公开(公告)号：US20030085319A1

公开(公告)日：2003-05-08

申请号：US10242036

申请日：2002-09-11

发明人： Joseph Wagner ,  Anthony Pruszenski JR. ,  Karl F. Milde JR.

IPC分类号： B64C015/02 ,  B64C029/00

CPC分类号： B64C3/56 ,  B64C27/20 ,  B64C29/0025 ,  Y02T50/14

摘要： A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a nulllevitatornull which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

摘要翻译： 能够垂直起飞和着陆（VTOL）的个人飞机（PAC）包括一个固定翼和一个具有前，后和两侧的乘客舱的机身，以及多个独立动力的推进器，最好集成到 机翼，在机身的每一侧。 飞机具有等于或大于2的提升阻力比。作为能够向飞行器提供垂直向上的力的导风扇单元的推进器具有这样的冗余度，即飞行器可以在一个推进器上无法操作 机身的每一边。 机体每一侧至少有一个推进器最好包括一个“升降机”，它从翼型空气入口以及空气从入口到出口的加速度产生升力。

公开(公告)号：US06536714B2

公开(公告)日：2003-03-25

申请号：US09837637

申请日：2001-04-17

申请人： Wolfgang Gleine ,  Knut Mau ,  Udo Carl

发明人： Wolfgang Gleine ,  Knut Mau ,  Udo Carl

IPC分类号： B64C344

CPC分类号： B64C9/24 ,  B64C3/46 ,  Y02T50/14 ,  Y02T50/32

摘要： An elastically expandable hollow displacement element is secured to the rear surface of an aircraft wing slat. When the displacement element is contracted, the slat may be retracted onto the wing's leading edge. When the slat is extended, the displacement element is expanded to protrude convexly from the slat, thereby preventing vortex formation in the slat air gap and reducing aero-acoustic noise. A pressure control system for inflating and deflating the displacement element includes a bleed air line connected from the aircraft engine bleed air system to the displacement element, a shut-off valve and a pressure control valve interposed in series in the bleed air line, and a slat contour controller connected by respective signal lines to the valves, which control the quantity and the pressure of the bleed air supplied into the displacement element, for properly inflating the same.

公开(公告)号：US06536711B1

公开(公告)日：2003-03-25

申请号：US09965310

申请日：2001-09-27

申请人： George Louis Conway, Jr. ,  Kendall G. Young ,  Ron L. Stroud

发明人： George Louis Conway, Jr. ,  Kendall G. Young ,  Ron L. Stroud

IPC分类号： B64D106

CPC分类号： B64C7/00 ,  B64C3/48 ,  B64D1/06 ,  Y02T50/14

摘要： A conformal aircraft bay having a single aperture or gap formed by doors with abutting edge portions being located side-by-side while the doors are in a closed position, the doors are structured to open to access the bay with the abutting edge portions moving apart from each other, and each door having an elastomeric transition closing the gaps between the abutting edge portions when the doors are closed.

摘要翻译： 具有由具有邻接边缘部分的门形成的单个孔或间隙的保形飞机舱在门处于关闭位置时并排定位，门被构造成打开以接近隔间，邻接边缘部分分开 并且每个门具有弹性体过渡，当门关闭时，关闭在邻接边缘部分之间的间隙。

公开(公告)号：US20020134888A1

公开(公告)日：2002-09-26

申请号：US09816185

申请日：2001-03-26

发明人： Allison Earl Hall

IPC分类号： B64C001/00 ,  B64C003/00 ,  B64C005/00

CPC分类号： B64C3/50 ,  Y02T50/14

摘要： The invention lies in the field of fluid dynamics. In particular, the invention pertains to aircraft airfoils and wing designs. The variable airfoil wing is a simple concept which divides an aircraft wing into a forward segment and a rearward segment. The wing forward segment is fixed and the wing rearward segment is movable. Using a symmetrical airfoil design as the base wing shape, the rearward segment is rotated downward to increase the wing camber. When utilized in accordance with specific limitations, the wing design offers a broad range of aerodynamic capabilities.

