公开(公告)号：US20030226935A1

公开(公告)日：2003-12-11

申请号：US10286937

申请日：2002-11-02

Inventor： Matthew D. Garratt ,  Gary H. Bray ,  Diana K. Denzer ,  Patrick Ulysse

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

CPC classification number: B64C3/24 ,  B21B1/026 ,  B21B1/08 ,  B21B2001/022 ,  B21B2003/001 ,  B21C23/001 ,  B21C23/14 ,  C22C21/16 ,  C22F1/053 ,  C22F1/057 ,  Y10S148/902 ,  Y10T428/12375 ,  Y10T428/12389 ,  Y10T428/1241

Abstract: An extruded structural member having improved damage tolerance. The structural member comprising: a base section; a rib stiffening section having at least one pair of structural ribs, the structural ribs integral with the base section and projecting outwardly thereof; and at least one intra-rib area positioned between the pair of structural ribs, the intra-rib area having a microstructure with intentionally increased amounts of fiber texture to reduce the rate of fatigue crack growth in the extruded structural member.

Abstract translation: 具有改善的损伤容限的挤压结构件。 所述结构构件包括：基部; 肋加强部分，其具有至少一对结构肋，所述结构肋与所述基部一体并向外突出; 以及位于所述一对结构肋之间的至少一个肋内区域，所述肋内区域具有有意增加的纤维织构数量的微结构，以降低所述挤压结构构件中的疲劳裂纹扩展速率。

公开(公告)号：US20030197089A1

公开(公告)日：2003-10-23

申请号：US10125579

申请日：2002-04-19

Inventor： William L. Klima

IPC: B64C001/00

CPC classification number: B64C1/00 ,  B64C3/56 ,  B64C39/026 ,  B64C2001/0045 ,  B64C2001/0063 ,  B64C2001/0072 ,  B64D17/00 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/43 ,  Y10S244/90 ,  Y10S244/904

Abstract: A personal aircraft device (nullPADnull) and a powered personal aircraft device (nullPPADnull) configured to be ridden and/or releasably connected to a person or user. The personal aircraft device can be configured to provide a large array of maneuvers during sky diving or free fall, and perform somewhat as a lifting device requiring a parachute landing and/or alternatively can be configured to glide to a safe landing. The personal aircraft device and powered personal aircraft device according to the present invention provide for high performance, speed and/or maneuvering of a person or user during free fall, and can provide increased or significantly increased gliding capability versus free falling or deployment of a high performance parachute.

Abstract translation: 个人飞机设备（“PAD”）和被配置为被人和用户骑乘和/或可释放地连接的被动式个人飞机设备（“PPAD”）。 个人飞行器装置可以被配置为在天空潜水或自由落体期间提供大量的动作，并且稍微执行需要降落伞着陆的提升装置和/或可替代地被配置成滑动到安全着陆。 根据本发明的个人飞机设备和动力式个人飞机设备在自由落体期间提供人或者使用者的高性能，速度和/或机动性，并且可以提供增加的或显着增加的滑翔能力与自由落体或部署高 性能降落伞

公开(公告)号：US20030192986A1

公开(公告)日：2003-10-16

申请号：US10437763

申请日：2003-05-14

Inventor： Mark A. Page ,  Jennifer P. Whitlock ,  Matthew W. Wilks

IPC: B64C001/00 ,  B64C003/00

CPC classification number: B64C1/0009 ,  B64C39/10 ,  B64C2039/105 ,  B64C2211/00

Abstract: A blended wing body aircraft having a modular body having a body that includes a plurality of laterally-extending body structures. Changes to the cargo capacity of the aircraft is accomplished through the employment of body structures that are wider or narrower. Configuration in this manner provides the aircraft with a structure that is relatively strong and efficient. While the body structures of this embodiment are not shared across a family of variously sized aircraft, the base design of the body structures is readily modifiable to adjust for an increase or decrease in width associated with a desired change to the aircraft's cargo capacity.

Abstract translation: 具有模块主体的混合翼体飞机具有包括多个横向延伸的主体结构的主体。 通过使用更宽或更窄的身体结构，可以改变飞机的货物能力。 以这种方式进行的配置为飞机提供了相对较强和高效的结构。 虽然该实施例的车身结构不是在不同尺寸的飞机系列之间共享，但是主体结构的基本设计是容易地可修改的，以适应与飞机货物容量的期望变化相关联的宽度的增加或减少。

公开(公告)号：US20030173460A1

公开(公告)日：2003-09-18

申请号：US10366606

申请日：2003-02-13

Inventor： W. Cullen Chapman JR.

