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1. 发明申请

US20040245375A1 INTEGRATED HIGH-SPEED AIRCRAFT AND ASSOCIATED METHODS OF MANUFACTURE 有权
标题翻译：综合高速飞机及相关制造方法
公开(公告)号：US20040245375A1
公开(公告)日：2004-12-09
申请号：US10683671
申请日：2003-10-09
发明人： Eric E. Adamson , Paul W. Dees , Edward W. Gronenthal , Walter H. Howard JR. , Chester P. Nelson , Mithra M. Sankrithi , Gerhard E. Seidel , V. Kenneth Stuhr
IPC分类号： B64C015/00
CPC分类号： B64C1/0009 , B64C1/26 , B64C25/04 , B64C25/10 , B64C30/00 , B64C2001/0027 , B64C2001/0045 , B64D9/003 , B64D11/00 , B64D27/18 , B64D37/04 , Y02T50/12 , Y02T50/44 , Y02T50/46
摘要： Integrated high-speed aircraft, such as high-speed transport aircraft, and associated methods of manufacture. In one embodiment, a high-speed transport aircraft includes a fuselage having a first fuselage portion and a second fuselage portion positioned aft of the first fuselage portion. The first fuselage portion can have a first cross-sectional area and the second fuselage portion can have a second cross-sectional area that is less than the first cross-sectional area. The high-speed transport aircraft can further include a wing and a propulsion system. The wing can extend outwardly from the fuselage at least proximate to the second fuselage portion and can include a leading edge region and a trailing edge region. The propulsion system can include an engine nacelle fixedly attached to the wing and laterally aligned with the second fuselage portion. In one aspect of this embodiment, the engine nacelle can include an air inlet positioned aft of the leading edge region of the wing and an exhaust gas outlet positioned aft of the trailing edge region of the wing.
摘要翻译：集成高速飞机，如高速运输飞机及相关制造方法。在一个实施例中，高速运输飞机包括具有第一机身部分的机身和位于第一机身部分后方的第二机身部分。第一机身部分可以具有第一横截面积，并且第二机身部分可以具有小于第一横截面积的第二横截面面积。高速运输机可以进一步包括机翼和推进系统。机翼可以从机身至少靠近第二机身部分向外延伸，并且可以包括前缘区域和后缘区域。推进系统可以包括固定地附接到机翼并与第二机身部分横向对齐的发动机机舱。在该实施例的一个方面，发动机舱可以包括位于翼的前缘区域后方的空气入口和位于翼的后缘区域后方的排气出口。

2. 发明申请

US20030094540A1 Last chance aircraft back-up hydraulic system 失效
标题翻译：最后机会飞机后备液压系统
公开(公告)号：US20030094540A1
公开(公告)日：2003-05-22
申请号：US09990639
申请日：2001-11-21
申请人： The Boeing Company
发明人： Paul E. Shappell , Richard H. Janiesch
IPC分类号： B64B001/36 , B64C015/00
CPC分类号： B64C13/42 , F15B20/005 , F15B21/06
摘要： A last chance aircraft back-up hydraulic system in which fuel from the fuel tanks of the aircraft is injected into the return line of a leaking hydraulic system by use of a pump activated by a guarded switch by the aircraft's pilot. The fuel serves as hydraulic fluid to operate the pumps of the system as it is injected upstream from the fluid being lost to extend the operating time of the system and prevent failure so the aircraft can be landed at a site.
摘要翻译：最后一次飞机后备液压系统，其中来自飞机的燃料箱的燃料通过使用由飞行器的驾驶员由防护开关激活的泵被注入到泄漏的液压系统的返回管线中。燃料用作液压流体，以在系统的泵被注入上游从被损失的流体喷射以延长系统的运行时间并且防止故障从而使飞机降落在现场时操作系统的泵。

