公开(公告)号：WO2005099380A2

公开(公告)日：2005-10-27

申请号：PCT/US2005/011541

申请日：2005-04-07

Applicant: LEE, John, R. ,  LEE, Craig ,  EASTLAKE, Charles ,  LADESIC, James, G. ,  MAHR, Peter ,  PIERPONT, Peter, S. ,  ANDERSON, Richard, P.

Inventor： LEE, John, R. ,  LEE, Craig ,  EASTLAKE, Charles ,  LADESIC, James, G. ,  MAHR, Peter ,  PIERPONT, Peter, S. ,  ANDERSON, Richard, P.

IPC: B64C3/54 ,  B64C3/56 ,  B64C3/58 ,  B64C11/00 ,  B64C23/06 ,  B64C39/04

CPC classification number: B64C3/54 ,  B64C3/56 ,  B64C3/58 ,  B64C11/001 ,  B64C23/072 ,  B64C39/04 ,  Y02T50/164

Abstract: This invention relates generally to a lift augmentation system for an airframe. More particularly, the invention concerns the combination of extendable/retractable wing tips with an airframe for lift augmentation as well as wings that can pivot into a deployed position. Flexible surface elements may be rolled for storage and unrolled for deployment with at least one being on the suction surface of the wing and at least one being on the pressure surface of the wing.

Abstract translation: 本发明一般涉及用于机身的提升增强系统。 更具体地，本发明涉及可伸缩翼尖与用于提升增加的机身以及可枢转到展开位置的翼的组合。 柔性表面元件可以被卷起以存储并展开以展开，其中至少一个位于机翼的抽吸表面上，并且至少一个位于机翼的压力表面上。

公开(公告)号：WO2005049423A3

公开(公告)日：2005-07-21

申请号：PCT/CA2004001927

申请日：2004-11-18

Applicant: DISTRIBUTED THERMAL SYSTEMS LT ,  HARRISON HOWARD R

Inventor： HARRISON HOWARD R

IPC: B64C11/00 ,  B64C11/46 ,  B64C11/48 ,  B64D20060101 ,  F02K3/04 ,  F02K3/065

CPC classification number: B64C11/001 ,  B64C11/48 ,  F02K3/04 ,  F02K3/065

Abstract: A coaxial propulsion system has a primary propeller, a flow control element to reduce swirl, and a secondary propeller, mounted in series configuration. A connecting shroud directs the combined thrust. Said primary propeller and said secondary propeller may be connected to the same engine, or independent engines for greater reliability and performance. A coaxial jet fan system has a primary fan, a flow control element to reduce swirl, and a secondary fan, mounted in a series configuration. A connecting shroud directs the combined bypass and jet thrust. Further, a secondary shroud provides a primary bypass and a secondary bypass thrust, thereby establishing a greater level of control over the bypass ratio and engine efficiency.

Abstract translation: 同轴推进系统具有主螺旋桨，用于减少涡流的流量控制元件以及以串联配置安装的辅助螺旋桨。 一个连接的导流罩引导组合推力。 所述主螺旋桨和所述辅助螺旋桨可以连接到相同的发动机或独立的发动机以获得更高的可靠性和性能。 同轴射流风机系统具有主风机，用于减少涡流的流量控制元件以及以串联配置安装的次级风机。 一个连接护罩指导组合的旁路和喷射推力。 此外，二级护罩提供了一级旁路和二级旁路推力，从而对旁路比和发动机效率建立了更高水平的控制。

公开(公告)号：WO2004033295A1

公开(公告)日：2004-04-22

申请号：PCT/EP2002/011386

申请日：2002-10-11

Applicant: UNZICKER, Stefan

Inventor： UNZICKER, Stefan

IPC: B64C29/00

CPC classification number: B64C11/001 ,  B64C3/50 ,  B64C11/48 ,  B64C29/0025 ,  Y02T50/14

Abstract: The present invention discloses an aircraft capable of vertical take-off and landing. The aircraft comprises a single constant speed variable pitch propeller (3), a fuselage (2), an empennage (21, 22) and main wings (6) fixed to the fuselage (2); arranged similar to a conventional aircraft, but sized and positioned for vertical flight. A stator is positioned a minimal distance behind the propeller so as to compensate the torque caused by the propeller. The aircraft comprises high lift and high drag devices such as flaps (19) and a leading edge slat (7) on the main wings (6), and a fuselage spoiler (18). The positioning of the center of gravity (23) allows for a stable nose-up take-off and landing, NUTOL, position. The propeller generated airflow (PGA) over the main wings (6) and high lift and drag devices (7, 18, 19) creates lift and drag forces. Due to the NUTOL position, the sum of the propeller thrust, the lift forces and the drag forces on the aircraft results in a vertical force and no forward (horizontal) force, thus enabling vertical flight. Roll, pitch and yaw control is achieved by aerodynamic surfaces positioned inside and outside of the PGA.

