公开(公告)号：US20040144893A1

公开(公告)日：2004-07-29

申请号：US10353660

申请日：2003-01-29

Inventor： Walter Dennis Clark

IPC: B64C001/00 ,  B64C003/00

CPC classification number: B64C1/0009 ,  B64C5/08 ,  B64C9/32 ,  B64C9/323 ,  B64C39/10 ,  B64C2001/0045 ,  B64C2039/105 ,  B64D7/00 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

Abstract: An aircraft comprises first and second wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface attached to an upper surface of the first wing, and a second forward opening control surface attached to an upper surface of the second wing, wherein each of the first and second hinges is canted with respect to a direction perpendicular to a longitudinal axis of the aircraft. A method of providing yaw control of an aircraft is also provided. The method comprises the steps of providing a first forward opening, canted spoiler in a top surface of a first wing of the aircraft, providing a second forward opening, canted spoiler in a top surface of a second wing of the aircraft, and operating the first and second spoilers differentially to create a yaw moment. The creation of yaw moments without any down force has application in sweptback wings where the tips are behind the center of gravity of the aircraft. The advantage is in reducing radar cross section over traditional (forward hinged, rearward opening) spoilers where there must be a spoiler on the bottom side to counter the down force created by the top spoiler.

Abstract translation: 飞机包括位于纵轴相对侧的第一和第二翼，附接到第一翼的上表面的第一向前开启控制表面和附接到第二翼的上表面的第二向前开启控制表面，其中 第一和第二铰链中的每一个相对于垂直于飞行器的纵向轴线的方向倾斜。 还提供了提供飞行器的偏航控制的方法。 该方法包括以下步骤：在飞行器的第一翼的顶表面中提供第一前进开口，倾斜扰流板，在飞行器的第二翼的顶表面中提供第二向前开口，倾斜扰流板，并操作第一 和第二扰流板差分地产生偏航力矩。 在没有任何向下的力的情况下创建偏航力矩可以应用在飞行器的翼部，其中尖端在飞行器的重心之后。 优点在于减少传统（前向铰链，向后开启）扰流板的雷达横截面，其中底部必须有扰流板，以抵抗由顶部扰流器产生的向下力。

公开(公告)号：US20030201367A1

公开(公告)日：2003-10-30

申请号：US10215733

申请日：2002-08-09

Inventor： Manuel Munoz Saiz

IPC: B64C021/04 ,  B64C003/00

CPC classification number: B64C23/00 ,  B64C2230/04 ,  B64C2230/20 ,  B64D2013/0622 ,  Y02T50/166 ,  Y02T50/56

Abstract: A process for the recovery of the energy from the air in pressurised areas of aircraft that involves linking or moving air from the pressurised areas to the lower areas of the fuselage or lower surfaces of the wings, the horizontal stabilisers, and other aerodynamic profiles, along ducting and/or by discharging through multiple slots or openings flowing downward and rearward with a small inclination against the direction of the air flow, to avoid turbulence. The pressure of the pressurised cabin air conditioning is used. In other cases, it is used the pressure produced at the front of the fuselage, on the leading edges of the wings, the horizontal stabiliser or other aerodynamic profiles. Lift is increased in all cases without further energy requirements.

Abstract translation: 一种从飞机加压区域的空气中回收能量的过程，包括将空气从加压区域连接或移动到机身的下部区域或机翼的下表面，水平稳定器和其他空气动力学特性 并且/或通过相对于空气流动的方向以小的倾斜向下和向后流动的多个槽或开口排出，以避免湍流。 使用加压舱室空调的压力。 在其他情况下，使用机身前部产生的压力，机翼前缘，水平稳定器或其他空气动力学特性。 在所有情况下，电梯的增加没有进一步的能源需求。

公开(公告)号：US20030197091A1

公开(公告)日：2003-10-23

申请号：US10447398

申请日：2003-05-29

Inventor： Manuel Munoz Saiz

IPC: B64C001/00 ,  B64C003/00

CPC classification number: B64C1/0009 ,  B64C39/10 ,  B64C2001/0045 ,  B64C2039/105

Abstract: The present invention is direct to an aircraft fuselage lift arrangement which includes an elongated vertically flattened oval cross section fuselage having a longitudinal axis; an upper longitudinal axis along the upper most portion of the fuselage and parallel to the longitudinal axis, a lower longitudinal axis parallel to the longitudinal axis and along the length of the bottom of the fuselage. The fuselage having a conical nose portion at one end and a conical tail portion at its opposite end. The nose portion of the fuselage having an upwardly inclined front wall extending upwardly from the bottom of the fuselage to at least the upper longitudinal axis of the fuselage. The tail portion of the fuselage having a downwardly declining rear wall extending from the upper longitudinal axis to the bottom of the fuselage. The fuselage also having a main landing gear.

Abstract translation: 本发明直接涉及具有纵向轴线的细长垂直扁平的椭圆形横截面机身的飞机机身升降装置， 沿着机身的最上部并且平行于纵向轴线的上纵向轴线，平行于纵向轴线并沿着机身底部的长度的下纵向轴线。 机身在一端具有锥形的鼻部，在其相对端具有锥形尾部。 机身的鼻部具有向上倾斜的前壁，其从机身的底部向上延伸至至少机身的上纵轴。 机身的尾部具有从上纵向轴线延伸到机身底部的向下延伸的后壁。 机身也有一个主起落架。

公开(公告)号：US20030192990A1

公开(公告)日：2003-10-16

申请号：US10175722

申请日：2002-06-20

Inventor： Craig B. Simpson ,  Mike Glen Allman ,  Steven Taylor Tuttle ,  Larry J. Ashton

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

CPC classification number: B64C3/20 ,  B29C37/0064 ,  B29C53/8016 ,  B29C53/8066 ,  B29C70/44 ,  B29C70/443 ,  B29C70/543 ,  B29C70/546 ,  B29L2031/3085 ,  B64C3/24 ,  Y02T50/43 ,  Y10S264/904

Abstract: A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame.

