公开(公告)号：US09783291B2

公开(公告)日：2017-10-10

申请号：US14689443

申请日：2015-04-17

申请人： Propulsive Wing, LLC

发明人： Joseph Kummer ,  Jimmie B. Allred, III

IPC分类号： B64C17/00 ,  B64C29/00 ,  B64C39/02 ,  B64C39/10

CPC分类号： B64C29/0025 ,  B64C29/0066 ,  B64C29/0083 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  Y02T50/12

摘要： A hybrid axial/cross-flow fan aerial vehicle includes both axial and cross-flow fan propulsion for efficient hover and forward flight performance. The axial fans provide primarily vertical thrust, while the cross-flow fan provides horizontal, as well as vertical, thrust. The vehicle takes off vertically, is capable of hover, and can fly forward by vectoring the thrust of the cross-flow fan system. This approach provides large internal cargo capacity and high forward flight speeds.

公开(公告)号：US09764819B2

公开(公告)日：2017-09-19

申请号：US14838297

申请日：2015-08-27

申请人： AeroVironment Inc.

发明人： Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

IPC分类号： B64C3/38 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C17/00 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  H04B7/185

CPC分类号： B64C3/38 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C17/00 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55

摘要： A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

公开(公告)号：US20170247100A1

公开(公告)日：2017-08-31

申请号：US15441510

申请日：2017-02-24

申请人： Airbus Operations SAS

发明人： Olivier Cazals ,  Jaime GENTY DE LA SAGNE

IPC分类号： B64C1/14 ,  B64C1/24 ,  B64D27/14 ,  B64C39/10

CPC分类号： B64C1/1423 ,  B64C1/143 ,  B64C1/24 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/14 ,  Y02T50/12

摘要： An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is outside a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall. This aircraft has optimum aerodynamic performance and the circulation of passengers between the pressurized housing and the exterior of the aircraft may be fluid.

公开(公告)号：US20170158309A1

公开(公告)日：2017-06-08

申请号：US15232510

申请日：2016-08-09

申请人： Advanced Product Development, LLC

发明人： William Randall McDonnell

IPC分类号： B64C3/10 ,  B64C39/10

CPC分类号： B64C3/10 ,  B64C30/00 ,  B64C39/10 ,  B64C2039/105 ,  Y02T50/12

摘要： An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft.

公开(公告)号：US09296477B1

公开(公告)日：2016-03-29

申请号：US14121022

申请日：2014-07-21

申请人： Glenn Coburn

发明人： Glenn Coburn

IPC分类号： B64C27/08 ,  B64C27/46 ,  B64C27/14 ,  B64C1/00 ,  B64D35/00 ,  B64C27/54 ,  B64C39/10

CPC分类号： B64C27/08 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64D35/04

摘要： A helicopter system has multiple rotors and methods of operation. The helicopter has a fuselage with four rotors and an engine operably connected to the four rotors for powered rotation of a rotor shaft with a set of rotor blades attached for each of the four rotors. Each of the rotor shafts is positioned in a housing with each housing attached at a lower end to a distal end of a beam with beams attached at a proximal end on the right side and on the left side adjacent to the nose end of the fuselage, and on the right side and on the left side adjacent to the tail end of the fuselage. All four rotor shafts are inclined from a lower end to an upper end toward the fuselage. All four rotor shafts may be inclined toward the nose end or the tail end of the fuselage.

摘要翻译： 直升机系统具有多个转子和操作方法。 直升机具有四个转子的机身和可操作地连接到四个转子的发动机，用于转子轴的动力旋转，一组转子叶片连接到四个转子中的每一个。 每个转子轴定位在壳体中，每个壳体在下端附接到梁的远端，梁的远端附近在靠近机身的鼻端的右侧和左侧， 并在靠近机身尾端的右侧和左侧。 所有四个转子轴从下端倾斜到上端朝向机身。 所有四个转子轴可以朝着机身的鼻端或尾端倾斜。

公开(公告)号：US08915467B2

公开(公告)日：2014-12-23

申请号：US13381190

申请日：2010-07-05

申请人： Roddam Narasimha ,  Suresh Madhusudan Deshpande ,  Chandrashekarappa Praveen ,  Belur Raghavan Rakshith

