the high-speed capability of a fixed wing aircraft. The rotorcraft includes a rotor for propulsion during low-speed flight and hover, which is stopped and locked to function as a fixed wing during a high-speed flight. Also included are a canard and a high-lift tail, which together function to provide substantially all of the lift for the rotorcraft during the transition between low and high-speed flight, so that the rotor may be unloaded while starting and stopping.

Abstract translation: 公开了一种双模高速旋翼飞机，其将直升机的效率与固定翼飞机的高速能力相结合。 旋翼航空器在低速飞行和悬停期间包括用于推进的转子，其在高速飞行期间被停止并锁定以用作固定翼。 还包括一个鸭子和一个高提升尾巴，它们一起起作用，在低速和高速飞行之间的过渡期间为旋翼航空器提供基本上所有的升降机，从而可以在启动和停止时卸载转子。

公开(公告)号：US6092990A

公开(公告)日：2000-07-25

申请号：US869725

申请日：1997-06-05

Applicant: Ahmed A. Hassan ,  Friedrich K. Straub ,  David B. Domzalski

Inventor： Ahmed A. Hassan ,  Friedrich K. Straub ,  David B. Domzalski

IPC: B64C23/04 ,  B64C27/467 ,  B64C27/51 ,  B64C27/04

CPC classification number: B64C27/467 ,  B64C23/04 ,  B64C27/51 ,  B64C2027/725 ,  B64C2230/02 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/14 ,  B64C2230/18 ,  B64C2230/22 ,  B64C2230/28 ,  Y02T50/166 ,  Y02T50/34 ,  Y10S416/50

Abstract: An active control system for reducing blade-vortex-interaction (BVI) noise generated by a rotor blade. The active control system includes a pressure sensor assembly, a device for changing a lift generated by the rotor blade, and a controller for activating the device upon a detected change in air pressure by the sensor assembly. The sensor assembly is disposed in close proximity to the rotor blade, and is adapted to detect a change in air pressure on a surface of the rotor blade near a leading edge of the rotor blade. The device is adapted to be activated by the controller, to thereby change a lift of the rotor blade. The controller activates the device to change a lift of the rotor blade in order to introduce a compensating pressure onto the surface of the rotor blade. This compensating pressure attenuates the magnitude of the change of air pressure. The device for changing a lift generated by the rotor blade can include at least one aperture on the rotor blade and a diaphragm in the interior of the rotor blade. The diaphragm can be activated and moved between a first position and a second position at a frequency. Movement of the diaphragm from the first position to the second position pushes air out of the at least one aperture, and movement of the diaphragm from the second position to the first position draws air into the at least one aperture.

Abstract translation: 一种用于减少由转子叶片产生的叶片 - 涡流相互作用（BVI）噪声的主动控制系统。 主动控制系统包括压力传感器组件，用于改变由转子叶片产生的升力的装置，以及用于通过传感器组件检测到的空气压力变化来启动装置的控制器。 传感器组件设置成紧邻转子叶片，并且适于检测在转子叶片的前缘附近的转子叶片的表面上的空气压力的变化。 该装置适于被控制器激活，从而改变转子叶片的升力。 控制器激活装置以改变转子叶片的升力，以便在转子叶片的表面上引入补偿压力。 这种补偿压力会降低气压变化的大小。 用于改变由转子叶片产生的升力的装置可包括转子叶片上的至少一个孔和转子叶片内部的隔膜。 隔膜可以在第一位置和第二位置之间以一个频率被激活和移动。 隔膜从第一位置移动到第二位置将空气推出至少一个孔，并且隔膜从第二位置移动到第一位置将空气吸入至少一个孔。

公开(公告)号：US5951608A

公开(公告)日：1999-09-14

申请号：US873504

申请日：1997-06-12

Applicant: Stephen S. Osder

Inventor： Stephen S. Osder

IPC: B64C27/18 ,  B64C27/24 ,  B64C39/12 ,  G05D1/08 ,  B64C11/34 ,  B64C27/57

CPC classification number: G05D1/0858 ,  B64C27/18 ,  B64C27/24 ,  B64C39/12

Abstract: The disclosed flight control system includes a rotor blade speed monitor for monitoring the rotor blade speed of the jet powered tri-mode aircraft and for outputting a rotor blade speed command. The flight control system also includes an aircraft attitude controller for controlling the aircraft attitude of the jet powered tri-mode aircraft. Weighted rotor blade attitude stabilization commands and weighted aero surface attitude stabilization commands are output from the aircraft attitude controller to distribute power, control, and lift between the rotor blade and the aero surfaces. Relative weights of the weighted rotor blade attitude stabilization commands decrease with increasing aircraft travelling velocities, and relative weights of the weighted aero surface attitude stabilization commands increase with increasing velocities. A rotor blade lift controller receives the weighted rotor blade attitude stabilization commands and the rotor blade speed commands, and positions the rotor blade swashplate to adjust lift and control according to these commands. An aero lift controller receives the weighted aero surface attitude stabilization commands and deploys the aero surfaces to generate lift and control according to the received weighted aero surface attitude stabilization commands.

