公开(公告)号：US20090065651A1

公开(公告)日：2009-03-12

申请号：US12138900

申请日：2008-06-13

申请人： Robert Parks

发明人： Robert Parks

IPC分类号： B64C3/14

CPC分类号： B64C3/10 ,  B64C31/028 ,  Y02T50/12

摘要： An aircraft comprising a fuselage, a sail wing appended to the fuselage, the sail wing having a sail wing root chord length, and wherein the sail wing includes a sail wing leading edge spar, a sail wing membrane attached to the sail wing leading edge spar, and a sail wing trailing edge wire located at a trailing edge of the sail wing membrane, the aircraft further comprising a wing surface extension, located aft and at an inboard area of the sail wing trailing edge wire, the wing surface extension having a wing surface extension root chord length, and wherein the wing surface extension includes a wing surface extension membrane attached to the sail wing trailing edge wire, and a wing surface extension trailing edge, and wherein the wing surface extension trailing edge is reflexed such that the wing surface extension trailing edge is positioned upwards at a first angle with respect to a plane formed along a centerline of the aircraft and along the lower surfaces of the sail wing. The wing surface extension is further configured to affect a reduced nose-up pitching moment, and to produce a more even coefficient of lift along the wing of the aircraft.

摘要翻译： 一种飞机，包括机身，附属于机身的帆翼，具有帆翼根弦长的帆翼，并且其中所述帆翼包括帆翼前缘翼梁，附连到帆翼前缘翼梁的帆翼膜 以及位于帆翼膜的后缘处的帆翼后缘线，所述飞机还包括机翼表面延伸部，所述机翼表面延伸部位于帆翼后缘线的后部和内侧区域，翼表面延伸部具有翼 表面延伸根弦长度，并且其中所述机翼表面延伸部包括附接到所述帆翼后缘线的翼表面延伸膜和翼表面延伸后缘，并且其中所述翼表面延伸后缘被反射，使得所述翼表面延伸膜 延伸后缘相对于沿着飞行器的中心线形成的平面并沿着帆翼的下表面以第一角度向上定位。 机翼表面延伸部进一步构造成影响减小的俯仰俯仰时刻，并且沿着飞行器的翼部产生更均匀的升力系数。

公开(公告)号：US07168656B2

公开(公告)日：2007-01-30

申请号：US11062946

申请日：2005-02-22

申请人： Bhaskar R Pai

发明人： Bhaskar R Pai

IPC分类号： B64C27/10

CPC分类号： B64C27/605 ,  B64C27/10 ,  B64C27/14 ,  B64C31/028

摘要： The present invention relates to a lightweight helicopter with features of coaxial, contra-rotating rotors and weight shift control. It has a rotary wing unit attached to a tricycle assembly through a hang bolt. The rotary wing unit has an engine mounted below a keel post, which drives a pair of contra-rotating coaxial rotors through a primary gearbox and a secondary gear box. The keel post is attached to a triangular control frame, the base of which forms the control bar. The keel post also supports a fuel tank connected to the engine and a tail plane having one or more articulated vertical flaps actuated by cables. The secondary gearbox is provided with a free-wheeling clutch, a pinion gear and bevel gears for transmitting the rotary movement of the engine to the counter rotating coaxial vertical shafts each carrying two rotor blades of airfoil cross section fixed by pitch bearing on teetering plates and teetering hinges to form horizontal rotors. The tricycle assembly has a pilot seat and landing gear as well as controls for operation of the engine, rotors, tail plane and landing gear. The directional control of the helicopter is achieved through the weight shift principle by manipulating the control bar, thereby causing a tilt of the contra-rotating rotors, which cause a corresponding tilt in the aerodynamic thrust of the rotors, propelling the helicopter in the required direction.

