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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

US20040195435A1 Wing with inflatable struts 有权
标题翻译：翼与充气支柱
公开(公告)号：US20040195435A1
公开(公告)日：2004-10-07
申请号：US10732046
申请日：2003-12-09
发明人： Tony Logosz
IPC分类号： B64C015/00
CPC分类号： B64C31/06 , B64C2031/065
摘要： An aerodynamic wing formed by a flexible canopy with integrated inflatable, elastically deformable members integrated into the lifting surface. Preferably, the elastically deformable member extends and contracts the lifting surface depending on forces experienced by the wing. In one embodiment, the wing comprises an inflatable leading edge kite.
摘要翻译：由柔性罩组成的气动翼，其具有集成在提升表面中的集成的可充气的可弹性变形的构件。优选地，可弹性变形构件根据机翼所经受的力而延伸和收缩提升表面。在一个实施例中，翼包括可充气的前缘风筝。

8. 发明申请

US20040129828A1 Gyrostabilized self propelled aircraft 有权
标题翻译： Gyrostabilized自推进飞机
公开(公告)号：US20040129828A1
公开(公告)日：2004-07-08
申请号：US10390222
申请日：2003-03-17
发明人： Nicolae Bostan
IPC分类号： B64C015/00 , B64C029/00
CPC分类号： B64C17/06 , B64C29/0025 , B64C29/02 , B64C39/024 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162
摘要： An unmanned air vehicle comprises a fuselage that defines aerodynamic flight surfaces, an engine mounted to the fuselage having an engine shaft arranged to rotate about a longitudinal axis with respect to the fuselage, and a propeller mounted to the engine shaft so as to rotate to thereby provide thrust. The aircraft also comprises a gyroscopic stabilization member coupled to the shaft such that rotation of the engine shaft results in rotation of the gyroscopic member. Thus, there is more stability during the entire flight envelope. In one embodiment, the gyroscopic stabilization member is comprised of a ring that is attached to the outer ends of the blades of the propeller and the ring is also selected so as to have a mass that will result in the gyroscopic stabilization member having a sufficient angular momentum so as to gyroscopically stabilize the aircraft.
摘要翻译：无人驾驶飞行器包括限定空气动力学飞行表面的机身，安装到机身上的发动机，其具有被布置为围绕相对于机身的纵向轴线旋转的发动机轴，以及安装到发动机轴上以便旋转的螺旋桨提供推力。飞机还包括联接到轴的陀螺稳定构件，使得发动机轴的旋转导致陀螺仪构件的旋转。因此，在整个飞行包络中有更多的稳定性。在一个实施例中，陀螺稳定构件包括附接到螺旋桨的叶片的外端的环，并且环也被选择为具有将导致陀螺稳定构件具有足够角度的质量动力，以便陀螺仪稳定飞机。

9. 发明申请

US20030122033A1 Ring-shaped wing helicopter 审中-公开
标题翻译：环形翼直升机
公开(公告)号：US20030122033A1
公开(公告)日：2003-07-03
申请号：US10295796
申请日：2002-11-15
发明人： Hengwei Gao
IPC分类号： B64C015/00 , B64C029/00
CPC分类号： B64C39/06 , B64C27/20 , B64C39/001
摘要： The invention discloses a new type ring-shaped wing helicopter, which is similar to a flying saucer in appearance with lift and attitude control torque brought by the blades of two ring-shaped wings rotating in opposite directions between the inlet cascade and the outlet cascade of the circular fringe of wing fuselage. The helicopter of this kind without any outer rotors has high flying speed, good hydrodynamic form and simple-small structure and extensive securitiesnullthe crewman can easy escape quickly by ejecting upwardly in danger, the body of the helicopter allows slight impact with other objects during routine flight, and the running parts with high kinetic energy cannot threaten the personnel inside and outside the helicopter directly in its taking off and landing processes.
摘要翻译：本发明公开了一种新型的环形翼直升机，其类似于外观上的飞碟，具有由入口级联和出口级联之间的相反方向旋转的两个环形翼片的叶片提升和姿态控制扭矩翼机身的圆形边缘。这种没有任何外转子的直升机具有高飞行速度，良好的流体动力形式和简单的小结构和广泛的证券 - 船员可以通过向上弹出危险而迅速逃脱，直升机的身体允许其他物体轻微的撞击常规飞行，高动能运行部分不能直接在直升机起飞和着陆过程中对直升机内外人员造成威胁。

10. 发明申请

US20020195521A1 Aeroplane spiralling mechanism - 2 审中-公开
标题翻译：飞机螺旋机构 - 2
公开(公告)号：US20020195521A1
公开(公告)日：2002-12-26
申请号：US10173634
申请日：2002-06-19
发明人： Tom Kusic
IPC分类号： B64C005/00 , B64C009/00 , B64C015/00 , B64C019/00
CPC分类号： B64C5/04 , B64C5/10 , B64C9/00 , B64C9/02 , B64C13/16 , B64C13/18
摘要： An aeroplane 1 with a spiral inducing assembly 2 which is capable of inducing the aeroplane to travel in a continuous spiralling motion without the aeroplane rolling. Two fins 3 and 4 are attached to a tube 5 that is able to rotate around the encircled part of the fuselage. The fins 3, 4 are able to rotate in a pivoting manner on the rotatable tube 5 with respect to the rotatable tube 5, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 5. Fin 3 is larger than fin 4. The difference in sizes between the fins makes the larger fin 3 exert a greater force on the rotatable tube 4 than the smaller fin 4 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 5 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 3, 4 would exert a lateral force on the rotatable tube 5. Thus, as well as forcing the rotatable tube 5 to rotate, the fins 3, 4 would also push the rotatable tube sideways. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the aeroplane when in flight.
摘要翻译：具有螺旋引导组件2的飞机1，其能够引导飞机以连续的螺旋运动而不飞机滚动。两个翅片3和4连接到能够围绕机身的环绕部分旋转的管5。翅片3,4能够相对于可旋转管5以可枢转的方式旋转在可旋转管5上，从而相对于可旋转管5的纵向轴线改变它们的间距。翅片3大于翅片4。散热片之间的尺寸差使得较大的翅片3在翅片一致倾斜时比较小的翅片4在可转动的管子4上施加更大的力。因此翅片之间的空气动力学不平衡使得可旋转管5旋转。当与纵向轴线一致地倾斜时，两个翅片3,4将在可旋转的管5上施加横向力。因此，以及迫使可旋转管5旋转，翅片3,4还将推动侧向旋转管。但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向不断旋转，导致飞机在飞行中的螺旋运动。

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