公开(公告)号：US20100230547A1

公开(公告)日：2010-09-16

申请号：US12486023

申请日：2009-06-17

Applicant: Steven K. Tayman

Inventor： Steven K. Tayman

IPC: B64C27/24

CPC classification number: B64C27/24 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/108

Abstract: Systems and methods for transitioning an aircraft between helicopter and fixed wing flight modes are provided. In one embodiment, an aircraft comprises a plurality of wings each having a spar and a flap; a flap actuator configured to move the flap with respect to the spar; and a center section rotatably coupled to each spar. The center section includes at least one spar actuator configured to rotate at least one of the wings about a rotational axis of the spar when the aircraft transitions between helicopter and fixed wing flight modes.

Abstract translation: 提供了在直升机和固定翼飞行模式之间转换飞机的系统和方法。 在一个实施例中，飞机包括多个翼，每个翼具有翼梁和翼片; 翼片致动器，其构造成相对于翼梁运动翼片; 以及可旋转地联接到每个翼梁的中心部分。 中心部分包​​括至少一个翼梁致动器，其构造成当飞机在直升机和固定翼飞行模式之间转换时围绕翼梁的旋转轴线旋转至少一个翼。

公开(公告)号：US20100051741A1

公开(公告)日：2010-03-04

申请号：US12230638

申请日：2008-09-03

Applicant: Anvar Ismailov

Inventor： Anvar Ismailov

IPC: B64C1/00 ,  B64C3/38 ,  B64D37/04 ,  B64F1/04 ,  B64C11/00 ,  B64D27/24 ,  B64D27/00 ,  G05D1/02 ,  F41A9/00 ,  F42B15/00 ,  B64F1/02 ,  B64F1/00 ,  F02K7/00

CPC classification number: F42B10/64 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  F42B10/14

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract translation: 用于军事，陆上安全等操作的无人驾驶飞行器包括设置有可折叠翼的机身，其具有前缘翼片和后缘副翼，其可以在发射时上升操作以控制翼折叠的飞行图案，翼部署成 在适当的时候打开展开位置。 车辆被容纳在发射的荚内，并且提供着陆甲板以在车辆返回陆地时减速和阻止车辆。

公开(公告)号：US07584925B2

公开(公告)日：2009-09-08

申请号：US11877201

申请日：2007-10-23

Applicant: Stephen W. Miller ,  Matthew Velazquez

Inventor： Stephen W. Miller ,  Matthew Velazquez

IPC: B64C3/56 ,  B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

Abstract: A portable unmanned air vehicle and launcher system that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract translation: 一种便携式无人机和发射系统，包括具有压力管的可折叠无人机; 用于发射气体的发射气藏; 操作地连接到发射气体储存器并具有位于空中载体的压力管中的自由端的发射管; 位于发射管内的自由活塞; 和自由活塞止挡件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中，并且将自由活塞从初始位置推动到自由活塞由自由活塞停止的终止位置。

公开(公告)号：US20090206196A1

公开(公告)日：2009-08-20

申请号：US12358036

申请日：2009-01-22

Applicant: Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Thomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

Inventor： Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Thomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

IPC: B64C3/56 ,  B64C3/30

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/127

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract translation: 公开了一种可用于能够在85,000英尺或以上的高度操作的高空飞机的折叠翼。 可折叠翼可以采用螺旋折叠展开，其中可折叠翼的每个片段之间的铰链稍微偏离垂直线。 连续定位的翼片彼此折叠。 或者，铰链基本上垂直，使得每个相应的翼段相对于下一个翼段线性地折叠。 具有可充气臂的充气肋可以被充气以提供抵抗两个相邻臂的力，从而将翼段展开完整的180度旋转。

公开(公告)号：US20090032648A1

公开(公告)日：2009-02-05

申请号：US12058520

申请日：2008-03-28

Applicant: Jerome Pearson

Inventor： Jerome Pearson

IPC: B64D27/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

Abstract: A long endurance powered aircraft includes a fuselage, a propeller coupled to the fuselage, a wing coupled to the fuselage, and an energy storage system disposed within the fuselage. The wing includes an adjustable surface area including solar cells configured to collect incident solar energy and convert the collected incident solar energy to electrical energy for powering the aircraft during daylight flight. The energy storage system is configured to convert excess electrical energy converted from collected incident solar energy to chemical energy, store the chemical energy, and convert the stored chemical energy to electrical energy for powering the aircraft during night flight.