摘要翻译： 本发明在于流体动力学领域。 特别地，本发明涉及飞机翼型和机翼设计。 可变翼型翼是一种将飞机机翼分成前段和后段的简单概念。 机翼前段固定，后翼段可移动。 使用对称的翼型设计作为基座翼形，向后的部分向下旋转以增加机翼弧度。 当根据具体限制使用时，机翼设计提供了广泛的空气动力学能力。

公开(公告)号：US06398157B1

公开(公告)日：2002-06-04

申请号：US09737825

申请日：2000-12-18

申请人： David Barry Ingram

发明人： David Barry Ingram

IPC分类号： B64C2722

CPC分类号： B64C29/02 ,  B64C3/40 ,  Y02T50/14

摘要： An aircraft capable of vertical take off and normal cruise flight has a fuselage and a pair of wings, the wings being movable relative to the fuselage from a rearwardly swept position to which the wings are moved for vertical take off, to a spread position to which the wings are moved for normal cruise flight.

摘要翻译： 能够垂直起飞和正常巡航飞行的飞机具有机身和一对机翼，所述机翼相对于机身可以从向后移动的位置移动以使机翼移动到垂直起飞位置到达扩展位置 机翼被移动以进行正常的巡航飞行。

公开(公告)号：US20020005461A1

公开(公告)日：2002-01-17

申请号：US09764032

申请日：2001-01-17

发明人： James E. Nettle ,  James R. Lord

IPC分类号： B64C003/50

CPC分类号： B64C3/48 ,  B64C9/16 ,  B64C9/20 ,  Y02T50/14 ,  Y02T50/32

摘要： A method and means are provided for increasing the aerodynamic efficiency of an airfoil employed by an aircraft. The method utilizes the primary flight control surfaces (11) (12) contiguous to the airfoil's trailing edge and relocates these devices to novel positions (21) (23) resulting in an expanded cord and enhanced camber for the aircraft wing (13). Self-adjusting push-pull rods (25) (60) replace conventional solid rods (24) where necessary in combination with a re-rigging of the flight control surfaces (11) (12) to predetermined positions (21) (23). Any voids created by this modification between the shared upper and lower fluid flow surfaces of the aircraft wing (13) and its flight control surfaces (11) (12) are eliminated through the installation of appropriate structure (40) or seal (43). Thus the aircraft wing (13) retains a unique geometric profile as a usual configuration.

摘要翻译： 提供了一种用于提高飞机使用的翼型件的空气动力学效率的方法和装置。 该方法利用与翼型件的后缘相邻的主飞行控制表面（11）（12）并将这些装置重新定位到新的位置（21）（23），导致用于飞行器机翼（13）的扩展的绳索和增强的弯度。 自调节推拉杆（25）（60）在必要时将常规实心杆（24）替换为将飞行控制表面（11）（12）重新安装到预定位置（21）（23）上。 通过安装适当的结构（40）或密封件（43），可以消除在飞行器机翼（13）及其飞行控制表面（11）（12）的共享的上部和下部流体流动表面之间通过这种修改产生的任何空隙。 因此，飞机机翼（13）保持独特的几何轮廓作为通常的配置。

公开(公告)号：US06328265B1

公开(公告)日：2001-12-11

申请号：US09318115

申请日：1999-05-25

申请人： Faruk Dizdarevic

发明人： Faruk Dizdarevic

IPC分类号： B64C350

CPC分类号： B64C3/50 ,  B64C9/28 ,  B64C9/32 ,  B64C9/323 ,  Y02T50/14 ,  Y02T50/32

摘要： A slot forming segment is inserted between two portions of a wing, which are adjacent along a longitudinal axis of wing, into a cove of a carved trailing edge of a leading portion of the adjacent portions and pivotal relatively to both adjacent portions of the wing between which it is inserted. The slot forming segment has such a shape and a position of its axis of rotation that by deflecting it downwardly relatively to the leading portion, it is formed a slot inside the wing's structure of large inlet cross section and high convergence ratio for the control of the boundary layer over an upper surface of the wing behind the slot forming segment for the need of extra lift production. Simultaneously, it is increased both a camber and an aerodynamic surface area of a following portion of the adjacent portions whereby additionally increasing the extra lift production on the wing. A slot changing spoiler is inserted directly in front of and above the slot forming segment and has such a shape of its undersurface and a position of its axis of rotation that a camber of an upper surface of the wing and the convergence ratio of the slot is changed by the simultaneous rotation of the slot changing spoiler and the slot forming segment in the opposite direction whereby increasing the rate of change of lift on the wing for the efficient maneuver of an aircraft at low speeds of flight.

