公开(公告)号：US20100252674A1

公开(公告)日：2010-10-07

申请号：US11653729

申请日：2007-01-16

申请人： James D. Lang

发明人： James D. Lang

IPC分类号： B64C3/50 ,  B64C3/00 ,  G06F19/00 ,  B64C39/10 ,  B64C21/00

CPC分类号： B64C23/06 ,  B64C19/00 ,  G05D1/0653 ,  Y02T50/162

摘要： Runway length requirement for take-off and landing of an aircraft is reduced by taking advantage of dynamic lift overshoot, and in some cases, dynamic stall. In take-off and landing, the angle of attack is rapidly increased so that the lift coefficient exceeds the maximum predicted by the steady flow lift curve. By increasing the angle of attack at an appropriate rate, the increased lift coefficient can be maintained, without loss of control, until the aircraft touches down in the case of a landing, or until the aircraft can begin a normal climb, in the case of take-off. A low aspect ratio lifting body is preferred because of its more gradual stall behavior, and the potential to use dynamic stall for further deceleration before touchdown. Vortex fences can be oscillated to delay the onset of stall, and, in cruise, to energize the boundary-layer and reduce drag and/or control roll and/or yaw.

摘要翻译： 通过利用动力升降过冲减少飞机起飞和降落的跑道长度要求，在某些情况下，动态停止。 起飞和着陆时，攻角迅速增加，使得升力系数超过稳定流量提升曲线预测的最大值。 通过以适当的速率增加迎角，可以保持增加的升力系数，而不会失控，直到在着陆的情况下飞机接触下来，或直到飞机开始正常爬升为止 脱掉。 低纵横比提升体是优选的，因为它具有更加缓慢的失速行为，以及在达阵之前使用动态失速进一步减速的可能性。 涡流围栏可以振荡以延迟失速的开始，并且在巡航中，激励边界层并减少拖动和/或控制滚动和/或偏航。

公开(公告)号：US20100243795A1

公开(公告)日：2010-09-30

申请号：US12675165

申请日：2008-08-29

申请人： William R McDonnell

发明人： William R McDonnell

IPC分类号： B64C39/10 ,  B64C3/00 ,  B64C17/10

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

摘要： An oblique wing aircraft (1) designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment (27) on one side of the wing and an aft swept wing segment (29) on the opposite side of the wing. A center oblique airfoil section (25) 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. The center oblique airfoil section is not shaped solely to function as a circular fairing to fill the gap between an oblique wing and a fuselage at different oblique wing angles, nor is it a second wing in an X wing configuration. Preferably, the aircraft is an all-wing aircraft.

摘要翻译： 斜翼飞机（1）设计用于减小表面积与体积比。 飞机具有斜翼，其包括在机翼的一侧上的向前扫掠翼段（27）和在翼的相对侧上的后扫掠翼段（29）。 中心斜翼部分（25）连接前掠翼部和后掠翼部。 中心斜翼型部分的中心线附近的弦杆比前方或后掠翼段的和弦更大。 中心倾斜翼型部分的和弦比前翼或后翼部分的下降更快，因为中心倾斜翼型部分朝向前后扫掠的翼部向外延伸。 中心斜翼型部分的形状不仅仅是作为圆形整流罩，以不同的倾斜翼角填充斜翼和机身之间的间隙，也不是X翼构型中的第二翼。 飞机最好是全翼飞机。

公开(公告)号：US20100187352A1

公开(公告)日：2010-07-29

申请号：US12526784

申请日：2008-01-29

申请人： Michael Yavilevich

发明人： Michael Yavilevich

IPC分类号： B64C3/00 ,  B64D11/06 ,  B64D47/00 ,  B64D37/04 ,  B64C1/22 ,  B64D45/00 ,  B64D13/02 ,  B64C1/06

CPC分类号： B64C1/061 ,  B64C1/062 ,  B64C2001/0027 ,  B64C2001/0036 ,  B64C2001/0072 ,  B64D9/00 ,  B64D11/00 ,  B64D37/04 ,  Y02T50/43 ,  Y02T50/44 ,  Y02T50/46

摘要： The invention relates to multi deck passenger aircraft, having passenger cabins and/or service facilities arranged on the upper and lower deck and inner load bearing cell structure provided within aircraft body. The present invention is also directed toward methods for manufacturing derivative multi deck aircrafts. Energy absorbing, floatable cargo containers (24) attached to fuselage belly. External fuel tanks (26) displaced on the top of fuselage. Center wing region of the fuselage is using for arranging rows of seats and service facilities. Addition seating configuration for narrow and wide bodied aircraft is provided. Multi deck seating configuration significantly reduces per passenger operating cost over existing technology. Less fuel per passenger is required since there is less airframe weight and wetted area per passenger. Due to the lower overall cost per passenger seat within the multi deck seating structure, the net profit and return on investment in the aircraft are also increased.