Abstract translation: 本发明公开了一种能够垂直起飞和着陆的飞机。 飞机包括固定在机身（2）上的单个恒速可变螺距螺旋桨（3），机身（2），尾翼（21,22）和主翼（6）。 布置类似于常规飞机，但尺寸和定位用于垂直飞行。 定子位于螺旋桨后面的最小距离处，以补偿由螺旋桨引起的扭矩。 飞机包括高升力和高阻力装置，例如主翼（6）上的翼片（19）和前缘板条（7）以及机身扰流板（18）。 重心的定位（23）允许稳定的起飞和着陆，NUTOL的位置。 螺旋桨在主翼（6）上产生气流（PGA），高升力和拖曳装置（7,18,19）产生升力和牵引力。 由于NUTOL的位置，螺旋桨推力，提升力和飞机上的牵引力的总和导致垂直力并且没有向前（水平）的力，因此能够进行垂直飞行。 滚动，俯仰和偏航控制通过位于PGA内部和外部的空气动力学表面实现。

公开(公告)号：WO2004020278A1

公开(公告)日：2004-03-11

申请号：PCT/ES2003/000415

申请日：2003-08-08

Applicant: ROMERO VAZQUEZ, Juan José

Inventor： ROMERO VAZQUEZ, Juan José

IPC: B63H1/16

CPC classification number: F04D29/325 ,  B63H1/14 ,  B63H1/26 ,  B63H1/28 ,  B63H5/14 ,  B64C11/001 ,  B64C11/18 ,  B64C11/26

Abstract: La invención se refiere a una hélice que comprende una base (2, 15) y una pluralidad de palas (1, 14) que se extienden de dicha base de forma inclinada aguas arriba, es decir, en la dirección correspondiente a la dirección de marcha (D1) hacia delante de la nave. Las palas se extienden en una dirección que forma un ángulo agudo α con la dirección de marcha hacia delante, 10° ≤α≤80°. La invención también se refiere a un sistema de propulsión que incluye la hélice así como a una nave que incluye el sistema de propulsión.

Abstract translation: 本发明涉及一种螺旋桨，其包括基部（2,15）和从所述基部延伸出并且向上游移动（即沿着移动方向（D1））朝向容器前部倾斜的许多叶片（1,4） 。 上述刀片沿着与正向运动方向形成锐角α的轴线延伸，10°=α= 80°。 本发明还涉及一种包括螺旋桨和配备有所述推进系统的容器的推进系统。

公开(公告)号：WO2003014853A1

公开(公告)日：2003-02-20

申请号：PCT/CA2002/001224

申请日：2002-08-06

Applicant: ASHWORTH, Eric

Inventor： ASHWORTH, Eric

IPC: G05D7/00

CPC classification number: F04D25/166 ,  B63H1/14 ,  B63H1/16 ,  B63H1/28 ,  B63H5/08 ,  B64C11/001 ,  B64C11/46 ,  F04D25/02

Abstract: A fluid flow control mechanism is provided for linearizing a fluid flow. The mechanism includes a frame having a cylindrical outer baffle which rotatably supports a plurality of propeller elements thereon. Each propeller element defines a respective sweep area as the propeller element is rotated which overlaps sweep areas of adjacent propeller elements. The outer baffle circumscribes an outer periphery of the collective sweeps areas of the respective propeller elements. The propeller elements rotate in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow through the mechanism. Additional baffles and infills within the areas of non blade sweeps may be provided for particular applications of the mechanism. In various applications, linear forces of vector flow are formed by integrating curvature forces of tangential flow and economy flow systems are formed by integrating curvature forces potentials on the planes of rotating propellers to provide the emission and induction flow with an insulation whereby fluid in the immediate vicinity of the mobile flow remains in an undisturbed static state. This allows a fluid propulsion assembly to be fitted with an outer utility mantle in the static zone of the field.