发明人： Roddam Narasimha ,  Suresh Madhusudan Deshpande ,  Chandrashekarappa Praveen ,  Belur Raghavan Rakshith

IPC分类号： B64C39/10 ,  B64C3/00

CPC分类号： B64C3/00 ,  B64C39/10 ,  Y02T50/12

摘要： The disclosure relates to Aeronautics, more particularly relating to wing planforms that reduce wing drag substantially in aircraft driven by propellers or other rotors in tractor configuration. An aircraft comprising a wing and propeller system (1), said system comprising wing planform (2) characterized into wing chord regions (3) behind each propeller/rotor (5) whose length is relatively varied with respect to length of wing chord regions (4) at outboard of the propeller/rotor (5) towards wing tip and/or at inboard of the propeller (5) towards fuselage, and plurality of propellers (5) fixed ahead of wing leading edge such that induced drag is reduced by exploiting the velocity field generated by the slipstream of the propeller (5). Also, provides for a method of optimizing wing and propeller system and a method reducing induced drag, among other possible parameters of interest.

摘要翻译： 本公开涉及航空，更具体地涉及机翼平面图，其能够在拖拉机构造中由推进器或其它转子驱动的飞机基本上减少机翼阻力。 一种包括翼和螺旋桨系统（1）的飞行器，所述系统包括机翼平台（2），其特征在于在每个螺旋桨/转子（5）后面的翼弦区域（3），其长度相对于翼弦区域的长度相对变化 4）在推进器/转子（5）的外侧朝向翼尖和/或在螺旋桨（5）的内侧朝向机身，以及多个螺旋桨（5）固定在机翼前缘之前，从而通过利用 由螺旋桨（5）的滑流产生的速度场。 此外，还提供了优化翼和螺旋桨系统的方法以及减少诱导阻力的方法以及感兴趣的其它可能的参数。

公开(公告)号：US20140231593A1

公开(公告)日：2014-08-21

申请号：US14205156

申请日：2014-03-11

申请人： Abe Karem

发明人： Abe Karem

IPC分类号： B64C1/00 ,  B64D37/00 ,  B64C39/10 ,  B64C39/02 ,  B64C3/56 ,  B64C1/06

CPC分类号： B64C39/10 ,  B64C1/00 ,  B64C1/0009 ,  B64C1/061 ,  B64C1/065 ,  B64C1/26 ,  B64C3/56 ,  B64C25/10 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/126 ,  B64C2211/00 ,  B64D37/00 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/43

摘要： A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

摘要翻译： 飞行可操作的，真正模块化的飞机具有飞行器核心，一个或多个外翼构件，机身，驾驶舱，前后联轴器，尾翼和尾翼部分可在其运行寿命期间可拆卸地联接和/或更换 的飞机。 在优选实施例中，飞机核心容纳推进发动机，航空电子设备，至少80％的燃料和所有起落架。 飞机核心优选地构造有弯曲的前向和后部复合翼梁，其在中心部分处传递载荷，同时容纳中翼构造。 飞机核心优选地具有大的中心空间，其大小可互换地携带军械发射器，监视有效载荷，电子对抗措施和其他类型的货物。 考虑的飞机可能相当大，例如具有至少80英尺的翼展。

公开(公告)号：US08602348B2

公开(公告)日：2013-12-10

申请号：US12865429

申请日：2009-02-02

申请人： Ashley Christopher Bryant

发明人： Ashley Christopher Bryant

IPC分类号： B64C15/12 ,  B64C29/00 ,  B64C39/10

CPC分类号： B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

摘要： A vertical take-off and landing flying-wing aircraft has a pair of thrust-vectoring propulsion units mounted fore and aft of the aircraft pitch axis on strakes at opposite extremities of the wing-structure, with the fore unit below, and the aft unit above, the wing-structure. The propulsion units are pivoted to the strakes, either directly or via arms, for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms are employed, the arms of fore and aft propulsion units are intercoupled via chain drives or linkages. The wing-structure may have fins, slats and flaps and other aerodynamic control-surfaces, and enlarged strakes may incorporate rudder surfaces. Only one propulsion unit may be mounted at each extremity and additional fan units may be used.