摘要翻译： 本发明涉及多层乘客机，其具有布置在飞机机体内的上下甲板和内承重单元结构的客舱和/或服务设施。 本发明还涉及制造衍生多层飞机的方法。 能量吸收，可浮动的货物集装箱（24），附在机身的腹部。 外部燃料箱（26）在机身顶部移动。 机身的中心翼区域用于排列座椅和服务设施。 提供了狭窄和宽体积飞机的增加座椅配置。 多层座椅配置大大降低了乘客运营成本，超过现有技术。 需要较少的乘客燃料，因为每个乘客的机身重量和湿润面积较小。 由于多座位座椅结构中乘客座位的总体成本较低，飞机的净利润和投资回报率也有所增加。

公开(公告)号：US20100155528A1

公开(公告)日：2010-06-24

申请号：US12388696

申请日：2009-02-19

申请人： Alberto Balsa Gonzalez ,  Francisco De Paula Burgos Gallego

发明人： Alberto Balsa Gonzalez ,  Francisco De Paula Burgos Gallego

IPC分类号： B64C9/00 ,  B64C3/00

CPC分类号： B64C5/02 ,  B64C3/28 ,  B64C9/00

摘要： Trailing edge (3) of an aircraft stabilizer surface (1), where this surface (1) is manufactured of a composite material and comprises an outer cladding (40) and an inner cladding (41) that are connected by a connecting clip type element (20) on this trailing edge (3), the connecting clip type element (20) comprising at its ends some recesses (23) used for coupling to the inner zone of the upper and lower claddings (40, 41) of the stabilizer surface (1), such that the connecting clip type element (20) is flexible enough to be pinched so that its ends will be housed, by means of these recesses (23), between the outer and inner claddings (40, 41) of the aircraft stabilizer surface (1), whereby the outer zone of the stabilizer surface (1), on its trailing edge (3), is formed by a continuous aerodynamic surface without changes of gradient.

摘要翻译： 飞机稳定器表面（1）的后缘（3），其中该表面（1）由复合材料制成并且包括外包层（40）和内包层（41），所述外包层（40）和内包层（41）通过连接夹式元件 （20）在所述后缘（3）上，所述连接夹型元件（20）在其端部包括用于联接到所述稳定器表面的上和下包层（40,41）的内部区域的一些凹部（23） （1），使得连接夹式元件（20）具有足够的柔性以被夹紧，使得其端部将通过这些凹部（23）容纳在外部和内部包层（40,41）之间， 飞机稳定器表面（1），由此在其后缘（3）上的稳定器表面（1）的外部区域由连续的空气动力学表面形成，而不改变梯度。

公开(公告)号：US20100155524A1

公开(公告)日：2010-06-24

申请号：US12396755

申请日：2009-03-03

申请人： Thomas C. Maganas

发明人： Thomas C. Maganas

IPC分类号： B64C1/00 ,  C23C4/12 ,  B64C27/04 ,  B64C3/00 ,  B64C9/00 ,  B64C11/20 ,  B64C5/06 ,  F01D5/14

CPC分类号： C23C30/00 ,  B64C21/10 ,  C23C16/26 ,  C23C16/44 ,  C23C16/4488 ,  F01D5/145 ,  F01D5/288 ,  Y02T50/166 ,  Y02T50/673

摘要： A monomolecular carbon-based film can be placed on an aircraft part, such as the leading edge designed to directly impinge against air during flight, ascent or descent, in order to form a smooth surface having increased lubricity and reduced air friction. The aircraft part may be in the form of a helicopter rotor, wing, propeller, fin, aileron, nose cone, and the like. The monomolecular carbon-based film can be deposited on the aircraft part, for example, using a reactor that includes a bed of silica and through which emissions from a diesel engine are passed. The monomolecular carbon-based film decreases air friction and increased lift of a modified aircraft that includes an aircraft part treated with the film. It also provides a structured shock absorber.

摘要翻译： 单分子碳基膜可以放置在飞机部件上，例如设计成在飞行，上升或下降期间直接冲击空气的前缘，以形成具有增加的润滑性和降低的空气摩擦的光滑表面。 飞机部件可以是直升机转子，翼，螺旋桨，翅片，副翼，鼻锥等的形式。 单分子碳基膜可以沉积在飞行器部件上，例如使用包括二氧化硅床并通过柴油发动机排放的反应器。 单分子碳基膜减少了空气摩擦并增加了改进的飞机的升力，其中包括用薄膜处理的飞机零件。 它还提供一个结构化的减震器。

公开(公告)号：US07686256B2

公开(公告)日：2010-03-30

申请号：US11226033

申请日：2005-09-14

申请人： Daniel N. Miller ,  David D. Young

发明人： Daniel N. Miller ,  David D. Young

IPC分类号： B64C3/00 ,  B64C5/00

CPC分类号： F15D1/12 ,  B64C21/04 ,  B64C23/00 ,  B64C23/04 ,  B64C2230/18 ,  Y02T50/166

摘要： The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices (submerged in the boundary layer) to create disturbances in the flow field that inhibit the growth of larger vortical structures and/or to energize the aft body shear layer to keep the shear layer attached the aft body surface. These undesirable aerodynamic phenomena produce increased vehicle drag which harms vehicle range, persistence, and loiter capabilities. Additionally, the unsteady nature of the turbulent vortical structures shed in the aft body wake region may produce increased dynamic buffeting and aft body heating by entraining nozzle jet exhaust (a.k.a. jet wash) —requiring additional structural support, shielding, and vehicle weight.