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

CPC classification number: B29D24/004 ,  B29C53/60 ,  B29C53/821 ,  B29C53/822 ,  B29C70/32 ,  B29L2031/3076 ,  B64C1/06 ,  B64C2001/0072 ,  Y02T50/43

Abstract: Integrally stiffened and formed, load carrying structures comprising a plurality of elongated thin-walled tubes placed co-extensively in a complementary side-by-side fashion which together form a hollow structure having a desired external contour. Integral skins forming the external and internal surfaces of the structure cooperatively therewith. The structure can be formed with an underlying internal support member spanning the interior of the load carrying structure, thereby connecting opposite sides of the structure together. Also, each of the tubes are wound with fibers in controlled orientations generally paralleling the direction of the loads applied to the tubes to optimize the strength to weight ratio of the tubes.

Abstract translation: 整体加强和形成的承载结构包括多个细长的薄壁管，其以互补的并排方式共同放置，共同形成具有期望的外部轮廓的中空结构。 与该结构的外表面和内表面协同地形成的整体表皮。 该结构可以形成有横跨负载承载结构的内部的底部内部支撑构件，从而将结构的相对侧连接在一起。 而且，每个管子以受控取向通常与施加在管上的负载方向平行的纤维缠绕，以优化管的强度与重量比。

公开(公告)号：US20030146341A1

公开(公告)日：2003-08-07

申请号：US10198369

申请日：2002-07-18

Inventor： Eric Thomas Schmidt

IPC: B64C001/00

CPC classification number: B64C23/04 ,  B63B1/32 ,  Y02T70/12

Abstract: The Shock Wave Absorber is an inverted, rotated sinusoidal form inserted in the foremost tip of a vessel traveling in a fluid, with an opening to the nose, which provides orientation for turbulent air, water, etc . . .

Abstract translation: 冲击波吸收器是一个倒置的，旋转的正弦曲线形式，插入在流体中行进的容器的最前端，具有朝向鼻部的开口，其提供湍流空气，水等的取向。 。 。

公开(公告)号：US20030141409A1

公开(公告)日：2003-07-31

申请号：US10310415

申请日：2002-12-05

Inventor： Derek L. Lisoski ,  Greg T. Kendall

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

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  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 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

Abstract translation: 太阳能可再充电，长时间，跨度的飞翼，没有机身或方向舵。 拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差速推力来转弯，俯仰和偏航。 机翼构造成在飞行载荷下变形以定位螺旋桨，使得可以实现控制。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。

公开(公告)号：US20030130771A1

公开(公告)日：2003-07-10

申请号：US10269169

申请日：2002-10-10

Inventor： Kelly C. Crank

IPC: G05D001/00 ,  B64C001/00 ,  G05D003/00 ,  G06F007/00 ,  G06F017/00 ,  G08B021/00

CPC classification number: G08G5/0013 ,  B64D45/0015 ,  B64D2045/004 ,  B64D2045/0045 ,  B64D2045/0055 ,  G08G5/0082 ,  G08G5/0086

Abstract: A system for monitoring an aircraft receives navigation signals and deriving a position vector therefrom and also asserts an alert signal in the event that the altitude of the aircraft above ground level is less than a predetermined value. The system samples the position vector at a selected sample rate and outputs a succession of samples of the position vector, the sample rate depending on whether the alert signal has been asserted. Data packets that contain respective samples of the position vector are transmitted to a ground-based receiving station. The ground-based receiving station may calculate secondary data.

Abstract translation: 用于监视飞行器的系统接收导航信号并从其导出位置矢量，并且在地面以上的飞行器的高度小于预定值的情况下也发出报警信号。 系统以选定的采样率对位置矢量进行采样，并输出一连串的位置矢量采样，取样速率取决于报警信号是否被确认。 将包含位置矢量的相应样本的数据包发送到地面接收站。 地面接收站可以计算二次数据。