Abstract translation: 公开了单件共固化复合翼。 机翼有飞行表面和结构构件。 在一个实施例中，结构构件可以是多个翼梁。 翼梁可以具有各种形状以增加屈曲强度。 翼梁可以是波形，例如正弦形状。 飞行表面和结构构件共同固化以形成单件，整体翼结构。 还公开了用于制造单件共固化翼的方法。 该方法可以包括为机翼的飞行表面布置复合片材。 然后，翼片的复合材料围绕多个可加压的形式布置。 最后，复合材料在蛤壳框架中固化。

公开(公告)号：US20030192985A1

公开(公告)日：2003-10-16

申请号：US10408981

申请日：2003-04-08

Inventor： Jay Lipeles

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

CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为一个小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

公开(公告)号：US20030001045A1

公开(公告)日：2003-01-02

申请号：US09895332

申请日：2001-07-02

Applicant: ELSE Ltd.

Inventor： Aharon Yifrach

IPC: B64C003/00

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

公开(公告)号：US20040135032A1

公开(公告)日：2004-07-15

申请号：US10175612

申请日：2002-06-20

Inventor： Robert D. Gregg III ,  John Charles Vassberg ,  David M. Pitera

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

CPC classification number: B64C3/14 ,  B64C3/10 ,  B64C2003/147 ,  Y02T50/12

Abstract: A method for forming a trailing edge wedge for a wing wherein the size and configuration of a trailing edge wedge at various points along the span of the trailing edge wedge are adjusted and analyzed in an iterative manner to form an improved trailing edge wedge. An improved wing assembly is also provided.

Abstract translation: 一种用于形成用于机翼的后缘楔块的方法，其中沿着后缘楔形跨度的不同点处的后缘楔块的尺寸和构造被以迭代方式进行调整和分析以形成改进的后缘楔形件。 还提供了改进的翼组件。

公开(公告)号：US20040129829A1

公开(公告)日：2004-07-08

申请号：US10302759

申请日：2002-11-22

Inventor： Michael Hoerle ,  Lawrence L. Micek ,  Donald T. Ireland

IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00 ,  B64C007/00

CPC classification number: B01F15/0416 ,  B01F5/0618 ,  B01F7/00908 ,  B01F13/0035 ,  C09K3/18 ,  C09K3/185

Abstract: An apparatus and method for preparing and dispensing a liquid deicer is disclosed. The apparatus and method allow deicer ingredients or precursors to be combined in an exothermic reaction to produce a heated deicer at the location where it will be used. In one implementation, potassium hydroxide and acetic acid are combined using the apparatus and method to make hot potassium acetate for use in numerous deicer applications, including deicing of airport runways.

Abstract translation: 公开了一种用于制备和分配液体除冰器的设备和方法。 该设备和方法允许除冰成分或前体在放热反应中组合以在其将被使用的位置产生加热的除冰机。 在一个实施方案中，使用装置和方法将氢氧化钾和乙酸混合以制备热的乙酸钾，用于许多除冰机应用，包括机场跑道除冰。

公开(公告)号：US20040079840A1

公开(公告)日：2004-04-29

申请号：US10674367

申请日：2003-09-30

Inventor： William D. Armstrong ,  William R. Lindberg ,  Jonathan W. Naughton ,  John E. McInroy

IPC: B64C003/00 ,  B64C005/00

CPC classification number: B64C23/005 ,  B64C2230/02 ,  Y02T50/166 ,  Y02T50/44

Abstract: An aircraft lift control system mounted on an aircraft is provided. The aircraft has at least one wing. The aircraft lift control system comprises an oscillating aero surface mounted to the aircraft wing. A resonant frame is connected to the oscillating aero surface. An actuator is mounted to the resonant frame wherein the sinusoidal force produced by the actuator on the resonant frame results in a resonant deformation in the resonant frame and resonant-sinusoidal displacement of the aero-surface.

Abstract translation: 提供安装在飞机上的飞机升降机控制系统。 飞机至少有一个翼。 飞机升降机控制系统包括安装到飞行器机翼的振荡空气表面。 谐振框架连接到振荡空气表面。 致动器安装到谐振框架，其中由谐振框架上的致动器产生的正弦力导致谐振框架中的谐振变形和空气表面的谐振正弦位移。

公开(公告)号：US20040021041A1

公开(公告)日：2004-02-05

申请号：US10464160

申请日：2003-06-18

Inventor： Kenneth R. Grossman ,  Bohdan Z. Cybyk ,  David M. VanWie

IPC: B64C021/04 ,  B64C003/00

CPC classification number: F15C1/006 ,  B64C21/04 ,  F15C1/14 ,  Y02T50/166

Abstract: The Spark Jet can manipulate high-speed flows without moving aerodynamic structures and generates exhaust streams that can penetrate supersonic (as well as subsonic) boundary layers without the need for active mechanical components. The Spark Jet comprises a chamber with embedded electrodes and a discharging orifice. High-chamber pressure may be generated by rapidly heating the gas inside SparkJet using an electrical or other useful discharge. The pressure may be relieved by exhausting the heated air though an orifice.

Abstract translation: Spark Jet可以在不移动空气动力学结构的情况下操纵高速流，并产生可以渗透超音速（以及亚音速）边界层的排气流，而不需要主动的机械部件。 火花喷气机包括具有嵌入电极和排放孔的腔室。 通过使用电气或其他有用的排放物快速加热SparkJet内部的气体可能会产生高室压力。 压缩可以通过通过孔口排出加热的空气来减轻。