摘要翻译： 本发明提供了流场控制技术，其适应后身体区域流场以消除或减轻大量分离的流场区域和相关联的不稳定涡旋流场结构的发展。 本发明的实施例使用流动控制装置（浸没在边界层中）的一个或多个分布式阵列在流场中产生阻碍较大涡旋结构生长的干扰和/或使后身体剪切层通电以保持 剪切层附着在船体后表面。 这些不期望的空气动力学现象产生增加的车辆阻力，这损害车辆范围，持久性和怠速能力。 另外，在船尾身体尾部区域中流动的湍流涡旋结构的不稳定性质可以通过夹带喷嘴喷射排气（例如喷射洗涤） - 需要额外的结构支撑，屏蔽和车辆重量来产生增加的动态缓冲和后体加热。

公开(公告)号：US20100071771A1

公开(公告)日：2010-03-25

申请号：US12589504

申请日：2009-10-22

申请人： Alistair K. Chan ,  Roderick A. Hyde ,  Nathan P. Myhrvold ,  Clarence T. Tegreene ,  Lowell L. Wood, JR.

发明人： Alistair K. Chan ,  Roderick A. Hyde ,  Nathan P. Myhrvold ,  Clarence T. Tegreene ,  Lowell L. Wood, JR.

IPC分类号： G05D7/00 ,  F16L9/00 ,  B64C3/00 ,  B64B1/40 ,  B61B13/00 ,  B61D17/02

CPC分类号： E04H12/02 ,  B64B1/40 ,  Y10T137/0318

摘要： A system and method is described generally for affecting atmospheric change. The system and method include providing a high altitude conduit or track. The system and method also include providing a first material through the conduit or via a payload delivery system. Further, the system and method include expelling the first material into the atmosphere at high altitude.

摘要翻译： 一般描述影响大气变化的系统和方法。 该系统和方法包括提供高空导管或轨道。 该系统和方法还包括通过导管或通过有效载荷递送系统提供第一材料。 此外，该系统和方法包括将第一种材料排出到高空的大气中。

公开(公告)号：US20080265094A1

公开(公告)日：2008-10-30

申请号：US12093151

申请日：2006-12-15

申请人： Sjoerd Van Der Veen ,  Jean-Christophe Ehrstrom ,  Henri Gerard ,  Francois Lemaitre

发明人： Sjoerd Van Der Veen ,  Jean-Christophe Ehrstrom ,  Henri Gerard ,  Francois Lemaitre

IPC分类号： B64C3/00 ,  B21D53/88

CPC分类号： B64C3/185 ,  B23K20/122 ,  B23K2101/28 ,  Y10T29/49622

摘要： In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

摘要翻译： 在用于制造用于航空结构的结构元件的方法中，至少第一和第二金属块可用，第一金属块的压缩下的弹性极限大于第二金属块的弹性极限。 第一金属块被加工成获得第一加工的整体部分，其具有第一腹板部分和至少一个纵梁元件，其高度使得纵梁部分延伸超出第一腹板部分。 通过成形第二金属块来制备至少一个具有至少第二腹板部分的第二部分，该第二腹板部分能够与第一腹板部分协作以形成腹板。 通过将第一和第二纤维网部分端对端放置在其整个公共长度上来组装第一整体部分和第二部分。

公开(公告)号：US20060226290A1

公开(公告)日：2006-10-12

申请号：US11101255

申请日：2005-04-07

申请人： Christian Campbell

发明人： Christian Campbell

IPC分类号： B64C3/00 ,  B64C21/04

CPC分类号： F01D5/147 ,  F01D5/146 ,  F05D2240/301 ,  F05D2240/57 ,  F05D2260/20 ,  F05D2260/221 ,  F05D2300/21 ,  F05D2300/603

摘要： Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.

公开(公告)号：US20050269458A1

公开(公告)日：2005-12-08

申请号：US10884032

申请日：2004-07-02

申请人： Jayden Harman

发明人： Jayden Harman

IPC分类号： B63G8/00 ,  B64C23/06 ,  F15D1/10 ,  F15D1/12 ,  F42B10/00 ,  F42B10/24 ,  B64C3/00

CPC分类号： B64C23/06 ,  F15D1/009 ,  F15D1/10 ,  F42B10/24 ,  Y02T50/162 ,  Y10T137/0391

摘要： A vortex ring generator adapted to be associated with a body subjected to fluid flow, the vortex ring generator being adapted to produce a fluid flow in the form of a vortex ring with the fluid flow moving over the body from the vortex ring generator.

摘要翻译： 涡流发生器适于与经受流体流动的物体相关联，所述涡流环发生器适于产生涡流形式的流体流，其中流体流从涡环发生器移动到身体上。