3. 发明申请

US20020104921A1 Electrical remote-control and remote-power flying saucer 审中-公开
标题翻译：电动遥控和遥控功率飞碟
公开(公告)号：US20020104921A1
公开(公告)日：2002-08-08
申请号：US10048091
申请日：2001-12-17
发明人： Philippe Louvel
IPC分类号： B64C015/00 , B64C029/00
CPC分类号： A63H27/12 , A63H27/002 , A63H27/04 , A63H30/02
摘要： The purpose of the invention is a light aircraft, remotely supplied and remotely controlled, propelled by electrical motors coupled to propellers, this device being able to perform stationary flight and to move in the three space dimensions in a controlled way. The system includes an aircraft (1), a control unit (3) and a handling unit (4). The aircraft comprises four propellers, each of them driven by a electric motor, a gyroscopic device, tilt sensors, a yaw sensor and an extrenal protective body. The invention also describes the method for the fliht closed loop control. The main purpose of this invention is to provide a enjoyable and educative toy, mainly intended for indoor flight. In a variant of the invention, the aircraft is fitted with a miniaturized video camera, in order to perform remote inspections on buildings or elements difficult to access.
摘要翻译：本发明的目的是远程供应和远程控制的轻型飞机，由耦合到螺旋桨的电动机驱动，该装置能够以受控的方式执行固定飞行并在三个空间维度中移动。该系统包括飞机（1），控制单元（3）和操纵单元（4）。飞机包括四个螺旋桨，每个螺旋桨由电动机驱动，陀螺装置，倾斜传感器，偏航传感器和外围保护体。本发明还描述了用于快速闭环控制的方法。本发明的主要目的是提供一种愉悦和有教育意义的玩具，主要用于室内飞行。在本发明的变型中，飞行器配备有小型化的摄像机，以便对难以进入的建筑物或元件执行远程检查。

4. 发明申请

US20020030137A1 Method of steering aircraft, and aircraft 失效
标题翻译：转向飞机和飞机的方法
公开(公告)号：US20020030137A1
公开(公告)日：2002-03-14
申请号：US09944182
申请日：2001-09-04
申请人： NATURAL COLOUR KARI KIRJAVAINEN OY
发明人： Kari Kirjavainen
IPC分类号： B64C015/00 , B64C027/82
CPC分类号： B64C29/00
摘要： A method of steering an aircraft, and an aircraft comprising a supporting structure, at least one utility space, at least two propellers whose axles are arranged horizontally, and a driving mechanism to rotate each propeller. The blade angles of at least one propeller of the aircraft are adjusted as a function of a rotation angle of the propeller such that the blow power of the propellers provides the aircraft with a lifting force, and after take-off of the aircraft the blade angles of the propellers are adjusted such that the blow power of the propellers provides the aircraft with horizontal flight.
摘要翻译：一种转向飞行器的方法，以及包括支撑结构的飞机，至少一个通用空间，至少两个其水平布置的螺旋桨的螺旋桨和用于旋转每个螺旋桨的驱动机构。飞机的至少一个螺旋桨的叶片角度被调节为螺旋桨的旋转角度的函数，使得螺旋桨的吹动功率为飞机提供提升力，并且在飞机起飞之后叶片角度的螺旋桨的调整使得螺旋桨的吹动能力为飞机提供水平飞行。

5. 发明申请

US20010032905A1 Method and apparatus for converting electrostatic potential energy 审中-公开
标题翻译：用于转换静电势能的方法和装置
公开(公告)号：US20010032905A1
公开(公告)日：2001-10-25
申请号：US09732110
申请日：2000-12-07
发明人： Peter Grandics
IPC分类号： B64C015/00 , B64C027/82
CPC分类号： B64G1/421 , B64G1/409
摘要： A new method is described to produce directional currents in the space lattice, the fundamental fabric of the universe. The currents may be unidirectional or vortexual in nature and are suitable for propulsion or the generation of electric power. For propulsion, the unidirectional currents are induced by charging capacitors possessing suitable geometries. This will allow the manufacture of vehicles capable of levitation and flight. The vortexual space lattice currents are produced in a suitable pyramid when electrostatic and magnetic fields interact transversally. The vortex causes charge separation and current in the coil wrapped around the pyramid.
摘要翻译：描述了一种新的方法来在宇宙的基本结构空间格中产生方向电流。电流本质上可以是单向的或涡流的，并且适用于推进或产生电力。对于推进，单向电流由具有合适几何形状的充电电容器引起。这将允许制造能够悬挂和飞行的车辆。当静电和磁场横向相互作用时，涡旋空间格子电流在适当的金字塔中产生。涡流引起电荷分离，并缠绕在金字塔周围的线圈中的电流。