Abstract translation: 提供流体流动控制机构用于使流体流线性化。 该机构包括具有可旋转地支撑多个螺旋桨元件的圆柱形外挡板的框架。 当螺旋桨元件旋转时，每个螺旋桨元件限定相应的扫掠区域，其与相邻螺旋桨元件的扫掠区域重叠。 外挡板限定各螺旋桨元件的集体扫掠区域的外周。 螺旋桨元件沿相同方向旋转，由此相邻螺旋桨元件的曲率流动力基本相互抵消，以使通过该机构的流体流动线性化。 在非叶片扫掠区域内的附加挡板和填充物可以用于该机构的特定应用。 在各种应用中，矢量流的线性力通过积分切向流的弯曲力而形成，经济流量系统是通过将旋转螺旋桨的平面上的弯曲力电位积分起来，以提供具有绝缘的排放和感应流而形成的， 移动流的附近保持静止状态。 这允许流体推进组件在现场的静态区域中装配外部实用地幔。

公开(公告)号：WO01058759A1

公开(公告)日：2001-08-16

申请号：PCT/GB2001/000473

申请日：2001-02-07

IPC: B64C11/00 ,  B64C39/10 ,  B64D27/10 ,  B64D27/12 ,  B64D27/14

CPC classification number: B64C11/001 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/10 ,  B64D27/12 ,  B64D27/14

Abstract: An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20). The support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced from the body or airframe of the aircraft.

Abstract translation: 发动机装置（14）包括燃气涡轮发动机单元（16）和第一和第二支撑构件（18,20）。 支撑构件（18,20）从发动机壳体（22）的结构部件（24）延伸，以将发动机单元支撑在与飞行器的主体或机身间隔开的位置。

公开(公告)号：WO01033084A1

公开(公告)日：2001-05-10

申请号：PCT/US2000/029664

申请日：2000-10-27

IPC: B64C11/00 ,  B64C11/48 ,  B64C27/20 ,  F04D1/14 ,  F15D1/00

CPC classification number: B64C11/001 ,  B64C11/48 ,  B64C27/20 ,  F04D1/14 ,  F15D1/00

Abstract: A vortex generating apparatus (60) has the capability of attracting and removably adhering one or more solid objects. The apparatus (60) comprises an impeller housed within a shell. The vortex attractor generates a vortical fluid flow (69a) generally in the form of a helical or spiral shaped flow. The fluid flow (69a) creates a low pressure region extending from the impeller end of the device. This low pressure region is contained by the walls of the fluid flow, thus directing the attractive forces toward a surface and minimizing effects of ambient fluid on the system. When the surface is part of a stationary object, wall, floor or ceiling, the vortex attractor may move toward and adhere to the surface. When the surface is part of a movable object, the vortex attractor may attract the object and maintain the attracted position.

Abstract translation: 涡流发生装置（60）具有吸引和可移除地粘附一个或多个固体物体的能力。 装置（60）包括容纳在壳体内的叶轮。 涡流吸引器产生通常为螺旋形或螺旋状流动形式的涡旋流体流（69a）。 流体流动（69a）产生从装置的叶轮端延伸的低压区域。 该低压区域被流体流动的壁容纳，从而将吸引力引导到表面并使环境流体对系统的影响最小化。 当表面是固定物体，墙壁，地板或天花板的一部分时，涡流吸引器可能向着表面移动并附着在表面上。 当表面是可移动物体的一部分时，涡流吸引器可以吸引物体并保持吸引位置。

公开(公告)号：WO2017146579A1

公开(公告)日：2017-08-31

申请号：PCT/NL2017/050116

申请日：2017-02-24

Applicant: TECHNISCHE UNIVERSITEIT DELFT

Inventor： VELDHUIS, Leonardus ,  VAN ARNHEM, Nando

IPC: B64C11/00 ,  B64D27/02

CPC classification number: B64C11/001 ,  B64C5/02 ,  B64C9/02 ,  B64C9/38 ,  B64C39/062 ,  B64C2003/445 ,  B64D27/02 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/66

Abstract: Airplane comprising a fuselage with an empennage, wherein the fuselage is provided with wings and comprises a propulsion system (6) with propellers, wherein the propulsion system is integrated with the aft-fuselage mounted empennage forming a propulsive empennage. The 'propulsive empennage' preferably comprises two ring wings (7), each forming a duct wherein each duct is provided with at least one propeller mounted in the duct. The two ring wings are mounted symmetrically on sides of the fuselage.