摘要翻译： 本发明涉及一种轻型直升机，具有同轴，反转转子和重量变速控制的特征。 它具有通过悬挂螺栓连接到三轮车组件的旋转翼单元。 旋转翼单元具有安装在龙骨柱下方的发动机，其通过主变速箱和次级齿轮箱驱动一对反转的同轴转子。 龙骨柱附接到三角形控制框架，其基座形成控制杆。 龙骨柱还支撑连接到发动机的燃料箱和具有由电缆致动的一个或多个铰接的垂直翼片的尾翼平面。 副齿轮箱设有一个续流离合器，一个小齿轮和一个锥齿轮，用于将发动机的旋转运动传递到反向旋转的同轴垂直轴，每个轴同轴承载两个叶片横截面的叶片横截面，这些叶片横截面通过俯仰轴承固定在旋转板上， 跷跷板铰链形成水平转子。 三轮车组件具有驾驶员座椅和起落架，以及用于发动机，转子，尾翼和起落架操作的控制。 直升机的方向控制通过操纵控制杆通过重量移位原理实现，从而引起反转转子的倾斜，这导致转子的空气动力学推力相应的倾斜，将直升机推向所需方向 。

公开(公告)号：US20030183721A1

公开(公告)日：2003-10-02

申请号：US10390109

申请日：2003-03-17

发明人： Jeffrey J. Wilson

IPC分类号： B64C001/00

CPC分类号： B64C31/028

摘要： An apparatus for enabling an individual to be propelled through air. The apparatus comprises a framework for holding such individual disposed substantially in a center of the apparatus and a pair of winglike members connected for articulated movement with respect to the framework. There is further a means disposed on the framework for initiating propulsion of the apparatus.

摘要翻译： 用于使个体能够通过空气推进的装置。 该装置包括用于保持基本上位于装置的中心的这种个体的框架，以及连接成相对于框架进行铰接运动的一对翼状构件。 还有一种装置设置在框架上用于启动装置的推进。

公开(公告)号：US06260795B1

公开(公告)日：2001-07-17

申请号：US09089602

申请日：1998-06-02

申请人： Kenneth Earl Gay ,  Marc Margulies

发明人： Kenneth Earl Gay ,  Marc Margulies

IPC分类号： B64C338

CPC分类号： B64C31/02 ,  B64C3/48 ,  B64C13/503 ,  B64C31/028 ,  B64D43/02 ,  Y02T50/44

摘要： The Oya glider is a modified hang-glider that incorporates many advanced aerospace technologies, such as, glues, for binding Shape Memory Alloy materials to Piezoelectric Ceramic Strips, and synthetic feathers. Lightweight composite plastic materials treated with the MuCell Process, both for framing and chassis construction. Piezoelectric Sensors and Actuators. Nano wires, and nano cables, for electrical connections and manual control levers. Computer firmware and software, designed to mimic, in real time, the aerodynamic flight reactions to external wind conditions, of a gliding bird. The Oya computerized glider will come as close as technologically possible to imitating a bird's mastery of the wind.

摘要翻译： Oya滑翔机是一种改装的悬挂滑翔机，结合了许多先进的航空航天技术，如胶水，用于将形状记忆合金材料结合到压电陶瓷条和合成羽毛。 用MuCell工艺处理的轻质复合塑料材料，用于框架和底盘结构。 压电传感器和执行器。 纳米线和纳米电缆，用于电气连接和手动控制杆。 计算机固件和软件，旨在实时模拟滑翔鸟的外部风力条件的空气动力学飞行反应。 大亚计算机化的滑翔机将在技术上尽可能接近，以模拟鸟的掌握风。

公开(公告)号：US5474257A

公开(公告)日：1995-12-12

申请号：US156322

申请日：1993-11-23

申请人： Jeffrey A. Fisher ,  Edward V. Miller ,  Dennis Van Dam

发明人： Jeffrey A. Fisher ,  Edward V. Miller ,  Dennis Van Dam

IPC分类号： B64C31/028 ,  B64C3/56

CPC分类号： B64C31/028 ,  Y10S244/901 ,  Y10S244/904

摘要： The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded and deployed in the air.