摘要翻译： 狭缝形成段被插入在翼的两个部分之间，这两个部分沿着翼的纵向轴线相邻，相邻部分的前部的雕刻后缘的轮廓相对于翼的两个相邻部分枢转， 它被插入。 槽形成段具有其旋转轴线的形状和位置，通过使其相对于前端部向下偏转，其在机翼结构内形成有较大入口截面的狭槽，并且具有高收敛比，用于控制 边界层位于槽形成段后面的翼的上表面上，用于需要额外的升力生产。 同时，增加相邻部分的后续部分的弯度和空气动力学表面积，这另外增加了机翼上的额外的升力产生。 狭缝变换扰流板直接插入槽形成段的前方和上方，并具有其下表面的形状和其旋转轴线的位置，即机翼上表面的弯度和槽的收敛比为 改变了槽位变换扰流板和槽形成段在相反方向的同时旋转，从而增加机翼上的升力改变率，以便在低速飞行时有效地操纵飞行器。

公开(公告)号：US06286789B1

公开(公告)日：2001-09-11

申请号：US09496138

申请日：2000-02-01

申请人： Ralph Shimovetz

发明人： Ralph Shimovetz

IPC分类号： B64C900

CPC分类号： F42B15/01 ,  B64C3/54 ,  F42B10/02 ,  F42B10/64 ,  Y02T50/14

摘要： A configurable aerial vehicle aerosurface is disclosed, The configurable aerial vehicle aerosurface includes first and second airfoil surfaces in sliding engagement. A plurality of apertures pass transversely through the airfoil surfaces and are disposed in such a relationship so as to define a first position wherein the apertures are in substantial alignment and a second position wherein the apertures are in substantial non-alignment. In this way, the configurable aerial vehicle aerosurface of the present invention can be configured from a first, low drag transport position, to a second, aerodynamic position to provide missile lift and control.

摘要翻译： 公开了一种可配置的飞行器气体表面。可配置的飞行器气体表面包括滑动接合的第一和第二翼面。 多个孔穿过翼型表面横向通过并且以这样的关系设置，以便限定第一位置，其中孔基本对齐，而第二位置其中孔几乎不对齐。 以这种方式，本发明的可配置的飞行器气体表面可以由第一，低阻力输送位置，第二空气动力学位置构成，以提供导弹升降和控制。

公开(公告)号：US20190202543A1

公开(公告)日：2019-07-04

申请号：US16297126

申请日：2019-03-08

申请人： Brunel University London

发明人： Alvin Gatto

IPC分类号： B64C3/52 ,  B64C3/18 ,  B64C13/40 ,  F03D1/06

CPC分类号： B64C3/52 ,  B64C3/187 ,  B64C3/48 ,  B64C13/40 ,  B64C2003/445 ,  B64C2003/543 ,  F01D5/00 ,  F03D1/0633 ,  F03D1/0675 ,  F05B2240/31 ,  F05B2250/02 ,  Y02T50/14

摘要： A blade or wing element includes a plurality of ribs (20) rotatable and/or slidable with respect to one another whereby to vary the aerodynamic configuration of the blade or wing element by causing a twist thereof. A blade or wing or blade or wing assembly, including such a blade or wing element is disclosed, as well as an aerodynamic apparatus such as an aircraft, or a wind turbine. A method of assembling a blade or wing element is also disclosed.

公开(公告)号：US20180273169A1

公开(公告)日：2018-09-27

申请号：US15990610

申请日：2018-05-26

申请人： Bell Helicopter Textron Inc.

发明人： Steven Ray Ivans ,  Nathan Gabriel Wu

IPC分类号： B64C29/00 ,  B64C7/02 ,  B64C11/00 ,  B64C3/38

CPC分类号： B64C29/0033 ,  B64C3/38 ,  B64C5/08 ,  B64C7/02 ,  B64C27/28 ,  B64C29/02 ,  Y02T50/14

摘要： A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.