Abstract translation: 包括具有尾翼的机身的飞机，其中机身设置有机翼并且包括具有螺旋桨的推进系统（6），其中推进系统与安装在机身后部的尾翼集成，形成推进器 尾翼。 “推进尾翼”优选包括两个环形翼（7），每个形成一个管道，其中每个管道设有至少一个安装在管道中的螺旋桨。 两个环翼对称安装在机身两侧。

公开(公告)号：WO2016201556A1

公开(公告)日：2016-12-22

申请号：PCT/CA2016/050676

申请日：2016-06-13

Applicant: PLUIM, Jeff

Inventor： PLUIM, Jeff

IPC: F03G3/00 ,  B63H1/14 ,  B64C11/00 ,  B64D35/00 ,  B64G1/40

CPC classification number: B64C11/006 ,  B63H1/14 ,  B64C11/001 ,  B64G1/40 ,  F03G3/00

Abstract: This invention relates to propulsion systems. The Centrifugal Propeller is a dosed propulsion system with no external moving parts, other than a drive shaft, and has no external vents. The Centrifugal Propeller creates thrust by redirecting the reaction from centrifugal force so as to create directed thrust. The Centrifugal Propeller has significant advantages over other propulsion systems because it can be closed to the environment that it operates in. That means that it can operate in water, in air, or in outer space. It does not produce energy such as an electric motor but rather, converts that energy from a drive source such as an electric motor, into directed thrust. The invention's operation is not limited to closed environments. The Centrifugal Propeller will create thrust in any environment that its drive source will operate in. An electric motor can be completely closed to the environment it operates in and so would be the best source of power for the Centrifugal Propeller. Potential drive sources for the invention are: electric motors, internal combustion motors, turbines, and rockets. The Centrifugal Propeller will operate in outer space. An ideal match would be to use an electric motor running off of a nuclear generator, to turn the Centrifugal Propeller. In space the Centrifugal Propeller will continually accelerate and so space craft will have constant gravity while accelerating or decelerating. The Centrifugal Propeller will be used to propel and/or lift objects. It can be used to replace any current propulsion systems including but not limited to: cranes, jet engines, rocket engines, marine propellers and aircraft propellers.

Abstract translation: 本发明涉及推进系统。 离心螺旋桨是一种定量推进系统，除驱动轴之外没有外部移动部件，没有外部通风口。 离心螺旋桨通过将反作用力从离心力引导而产生推力，从而产生定向推力。 离心螺旋桨与其他推进系统相比具有显着的优势，因为它可以与其所在的环境接近，这意味着它可以在水，空气或外部空间中运行。 它不产生诸如电动机的能量，而是将来自诸如电动机的驱动源的能量转换成定向推力。 本发明的操作不限于封闭环境。 离心螺旋桨将在其驱动源运行的任何环境中产生推力。电动机可以完全关闭其运行的环境，因此将成为离心螺旋桨的最佳动力来源。 本发明的潜在驱动源是：电动机，内燃机，涡轮机和火箭。 离心螺旋桨将在外太空运行。 理想的搭配是使用从发电机运行的电动马达来转动离心螺旋桨。 在太空中，离心螺旋桨将不断加速，因此太空飞船在加速或减速时将具有恒定的重力。 离心螺旋桨将用于推进和/或提升物体。 它可用于替代目前的任何推进系统，包括但不限于：起重机，喷气发动机，火箭发动机，船用螺旋桨和飞机螺旋桨。

公开(公告)号：WO2016048785A1

公开(公告)日：2016-03-31

申请号：PCT/US2015/050672

申请日：2015-09-17

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： HALCOM, Lance ,  BASKIN, Bryan Kenneth

IPC: B64C11/02 ,  B64C27/10 ,  B64C27/20 ,  B64C27/30 ,  B64C27/82

CPC classification number: B64C11/001 ,  B64C11/02 ,  B64C27/10 ,  B64C27/20 ,  B64C27/30 ,  B64C27/82 ,  B64C2027/8236 ,  B64C2027/8254 ,  B64C2027/8272 ,  B64C2027/8281

Abstract: A diverter duct for a propeller includes a second duct element having a semi-annular wedge shape, which is pivotably coupled to the first duct element, a first drive structure configured to drive a pivoting of the second duct element relative to the first duct element and a second drive structure configured to drive a rotation of the first and second duct elements about an axis of rotation of the propeller.

Abstract translation: 用于推进器的分流管包括具有半环形楔形形状的第二管道元件，其可枢转地联接到第一管道元件，构造成驱动第二管道元件相对于第一管道元件枢转的第一驱动结构，以及 第二驱动结构，其构造成驱动所述第一和第二管道元件围绕所述螺旋桨的旋转轴的旋转。