摘要翻译： 本发明的可部署翼包括内部结构，其具有连接到龙骨翼梁上的分叉的前缘翼梁和交叉翼梁以形成三角翼构型。 该内部结构封闭在由具有上部，下部和布置在其间的织物肋条的织物帆布限定的体积内。 这种织物帆布体积在鼻部停滞点处通过压头进气口内部加压。 这种可部署的机翼可以折叠和部署在空中。

公开(公告)号：US5275117A

公开(公告)日：1994-01-04

申请号：US900193

申请日：1992-06-17

申请人： Jeffrey J. Magnan

发明人： Jeffrey J. Magnan

IPC分类号： B63B35/79 ,  B63H9/06 ,  B64C31/028 ,  B63H9/04

CPC分类号： B64C31/028 ,  B63B35/7973 ,  B63H9/06

摘要： A tensioner for drawing a point on a flexible wing's surface toward its leading edge. The wing's camber is thereby increased and maintained even at high airflow velocities and low angles of attack. The provision of a tensioner length adjustment system allows the wing's camber to be optimized for a particular set of conditions. The fitment of a plurality of such tensioners along the wing's chordlines and along its span allows the wing's shape to be fine-tuned both in terms of camber as well as twist.

摘要翻译： 一个张紧器，用于在柔性翼的表面上朝向其前缘绘制点。 因此，即使在高气流速度和低迎角下，机翼的外倾角也增加并保持。 提供张紧器长度调节系统允许机翼的弯度针对特定的一组条件进行优化。 多个这样的张紧器沿着机翼的弦线并沿其跨度的装配允许机翼的形状在外倾和扭转方面都被微调。

公开(公告)号：US4781341A

公开(公告)日：1988-11-01

申请号：US307861

申请日：1981-10-02

申请人： Witold A. Kasper

发明人： Witold A. Kasper

IPC分类号： B64C31/028 ,  B64C3/14 ,  B64C39/10

CPC分类号： B64C31/028 ,  Y10S244/903

摘要： An ultralight aircraft having a generally rectangular, swept-back, single-surface wing. The wing, which is formed by fabric mounted on exposed spars and ribs, has a reflex profile to provide pitch stability which is further augmented by horizontal stabilizers projecting rearwardly from the wing adjacent the tips. Roll and yaw control are provided by a pair of rudders pivotally mounted at each wing tip. The forward ends of the rudders pivot inwardly to alter the magnitude of the wing's lift. The rudders pivoted simultaneously act as spoilers and speed brakes controlling the rate of descent. Pivoting one of the rudders individually moves the center of lift for one wing inwardly and increases the drag of that wing to roll the aircraft into that wing. The rudders tilt upwardly and outwardly in a dihedral configuration to provide roll stability. Stationary end plates mounted at each wing tip adjacent the rudders provide yaw stability. The aircraft utilizes a single surface wing so that it can descend safely at zero forward speed in a parachute-like manner. Pitch control is made by shifting the pilot's body forward and back. A chassis mounted beneath the wing supports a pilot and a gasoline engine driving a pusher propeller.

摘要翻译： 一架超轻型飞机，具有一般矩形，扫掠的单面翼。 由安装在暴露的翼梁和肋骨上的织物形成的机翼具有反射轮廓，以提供俯仰稳定性，其进一步由水平稳定器进一步增强，该稳定器从邻近尖端的翼向后突出。 滚动和偏航控制由枢转地安装在每个翼尖处的一对舵提供。 方向舵的前端向内枢转以改变机翼升力的大小。 同时枢转的方向舵作为扰流板，并加速制动器控制下降速度。 旋转其中一个方向舵单独地将电梯的中心向内移动一个翼，并增加该翼的阻力以将飞机卷成该翼。 方向舵以二面体结构向上和向外倾斜，以提供辊稳定性。 安装在靠近方向舵的每个翼尖处的固定端板提供偏航稳定性。 飞机使用单个表面翼，使其能够以降落伞状的方式以零前进速度安全地下降。 通过将飞行员的身体向前和向后移动来进行俯仰控制。 安装在机翼下方的底盘支撑驾驶员和驾驶推进器螺旋桨的汽油发动机。