Abstract translation: 长寿命动力飞机包括机身，与机身相连的螺旋桨，与机身相连的机翼，以及设置在机身内的能量存储系统。 机翼包括可调节的表面区域，包括被配置为收集入射的太阳能并且将收集的入射太阳能转换成电能的太阳能电池，以在日间飞行期间为飞机供电。 能量存储系统被配置为将从收集的入射太阳能转换的过量电能转换成化学能，存储化学能，并将存储的化学能转换成电能，以在夜间飞行期间为飞行器供电。

公开(公告)号：US20080210818A1

公开(公告)日：2008-09-04

申请号：US11822278

申请日：2007-07-03

Applicant: Tien-Seng Chiu ,  Jay Willmott ,  Kirk Jenkins

Inventor： Tien-Seng Chiu ,  Jay Willmott ,  Kirk Jenkins

IPC: B64C1/00 ,  B64C1/10 ,  A45C5/00

CPC classification number: B64C1/00 ,  A45C5/00 ,  A45C13/02 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2201/203

Abstract: A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

Abstract translation: 具有机身，鼻锥，左翼片，右翼片和尾部的模块化无人驾驶飞行器（UAV）。 尾部和鼻锥每个通过配合的隔板结构连接到机身，提供快速的连接能力，同时易于分离，以便使UAV在这些连接点处分裂，从而吸收或消散着陆时的冲击。 无人机能够在现场快速组装两人发射和数据检索，以及快速拆卸到这五个部件中，用于运输和存储，可以作为背包携带的高度紧凑的运输箱。

公开(公告)号：US20070034737A1

公开(公告)日：2007-02-15

申请号：US11200319

申请日：2005-08-09

Applicant: Glenn Tierney

Inventor： Glenn Tierney

IPC: B64C39/00

CPC classification number: B64C39/005 ,  B64B1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/165

Abstract: A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of the vehicle (prolate flight). Also, rotation of the hub can be stopped and the airfoils used for fixed wing flight.

Abstract translation: 沿着飞行路径移动飞行器的系统和方法包括安装在车辆的相对侧上的可旋转轮毂。 细长的翼型件平行于公共轮毂轴线安装在轮毂上，以便在叶片路径上围绕轮毂轴线旋转。 每个翼型件限定弦线，并且该系统包括齿轮组件，在轮毂旋转期间，其中翼型弦线保持与叶片路径相切的第一模态（curtate飞行）和第二模态，其中翼型弦线保持平行于 车辆的飞行路线（长跑）。 此外，轮毂的旋转可以停止，翼型件用于固定翼飞行。

公开(公告)号：US07090166B2

公开(公告)日：2006-08-15

申请号：US10758948

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Andreas H. von Flotow

Inventor： Brian D. Dennis ,  Andreas H. von Flotow

IPC: B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/06

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes an extendable boom. A launch carriage is positioned on a launch guide structure of the boom and carries the aircraft during takeoff. An energy reservoir is configured to provide energy to the launch carriage during takeoff of the aircraft, and can absorb energy from the launch carriage to decelerate the launch carriage after takeoff. The apparatus can further include a transmission that smoothly and rapidly accelerates and/or decelerates the launch carriage.

Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括可扩展起重臂的装置发射。 发射架位于起重臂的发射导向结构上，并在起飞时承载飞机。 能量储存器构造成在飞行器起飞期间向发射台提供能量，并且可以从起飞台吸收能量，以在起飞后减速发射台。 该装置还可以包括使发射台平滑且快速地加速和/或减速的变速器。

公开(公告)号：US07059564B2

公开(公告)日：2006-06-13

申请号：US10758940

申请日：2004-01-16

Applicant: Brian D. Dennis

Inventor： Brian D. Dennis

IPC: B64F1/02

CPC classification number: B64F1/06 ,  B63B27/26 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured by a recovery line in flight, a process that can be aided by a line capture device having a retainer with two portions spaced apart by a distance great enough to receive the recovery line, e.g., to capture the recovery line with increased security. The line capture device can be operatively mounted on a lifting surface of the aircraft.

Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由飞行中的恢复线捕获，该过程可以由具有保持器的线捕获装置辅助，该保持器具有两个间隔开足够大的距离以接收恢复线，例如捕获 恢复线增加了安全性。 线捕获装置可以可操作地安装在飞行器的提升表面上。

公开(公告)号：US20060102798A1

公开(公告)日：2006-05-18

申请号：US11030379

申请日：2005-01-06

Applicant: Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: B64C39/12 ,  B64C13/20

CPC classification number: B64C39/024 ,  B64C1/26 ,  B64C3/14 ,  B64C13/20 ,  B64C39/08 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185

Abstract: The present invention provides an unmanned airborne reconnaissance vehicle having a fuselage, a forward wing pair and a rearward wing pair vertically separated by a gap and staggered fore and aft therebetween such that a general biplane configuration is formed. The present invention provides a pair of wing tip plates for joining the wing tips of the forward and rearward wings. The unmanned airborne reconnaissance vehicle of the present invention includes a power plant to propel the vehicle through the air and a generally T-shaped tail having a vertical stabilizer including a rudder and a full span elevator.