6. 发明申请

US20010020665A1 Vehicle with vertical wings and a stabilizing torque system of jets to use fluid energy for forward motion 有权
标题翻译：具有垂直翼的车辆和用于向前运动的流体能量的喷射器的稳定扭矩系统
公开(公告)号：US20010020665A1
公开(公告)日：2001-09-13
申请号：US09800659
申请日：2001-03-08
发明人： James C. Hayes
IPC分类号： B64C015/00
CPC分类号： B64C5/00 , B64C5/08 , B64C15/00 , B64C15/14
摘要： Disclosed is a fluid vehicle having one or more vertical wings in contact with the fluid for generating a forward motion. This fluid vehicle also has a stabilizing torque system for generating jets transverse to the forward motion for the purpose of counterbalancing any capsizing effect. Preferably, the system is devised to generate up and down jets to the opposite ends of at least one horizontal wing.
摘要翻译：公开了一种流体车辆，其具有与流体接触的一个或多个垂直翼片，用于产生向前运动。该流体车辆还具有用于产生横向于向前运动的喷气的稳定扭矩系统，以平衡任何倾覆效果。优选地，该系统被设计成向至少一个水平翼的相对端产生上下喷射。

7. 发明申请

US20040200929A1 BALL SCREW ACTUATOR FOR AIRCRAFT CONTROL SURFACES 失效
标题翻译：用于飞机控制表面的滚珠丝杠执行器
公开(公告)号：US20040200929A1
公开(公告)日：2004-10-14
申请号：US10642603
申请日：2003-08-19
申请人： UMBRA CUSCINETTI S.P.A.
发明人： Federico Perni , Sandro Capolungo , Luciano Pizzoni
IPC分类号： B64C015/00
CPC分类号： F16H25/205 , B64C13/28 , F16H25/2204 , F16H25/2472
摘要： A ball screw actuator for aircraft control surfaces comprises a lead screw, motor means to set the screw in rotation about its longitudinal axis and a primary body connected to a control surface and engaged on the control screw by means of a plurality of balls movable on the thread of said screw. A secondary body is connected to the primary body and has an auxiliary portion provided with an engagement surface facing the thread of the lead screw at a predetermined distance; the engagement surface is shaped to engage on the thread of said lead screw. The actuator further comprises means for uncoupling the secondary body from the auxiliary portion in the rotation motion about the longitudinal axis.
摘要翻译：用于飞行器控制表面的滚珠丝杠致动器包括导螺杆，用于将螺钉围绕其纵向轴线旋转的马达装置和连接到控制表面的主体，并且借助于可在其上移动的多个球接合在控制螺钉上所述螺丝的螺纹。副主体连接到主体并且具有辅助部分，其设置有以预定距离面对着丝杠螺纹的接合表面; 接合表面成形为接合在所述丝杠的螺纹上。致动器还包括用于在围绕纵向轴线的旋转运动中使副主体与辅助部分脱离联接的装置。