公开(公告)号：US4546938A

公开(公告)日：1985-10-15

申请号：US421192

申请日：1982-09-22

申请人： Jerzy W. Kolecki

发明人： Jerzy W. Kolecki

IPC分类号： B64C31/028 ,  B64D35/00 ,  B64D27/00

CPC分类号： B64C31/028

摘要： A power unit for a hang-glider (1) or the like comprises a combustion motor (2) connected to one end of a drive shaft (9) and a propeller (10) connected to the other end of the drive shaft. To enable the power unit to be used both with pulling or traction-force propellers and pushing propellers (10) there is provided between the drive shaft (9) and the shaft (22) of the propeller (10) a flexible coupling (14) which enables the angle between the drive shaft and the propeller shaft to be adjusted at least in a vertical direction.

摘要翻译： 用于悬挂滑翔机（1）等的动力单元包括连接到驱动轴（9）的一端的燃烧马达（2）和连接到驱动轴的另一端的螺旋桨（10）。 为了使牵引力或牵引力螺旋桨和推动螺旋桨（10）能够使用动力单元，驱动轴（9）和螺旋桨（10）的轴（22）之间设置有柔性联轴器（14） 这使得驱动轴和传动轴之间的角度至少在垂直方向上被调节。

公开(公告)号：US4398684A

公开(公告)日：1983-08-16

申请号：US252153

申请日：1981-04-08

申请人： Dennis Von Ruden

发明人： Dennis Von Ruden

IPC分类号： B64C31/028 ,  B64D27/00 ,  B64D35/00

CPC分类号： B64C31/028 ,  B64D27/00 ,  Y02T50/44 ,  Y10S244/903

摘要： A connecting apparatus (16) for attaching a propeller or fan (14) to an engine (12) is disclosed. A connecting apparatus (16) includes a centrifugal clutch device (48) and drive and driven gears (40, 78) for reducing the speed of propeller (14) relative to engine (12). These elements are contained within a lubricant-filled housing comprised of housing (38) and spider bracket (34). Spider bracket (34) includes two pairs of vibration-dampening first and second mountings (140). First mountings (140) more stiffly resist engine vibration than second mountings (142), thereby dynamically balancing the powerplant with respect to the structural frame (20).

摘要翻译： 公开了一种用于将螺旋桨或风扇（14）附接到发动机（12）的连接装置（16）。 连接装置（16）包括离心式离合器装置（48）和用于降低螺旋桨（14）相对于发动机（12）的速度的驱动和从动齿轮（40,48）。 这些元件包含在由壳体（38）和支架托架（34）组成的润滑剂填充的壳体内。 蜘蛛托架（34）包括两对防振第一和第二安装件（140）。 第一安装件（140）比第二安装件（142）更加硬地抵抗发动机振动，从而相对于结构框架（20）动态平衡动力装置。

公开(公告)号：US4262863A

公开(公告)日：1981-04-21

申请号：US869833

申请日：1978-01-16

申请人： Charles J. Slusarczyk

发明人： Charles J. Slusarczyk

IPC分类号： B64C31/028 ,  F02B75/02 ,  B64C1/16

CPC分类号： B64C31/028 ,  F02B2075/025 ,  Y10S244/903

摘要： A foot-launched and foot-landed hang glider is powered by an internal combustion two-cycle engine drivingly connected through a reduction-drive unit to a large relatively slow-moving propeller. A reduction mount, so referred to because it couples the reduction-drive unit closely to the engine, allows the engine to rotate a large propeller relatively slowly, thus providing more thrust at near-stalling flight conditions. The hang glider, thus powered, also obviates the necessity of being launched from the edge of a precipice and permits flight which is not predicated on the fortuitous selection of favorable air currents.

摘要翻译： 脚踏式和脚踏式悬挂式滑翔机由内燃式二冲程发动机驱动，通过减速驱动单元驱动连接到大型相对较慢的螺旋桨。 因为减速装置将减速驱动单元紧密地连接到发动机上，所以减速装置允许发动机相对缓慢地旋转大的螺旋桨，从而在接近失速的飞行条件下提供更多的推力。 悬挂滑翔机，因此动力，也避免了从悬崖边缘发射的必要性，并允许飞行，而不是偶然选择有利的气流。