Abstract translation: 所公开的飞行控制系统包括用于监测喷射式三模飞行器的转子叶片速度并用于输出转子叶片速度命令的转子叶片速度监视器。 飞行控制系统还包括用于控制喷气动力三模飞行器的飞行器姿态的飞行器姿态控制器。 从飞机姿态控制器输出加权转子叶片姿态稳定命令和加权航空表面姿态稳定命令，以分配转子叶片和航空表面之间的动力，控制和升力。 加权转子叶片姿态稳定指令的相对权重随着飞行器行进速度的增加而减小，加权航空表面姿态稳定指令的相对权重随着速度的增加而增加。 转子叶片提升控制器接收加权的转子叶片姿态稳定命令和转子叶片速度命令，并且定位转子叶片斜盘以根据这些命令调节升程和控制。 航空提升控制器接收加权的航空表面姿态稳定命令并且部署航空表面以根据所接收的加权航空表面姿态稳定命令产生升力和控制。

公开(公告)号：US5934875A

公开(公告)日：1999-08-10

申请号：US987259

申请日：1997-12-09

Applicant: Robert E. Head

Inventor： Robert E. Head

IPC: B64C27/04 ,  A47C7/74

CPC classification number: B64C27/12 ,  B64C27/04

Abstract: A helicopter's main rotor blades are removably attached to a hub, which is rotatably mounted on a mast. The base of the mast is attached to the helicopter's body by unthreaded, expandable bushing bolts. When inserted, the bolts' centerlines lie in a plane which perpendicularly intersects the axial centerline of the mast. The mast is hollow and encases a drive shaft. Splines at one end of the drive shaft removably engage splines on the engine transmission. The hub has a removal fitting for engaging an end of the drive shaft. When the mast is detached and pulled apart from the helicopter body for storage, the removal fitting forces the drive shaft splines to disengage from the tnansmission splines, and keeps the drive shaft inside the mast while the mast is being removed. The main rotor blades' pitch is controlled by a plurality of pitch control linkages. Each linkage is comprised of a first part connected to the mast and a second part connected to the helicopter body. The two parts of each linkage are connected solely by an expandable bushing bolt. Removal of the bolt allows the two parts to be disconnected pursuant to removal of the mast from the body, and keeps the first part attached to the mast during the removal and afterwards. Reaachment of the mast to the helicopter body is accomplished by the reverse of the foregoing operations.

Abstract translation: 直升机的主转子叶片可拆卸地连接到轮毂，轮毂可旋转地安装在桅杆上。 桅杆的基座通过无螺纹的可扩展衬套螺栓连接到直升机的身体。 当插入时，螺栓的中心线位于与桅杆的轴向中心线垂直相交的平面中。 桅杆是空心的并且包围驱动轴。 驱动轴一端的花键可拆卸地接合发动机变速箱上的花键。 轮毂具有用于接合驱动轴的端部的拆卸配件。 当桅杆被拆卸并从直升机主​​体分离以进行存储时，拆卸配合件迫使驱动轴花键与断层花键脱离，并且在桅杆被移除的同时将驱动轴保持在桅杆内。 主转子叶片的间距由多个俯仰控制连杆控制。 每个联动装置包括连接到桅杆的第一部分和连接到直升机主体的第二部分。 每个连杆的两个部分仅由可扩展的衬套螺栓连接。 螺栓的拆除允许两个部件根据桅杆从主体上的拆卸而断开，并且在拆卸和之后将第一部件保持在桅杆上。 通过与前述操作相反的方式，将桅杆重新连接到直升机身上。

公开(公告)号：US5934608A

公开(公告)日：1999-08-10

申请号：US8118

申请日：1998-01-16

Applicant: Gregory E. Dockter

Inventor： Gregory E. Dockter

IPC: B64C27/82

CPC classification number: B64C27/82 ,  B64C2027/8245

Abstract: The bi-directional air flow deflector of the present invention efficiently deflects air to the left opening and the right opening, and minimizes any vertical components of force which may be generated. The air flow vector exiting from each of the openings comprises a dominant horizontal force vector rather than a large component of force in the vertical direction. Vertical components of force may be added, if desired. The bi-directional air flow deflector provides reduced transmission torque requirements, and generally comprises a relatively small number of moving parts. A single moving part may be used to deflect air to either the left opening or the right opening, and this single moving part is not exposed to the outside environment and, accordingly, will generally provide reliable functionality. The bi-directional air flow deflector of the present invention is simple in design, comprises a small number of relatively easy to manufacture parts, and can be used to retrofit existing direct jet thrusters. The components of the bi-directional air flow deflector generally comprise relatively straight sides and surfaces, which require less sophisticated tooling and reduce costs. The reduced number of parts will require a smaller stock of parts for inventory and field support. The bi-directional air flow deflector can be assembled with generally less man power than prior art devices, and generally comprises an increased reliability. Since less energy is generally required to operate the bi-directional air flow deflector of the present invention, increased fuel efficiency can also be realized.

Abstract translation: 本发明的双向空气导流板有效地将空气偏转到左开口和右开口，并且使得可能产生的任何垂直的力分量最小化。 从每个开口排出的空气流动矢量包括主要的水平力矢量，而不是垂直方向上的大的力分量。 如果需要，可以添加力的垂直分量。 双向气流导流器提供降低的传动扭矩要求，并且通常包括相对较少数量的运动部件。 单个移动部件可以用于将空气偏转到左开口或右开口，并且该单个移动部件不暴露于外部环境，因此通常将提供可靠的功能。 本发明的双向气流导流器设计简单，包括少量相对容易制造的部件，可用于改造现有的直接喷射推进器。 双向空气导流器的部件通常包括相对直的侧面和表面，这需要较不复杂的工具并降低成本。 零件数量的减少将需要较少的零件库存和现场支持。 双向气流导流器可以以比现有技术的装置通常更少的人力组装，并且通常包括增加的可靠性。 由于通常需要较少的能量来操作本发明的双向空气导流板，所以也可以实现提高的燃料效率。