8. 发明申请

US20030213869A1 Translational propulsion system for a hybrid vehicle 审中-公开
标题翻译：混合动力车辆的平移推进系统
公开(公告)号：US20030213869A1
公开(公告)日：2003-11-20
申请号：US10146754
申请日：2002-05-16
发明人： Mark Winfield Scott , Vincent Francis Millea
IPC分类号： B64C015/00 , B64C029/00
CPC分类号： B64C27/20
摘要： A translational propulsion system for a hybrid UAV includes a pusher prop mounted to the rear of the aircraft with its rotational axis oriented substantially horizontal. The pusher prop is mounted to a driveshaft assembly which transmits power from a coaxial transmission to drive the pusher prop. The driveshaft assembly includes a shaft which defines an axis of rotation. The shaft is mounted to the transmission through a crown spline assembly and is supported by a single bearing. The crown spline and the inherent slop in the bearing accommodates angular deflection and misalignment. The length of the shaft is selected such that the force on the crown spline is less than an allowable level.
摘要翻译：用于混合动力UAV的平移推进系统包括安装在飞行器后部的推杆，其旋转轴线基本上水平地定向。推进器支架安装到传动轴组件，其传动来自同轴传动装置的动力以驱动推杆支架。驱动轴组件包括限定旋转轴线的轴。轴通过冠状花键组件安装到变速器上，并由单个轴承支撑。冠状花键和轴承中的固有斜率可以承受角度偏转和不对准。轴的长度选择为使得花键的力小于允许水平。

9. 发明申请

US20030173455A1 Ground-effect aircraft and airfield 审中-公开
标题翻译：地面飞机和机场
公开(公告)号：US20030173455A1
公开(公告)日：2003-09-18
申请号：US10100734
申请日：2002-03-18
发明人： Zoltan Herpay
IPC分类号： B64C015/00 , B64C029/00
CPC分类号： B64C39/12 , B60V1/08 , B64F1/00
摘要： A Ground-effect Aircraft and Airfield, both for serving sea-sides located mass-transportation in a manner that this aircraft is alway flying very near to the sea-level and always landing on sea-side resources on its own specially designed framed sea-strip, inside which the water is always mirror smooth, having a wide span for carrying about 500 passengers in the wing, quickly removable from the long and wide double-bubble fuselage, the fuel-tank, whose nose has a canard wing, its tail has a big, singular, specially designed engine, quickly removeable from the main wing, which is very quickly refillable, having two stabilizer tail plains, each with two knife-edged fuselages, using inflatables for the quick lifting up of the wing in changing a new fuselage, making the flying capacity more economical, thus, while it is the wing which is the heart of the matter, it is served by twice as many fuselages.
摘要翻译：一个地面效应的飞机和机场，用于服务海边，以这种飞机飞越非常接近海平面的方式进行群众交通，并且始终着陆在海边资源上，专门设计的框架海上，水面总是镜面光滑，宽阔的范围内可以携带约500名乘客的机翼，可以从长而宽的双层泡沫机身快速拆下，燃油箱的鼻子有一个鸭翼，尾部有一个大，独特的，特别设计的发动机，可以从主翼快速拆除，这是非常快速的可重新填充，有两个稳定器尾翼平原，每个都有两个刀刃机身，使用气球快速提升机翼改变新的机身，使飞行能力更加经济，因此，它是机翼的核心，它是由机身的两倍。

10. 发明申请

US20030167763A1 Contingency hydraulic power unit 失效
标题翻译：应急液压动力装置
公开(公告)号：US20030167763A1
公开(公告)日：2003-09-11
申请号：US10093151
申请日：2002-03-07
发明人： Tibor Farkas
IPC分类号： B64C005/00 , B64C009/00 , B64C013/00 , B64C015/00
CPC分类号： B64D25/00 , B64C13/42 , B64G1/14 , B64G1/22 , B64G1/24 , B64G1/26 , Y02T50/44
摘要： An hydraulic power assembly 10 is provided, including at least one primary hydraulic power unit 20 supplying hydraulic fluid 30 to a hydraulic system 34, and a contingency hydraulic power unit 50 utilizing the orbiter's helium storage tank 52 to power a contingency hydraulic drive 56 to supply hydraulic fluid 30 from a contingency hydraulic fluid reserve 58 to the hydraulic system 34 during peak loading conditions.
摘要翻译：设置有液压动力组件10，其包括至少一个主液压动力单元20，其向液压系统34供应液压流体30;以及应急液压动力单元50，其利用轨道飞行器的氦储存罐52为偶然的液压驱动器56提供动力以供应液压流体30从紧急液压储备58到达液压系统34。

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