摘要翻译： 垂直起飞和着陆的飞翼飞机具有一对推力矢量推进装置，其在机翼结构的相对两端的前翼和后部单元的前后悬架的飞机俯仰轴上前后安装 以上，翼结构。 推进单元直接或经由臂枢转到斜面，用于单独的角位移，用于以偏航，俯仰和滚动以及用于悬停和向前和向后飞行的推力向导操纵飞行器。 当使用武器时，前后推进单元的臂通过链条驱动器或连杆相互联接。 机翼结构可以具有翅片，板条和翼片以及其它空气动力学控制表面，并且扩大的履带可以包括舵面。 每个末端只能安装一个推进装置，也可以使用额外的风扇装置。

公开(公告)号：US08191820B1

公开(公告)日：2012-06-05

申请号：US12001218

申请日：2007-12-11

申请人： Bryan Wayne Westra ,  Roxanne Marie Sato ,  Douglas Ellwood Shultz ,  James Franklin Kerswell ,  Perry Bruce Petersen ,  Scott Walter Collins

发明人： Bryan Wayne Westra ,  Roxanne Marie Sato ,  Douglas Ellwood Shultz ,  James Franklin Kerswell ,  Perry Bruce Petersen ,  Scott Walter Collins

IPC分类号： B64C39/10 ,  B64C5/04 ,  B64C5/12 ,  B64C21/04

CPC分类号： B64C39/10 ,  B64C5/12 ,  B64C9/12 ,  B64C21/04 ,  B64C21/08 ,  B64C39/12 ,  B64D27/20 ,  Y02T50/166

摘要： The invention is an aircraft that includes a flying wing having a plurality of extendable flaps mounted on the trailing edge of the flying wing. A canard is mounted on the nose of said flying wing. A system is mounted in the flying wing for providing high pressure air over the canard and the flaps. A second system is provided for controlling the flow of air over the canard to provide pitch control of the aircraft.

摘要翻译： 本发明是一种飞行器，其包括具有安装在飞翼的后缘上的多个可延伸翼片的飞翼。 鸭子安装在飞行翼的鼻子上。 系统安装在飞翼中，用于在鸭舌和襟翼上提供高压空气。 提供了一种第二系统，用于控制在鸭子上的空气流动，以提供飞行器的俯仰控制。

公开(公告)号：US20050258306A1

公开(公告)日：2005-11-24

申请号：US10853299

申请日：2004-05-24

申请人： Edward Barocela ,  Patrick Cassidy

发明人： Edward Barocela ,  Patrick Cassidy

IPC分类号： B64B1/20 ,  B64C39/10 ,  B64D27/24

CPC分类号： B64C39/10 ,  B64B2201/00 ,  B64D27/24 ,  B64D2211/00 ,  Y02T50/55 ,  Y02T50/64 ,  Y10S244/901

摘要： In one aspect, a hybrid airship including an outer shell, a plurality of helium filled gas envelopes, and an all-electric propulsion system may have the shape of a delta-wing. In some embodiments, the hybrid airship may be launched using buoyancy lift alone and aerodynamic lift may be provided by the all-electric propulsion system. In one aspect, a photovoltaic array and a high energy density power storage system may be combined to power the propulsion system making the propulsion system regenerative. The delta-wing shape can provide a surface area large enough to accommodate very large circular or elliptical transmission devices. By continuously recharging the power storage system, the hybrid airship in accordance with some embodiments can stay aloft at an operational altitude of at least about 85,000 ft for months or even years. The hybrid airship may function as an airborne military communications relay platform.

摘要翻译： 一方面，包括外壳，多个氦气填充的气体包络和全电动推进系统的混合式飞艇可以具有三角翼的形状。 在一些实施例中，混合式飞艇可以单独使用浮力提升机来启动，而空气动力提升可由全电动推进系统提供。 在一个方面，光伏阵列和高能量密度功率存储系统可以组合起来，为推进系统提供动力，使推进系统再生。 三角翼形状可以提供足够大的表面积以适应非常大的圆形或椭圆形传输装置。 通过不断地对蓄电系统充电，根据一些实施例的混合式飞艇可以在至少约85,000英尺的操作高度上保持高度数月甚至数年。 混合型飞艇可以作为空中军事通信中继平台。