公开(公告)号：US20030130768A1

公开(公告)日：2003-07-10

申请号：US10272293

申请日：2002-10-17

Inventor： Paul Eglin

IPC: B64C001/00 ,  G05D001/00 ,  G05D003/00 ,  G06F007/00 ,  G06F017/00

CPC classification number: G05D1/0825

Abstract: Process and device for determining in real time the behavior of a craft, in particular of an aircraft. Said device (1) comprises first means (2) for determining, from a current linear model modeling the behavior of the craft, a vector null illustrating an equilibrium state, second means (3) connected to said first means (2), for determining, from this vector null, the values at equilibrium of parameters of said linear model, third means (5) connected to said second means (3), for calculating, from at least some of these values, the dynamic component of the behavior of the craft, and fourth means (7) connected to said first and third means (2, 5), for introducing this dynamic component into said linear model so as to obtain a new current linear model and to deduce the behavior of said craft therefrom.

Abstract translation: 用于确定飞行器，特别是飞行器的行为的过程和装置。 所述装置（1）包括第一装置（2），用于根据当前线性模型确定飞行器的行为，示出平衡状态的矢量羔羊，连接到所述第一装置（2）的第二装置（3），用于确定 从所述向量lambd中，所述线性模型的参数平衡的值，连接到所述第二装置（3）的第三装置（5））用于从这些值中的至少一些值计算所述线性模型的行为的动态分量 工具和连接到所述第一和第三装置（2,5）的第四装置（7），用于将该动力分量引入到所述线性模型中，以获得新的当前线性模型并推导出所述工艺的行为。

公开(公告)号：US20030127563A1

公开(公告)日：2003-07-10

申请号：US10280271

申请日：2002-10-25

Inventor： Richard J. LaConte

IPC: B64C001/00

CPC classification number: B64G1/52 ,  B64C1/14 ,  B64C1/1423 ,  B64C1/1446 ,  B64C1/1469 ,  B64C1/32 ,  B64C2001/009

Abstract: A differential pressure sensing release system and apparatus specifically adapted for use with an aircraft or spacecraft compartment panel. The apparatus utilizes a mechanism activated by a pressure differential acting on a diaphragm(s) to trigger a single latch bolt or series of latch bolts or other retention mechanisms, thereby releasing the panel. The apparatus thus provides a means of equalizing the pressure differential between adjacent compartments, eliminating potential damage due to forces created by the pressure differential.

Abstract translation: 一种特别适用于飞机或航天器隔间板的差压传感释放系统和装置。 该装置利用由作用在隔膜上的压差激活的机构以触发单个闩锁栓或一系列闩锁螺栓或其他保持机构，从而释放面板。 因此，该装置提供了一种均衡相邻隔室之间的压力差的装置，消除了由压差产生的力引起的潜在损害。

公开(公告)号：US20030127557A1

公开(公告)日：2003-07-10

申请号：US10215221

申请日：2002-08-07

Inventor： Norman G. Anderson ,  Douglas Huff ,  Elizabeth A. Anderson

IPC: B64C001/00

CPC classification number: B64D43/00 ,  G01C23/00

Abstract: Flight information is displayed using visual indications that resemble real world visual cues. For example, left and right side attitude displays extend vertically along each side of the windshield and a yaw display extends along a lower edge of the windshield. The attitude displays employ reference indications and outermost indications which track the position of the actual horizon. The yaw display employs outermost indications spaced from a reference indication a distance proportional to the rate of turn. Indexing of indications between the references and the outermost indications provides the appearance of movement representing climb, descent and turns. The rate and direction of indexing may be proportional to the rate and direction of change. Alternatively, indications such as lines are presented on a display screen, the lines being vertically displaced from a reference to represent angle of attack, slanted or angled to indicate the degree and direction of bank, and indexed to create the appearance of movement representing climb, descent and turns.

Abstract translation: 使用与现实世界的视觉线索相似的视觉指示显示飞行信息。 例如，左右姿势显示器沿挡风玻璃的每一侧垂直地延伸，并且偏航显示器沿挡风玻璃的下边缘延伸。 态度显示使用参考指示和跟踪实际水平位置的最外面的指示。 偏航显示器使用与参考指示间隔开的最小指示与转弯速度成比例的距离。 参考和最外层指示之间的指示索引提供了表示爬升，下降和转弯的运动的出现。 索引的速率和方向可能与变化的速度和方向成比例。 或者，诸如线的指示呈现在显示屏幕上，线从参考垂直移位以表示迎角，倾斜或成角度以指示银行的程度和方向，并被索引以产生表示爬升的运动的外观， 下降和转弯